US20190249875A1 - Liner for a Gas Turbine Engine Combustor - Google Patents

Abstract

A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a film cooling hole extending from the second side to the first side, the film cooling hole defining an outlet on the first side of the liner, the liner including an airflow feature on the first side of the of the liner adjacent to the outlet of the film cooling hole to increase a cooling of the liner.

Description

FIELD
• The present subject matter relates generally to a liner for a gas turbine engine combustor.
BACKGROUND
• A gas turbine engine typically includes an inlet, one or more compressors, a combustor, and at least one turbine. The compressors compress air which is channeled to the combustor where it is mixed with fuel. The mixture is then ignited for generating hot combustion gases. The combustion gases are channeled to the turbine(s) which extracts energy from the combustion gases for powering the compressor(s), as well as for producing useful work to propel an aircraft in flight or to power a load, such as an electrical generator. For example, in at least certain embodiments, the gas turbine engine may further include a fan driven by the one or more turbines.
• Additionally, typical combustion sections include one or more liners defining a combustion chamber. Film cooling holes may be defined within these liners to form a cooling air film on a hot side of the liner to maintain the liner within a desired operating temperature range. Accordingly, the film cooling holes allow for a stream of relatively cool compressed air to flow into the combustion chamber. Notably, however, hotspots may form around the stream of compressed air flowing through the film cooling holes into the combustion chamber, potentially damaging or prematurely wearing the liner. Accordingly, a liner capable of reducing, or better managing, these hotspots would be useful.
BRIEF DESCRIPTION
• Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.
• In one exemplary embodiment of the present disclosure, a gas turbine engine combustor is provided. The gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a film cooling hole extending from the second side to the first side, the film cooling hole defining an outlet on the first side of the liner, the liner including an airflow feature on the first side of the of the liner adjacent to the outlet of the film cooling hole to increase a cooling of the liner.
• In certain exemplary embodiments the combustion chamber defines an airflow direction over the outlet of the film cooling hole on the first side of the liner, and wherein the airflow feature is positioned at least partially downstream of the outlet along the airflow direction.
• For example, in certain exemplary embodiments the airflow feature is a first airflow feature, wherein the liner further includes a second airflow feature also positioned at least partially downstream of the outlet along the airflow direction, wherein the combustion chamber further defines a transverse direction perpendicular to the airflow direction, and wherein the second airflow feature is spaced from the first airflow feature along the transverse direction.
• For example, in certain exemplary embodiments the first airflow feature is a protrusion on the first side of the liner extending into the combustion chamber, and wherein the second airflow feature is an indentation on the first side of liner.
• In certain exemplary embodiments the combustion chamber defines an airflow direction over the outlet of the film cooling hole on the first side of the liner, and wherein the airflow feature is positioned at least partially upstream of the outlet along the airflow direction.
• For example, in certain exemplary embodiments the airflow feature is a first airflow feature, wherein the liner further includes a second airflow feature also positioned at least partially upstream of the outlet along the airflow direction, wherein the combustion chamber further defines a transverse direction perpendicular to the airflow direction, and wherein the second airflow feature is spaced from the first airflow feature along the transverse direction.
• For example, in certain exemplary embodiments the first airflow feature is a protrusion on the first side of the liner extending into the combustion chamber, and wherein the second airflow feature is an indentation on the first side of liner.
• For example, in certain exemplary embodiments the first airflow feature is a protrusion on the first side of the liner extending into the combustion chamber, and wherein the second airflow feature is also a protrusion on the first side of the liner extending into the combustion chamber.
• For example, in certain exemplary embodiments the liner further includes a third airflow feature and a fourth airflow feature, wherein the third airflow feature and the fourth airflow feature are each positioned at least partially downstream of the outlet along the airflow direction and spaced from one another along the transverse direction.
• For example, in certain exemplary embodiments at least one of the first airflow feature, the second airflow feature, the third airflow feature, and the fourth airflow feature is a protrusion extending into the combustion chamber, and wherein at least one of the first airflow feature, the second airflow feature, the third airflow feature, and the fourth airflow feature is an indentation on the first side of liner.
• In certain exemplary embodiments the combustion chamber defines an airflow direction over the outlet of the film cooling hole on the first side of the liner, wherein the airflow feature is a first airflow feature, wherein the liner further includes a second airflow feature, wherein the first and second airflow features are aligned with one another and the outlet of the film cooling hole along the airflow direction, and wherein the first airflow feature is positioned adjacent to the second airflow feature along the airflow direction.
• In certain exemplary embodiments the combustion chamber defines an airflow direction over the film cooling hole on the first side of the liner and a transverse direction perpendicular to the airflow direction, wherein the airflow feature defines a length along the airflow direction and a width along the transverse direction, and wherein the width of the airflow feature is greater than the length of the airflow feature and up to about five times the length of the airflow feature.
• In certain exemplary embodiments the film cooling hole defines a diameter at the outlet, wherein the airflow feature defines a width and a height, wherein the width of the airflow feature is greater than or equal to about 0.1 times the diameter of the of the film cooling hole and up to about 6 times the diameter of the film cooling hole, and wherein the height of the airflow feature is greater than or equal to about 0.1 times the diameter of the film cooling hole and up to about 6 times the diameter of the film cooling hole.
• In certain exemplary embodiments the film cooling hole is a first film cooling hole of a plurality of film cooling holes defined by the liner.
• In certain exemplary embodiments the film cooling hole defines a substantially constant diameter along a length thereof.
• In another exemplary embodiment of the present disclosure, a gas turbine engine is provided. The gas turbine engine includes a combustion section including a combustor liner, the combustor liner defining at least in part a combustion chamber, a hot side exposed to the combustion chamber, a cold side opposite the hot side, and a plurality of film cooling holes extending from the cold side to the hot side, the plurality of film cooling holes each defining an outlet on the hot side of the liner, the liner including a plurality of airflow features on the hot side of the of the liner, each airflow feature of the plurality of airflow features positioned adjacent to the outlet of one of the plurality of film cooling holes to increase a cooling of the liner.
• In certain exemplary embodiments the combustion chamber defines an airflow direction over the outlets of the plurality of film cooling holes on the hot side of the liner, and wherein the airflow features are each positioned at least partially downstream of the outlet of one of the plurality of film cooling holes along the airflow direction.
• In certain exemplary embodiments the combustion chamber defines an airflow direction over the outlets of the plurality of film cooling holes on the hot side of the liner, and wherein the airflow features are each positioned at least partially upstream of the outlet of one of the plurality of film cooling holes along the airflow direction.
• In certain exemplary embodiments the combustion chamber defines an airflow direction over the outlets of the plurality of film cooling holes on the hot side of the liner and a transverse direction perpendicular to the airflow direction, wherein each airflow feature defines a length along the airflow direction and a width along the transverse direction, and wherein the width of each airflow feature is greater than the length of the airflow feature and up to about five times the length of the airflow feature.
• In certain exemplary embodiments a first film cooling hole of the plurality of film cooling holes defines a diameter at its outlet, wherein a first airflow feature of the plurality of airflow features defines a width and a height, wherein the width of the first airflow feature is greater than or equal to about 0.1 times the diameter of the of the first film cooling hole and up to about 6 times the diameter of the first film cooling hole, and wherein the height of the first airflow feature is greater than or equal to about 0.1 times the diameter of the first film cooling hole and up to about 6 times the diameter of the first film cooling hole.
• These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
• A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended Figs., in which:
• FIG. 1 is a perspective view of a gas turbine engine combustor in accordance with an exemplary embodiment of the present disclosure.
• FIG. 2 is a perspective view of a section of a liner of the exemplary gas turbine engine combustor ofFIG. 1.
• FIG. 3 is a plan view of one side of a section the exemplary linerFIG. 2.
• FIG. 4 is a cross-sectional view of the exemplary liner ofFIG. 2 along an airflow direction.
• FIG. 5 is a cross-sectional view of a liner in accordance with another exemplary embodiment of the present disclosure along an airflow direction.
• FIG. 6 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with another exemplary embodiment of the present disclosure.
• FIG. 7 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with yet another exemplary embodiment of the present disclosure.
• FIG. 8 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with another exemplary embodiment of the present disclosure.
• FIG. 9 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with yet another exemplary embodiment of the present disclosure
• FIG. 10 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with still another exemplary embodiment of the present disclosure.
• FIG. 11 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with another exemplary embodiment of the present disclosure.
• FIG. 12 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with yet another exemplary embodiment of the present disclosure
• FIG. 13 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with still another exemplary embodiment of the present disclosure.
• FIG. 14 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with yet another exemplary embodiment of the present disclosure.
• FIG. 15 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with still another exemplary embodiment of the present disclosure.
• FIG. 16 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with yet another exemplary embodiment of the present disclosure.
• FIG. 17 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with still another exemplary embodiment of the present disclosure.
• FIG. 18 is a plan view of one side of a section of a liner of a gas turbine engine combustor in accordance with yet another exemplary embodiment of the present disclosure.
• FIG. 19 is a cross-sectional view of the exemplary liner ofFIG. 18 along a tangential direction.
• It will be appreciated that use of the same or similar numbers throughout the Figures may refer to same or similar part.
DETAILED DESCRIPTION
• Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention.
• As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.
• The terms “forward” and “aft” refer to relative positions within a gas turbine engine or vehicle, and refer to the normal operational attitude of the gas turbine engine or vehicle. For example, with regard to a gas turbine engine, forward refers to a position closer to an engine inlet and aft refers to a position closer to an engine nozzle or exhaust.
• The terms “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows.
• The terms “coupled,” “fixed,” “attached to,” and the like refer to both direct coupling, fixing, or attaching, as well as indirect coupling, fixing, or attaching through one or more intermediate components or features, unless otherwise specified herein.
• The singular forms “a”, “an”, and “the” include plural references unless the context clearly dictates otherwise.
• Approximating language, as used herein throughout the specification and claims, is applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about”, “approximately”, and “substantially”, are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value, or the precision of the methods or machines for constructing or manufacturing the components and/or systems. For example, the approximating language may refer to being within a 10 percent margin.
• Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other.
• Referring to the drawings wherein identical reference numerals denote the same elements throughout the various views,FIG. 1 shows acombustor10 of the type suitable for use in a gas turbine engine. For example, theexemplary combustor10 depicted may be utilized within an aeronautical gas turbine engine, such as a turboshaft engine, turboprop engine, turbojet engine, etc. Additionally, or alternatively, thecombustor10 may be utilized in any other suitable gas turbine engine, such as an aeroderivative gas turbine engine, a power generation gas turbine engine, etc. As shown,combustor10, or rather the gas turbine engine within which thecombustor10 is installed (not shown) defines a longitudinal direction L, a radial direction R, and a circumferential direction C.
• As shown, thecombustor10 includes a liner, and more specifically, anouter liner12 and aninner liner14 disposed between anouter combustor casing16 and aninner combustor casing18. Outer andinner liners12,14 are radially spaced from each other to define at least in part acombustion chamber20.Outer liner12 andouter casing16 form anouter passage22 therebetween, andinner liner14 andinner casing18 form aninner passage24 therebetween. Acowl assembly26 is mounted to the upstream ends of outer andinner liners12,14. Anannular opening28 is formed incowl assembly26 for the introduction of compressed air intocombustor10. The compressed air is supplied from a compressor (not shown) in a direction generally indicated byarrow27 ofFIG. 1. The compressed air passes principally throughannular opening28 to support combustion and partially into outer andinner passages22 and24 where it is used to cool theliners12,14.
• Disposed between and interconnecting the outer andinner liners12,14 near their upstream ends is anannular dome plate30. A plurality of circumferentially spacedswirler assemblies32 is mounted indome plate30. Eachswirler assembly32 receives compressed air fromannular opening28 and fuel from a correspondingfuel tube34. The fuel and air are swirled and mixed byswirler assemblies32, and the resulting fuel/air mixture is discharged intocombustion chamber20. It is noted that althoughFIG. 1 illustrates one preferred embodiment of a single annular combustor, the present invention is equally applicable to any type of combustor, including double annular combustors, which uses multi-hole film cooling.
• It will be appreciated, however, that in other exemplary embodiments, thecombustor10 may have any other suitable configuration. For example, in other exemplary embodiments, thecombustor10 may be configured as one of a pulse detonation combustor, a rotating detonation combustor, a can combustor, a cannular combustor, or any other suitable type of combustor.
• Outer andinner liners12,14 each have an annular and axially extending configuration. In at least certain embodiments, the outer andinner liners12,14 may be a single shell, such as a single metal or metal alloy shell. However, in other embodiments, the outer andinner liners12,14 may instead be formed of a ceramic matrix composite material, or any other suitable material. Further, it will be appreciated that the outer andinner liners12,14 may be formed through any suitable process. For example, in certain embodiments, one or both of the outer andinner liners12,14 may be formed using an additive manufacturing, or 3D printing, process. Such may provide for a relatively cost-effective means for forming a liner having the various airflow features described below.
• Referring still toFIG. 1, theouter liner12 defines a first side and a second side opposite the first side. For the embodiment depicted, the first side is ahot side36 exposed to thecombustion chamber20 and facing the hot combustion gases incombustion chamber20, and the second side is acold side38 in contact with the relatively cool air inouter passage22. Similarly,inner liner14 defines a first side and a second side opposite the first side. As with theouter liner12, the first side of theinner liner14 is ahot side40 exposed to thecombustion chamber20 and facing the hot combustion gases incombustion chamber20, and the second side is acold side42 in contact with the relatively cool air ininner passage24. Bothliners12 and14 include a large number of closely spaced film cooling holes44 formed therein.
• Moreover, as is also depicted inFIG. 1, and as will be described in more detail below, the outer liner andinner liner12,14 each define a plurality of film cooling holes44 therein to form a cooling film on the first sides/hot sides36,40 thereof. Additionally, the outer liner andinner liner12,14 each also define a plurality of dilution holes48 for introducing dilution air to thecombustion chamber20. The dilution holes48 are arranged in rows, with the rows spaced generally along an axial direction A of the gas turbine engine, and the dilution holes48 of each row spaced generally along a circumferential direction C of the gas turbine engine. Additionally, as shown, the dilution holes48 are disposed in each of outer andinner liners12,14. Dilution holes48 are generally smaller in number than the film cooling holes44, and eachdilution hole48 has a cross-sectional area that is substantially greater than the cross-sectional area of one of the film cooling holes44. Dilution holes48, and to a smaller extent the film cooling holes44, serve to admit dilution air intocombustor chamber20 that will dilute the combustion products to get a leaner air/fuel mixture, quickly and efficiently.
• For example, conventionally the film cooling holes44 in typical combustor liners have relatively small diameters on the scale of between about 0.01 inches and about 0.1 inches, with a circumferential hole spacing between about 0.05 inches and about 0.25 inches. By contrast, the dilution holes48 conventionally have a relatively large diameters, such as greater than about 0.15 inches and up to about 1.5 inches.
• Referring now toFIG. 2, a perspective, cut out view of aliner50 for a combustor of a gas turbine engine in accordance with an exemplary embodiment of the present disclosure is provided. In certain exemplary embodiments, theliner50 ofFIG. 2 may be incorporated into theexemplary combustor10 described above with reference toFIG. 1. For example, in certain exemplary embodiments, theliner50 ofFIG. 2 may be one of theinner liner14 orouter liner12 of thecombustor10 ofFIG. 1.
• Accordingly, it will be appreciated thatliner50 defines at least in part acombustion chamber20, afirst side36, asecond side38 opposite thefirst side36, and afilm cooling hole44 extending between thefirst side36 andsecond side38. For the embodiment depicted, thefirst side36 is a hot side, and accordingly, thefirst side36 is exposed to (and at least partially defines) the combustion chamber20 (see alsoFIG. 1). Additionally, in such a manner it will be appreciated that thefilm cooling hole44 extends from thesecond side38 to thefirst side36, defining anoutlet52 on thefirst side36. Furthermore, during operation of the combustor, thecombustion chamber20 defines an airflow direction A over the dilution hole on thefirst side36 of theliner50, as well as a transverse direction T perpendicular to the airflow direction A. The transverse direction T is also parallel to asurface54 of theliner50 on thefirst side36, and may be locally aligned with a circumferential direction of the gas turbine engine including the combustor (e.g., circumferential direction C described above with respect toFIG. 1).
• More specifically, as with the embodiment depicted inFIG. 1, thefilm cooling hole44 is a firstfilm cooling hole44A of a plurality of film cooling holes44 defined by theliner50. Each of the plurality of film cooling holes44 are spaced a distance S from one another along the transverse direction T and a distance P from one another along the airflow direction A. Notably, however, in other exemplary embodiments, the plurality of film cooling holes44 may be arranged in any other suitable manner.
• Referring now also toFIG. 3, a plan view of the first side36 (i.e., the hot side) of theexemplary liner50 ofFIG. 2 is provided. As is depicted schematically, theliner50 further includes anairflow feature56 on thefirst side36 of theliner50 adjacent to theoutlet52 of thefilm cooling hole44 to increase a cooling of theliner50, and more specifically, adjacent to afirst outlet52A of the firstfilm cooling hole44A to increase a cooling of theliner50. As used herein, the term “adjacent to the outlet of the film cooling hole,” with reference to a positioning of an airflow feature, refers to such airflow feature being spaced (edge-to-edge) from the outlet of the respective film cooling hole a distance no more than twice the diameter of the film cooling hole.
• More specifically, still, as noted above, thecombustion chamber20 defines the airflow direction A over theoutlet52 of thefilm cooling hole44 on thefirst side36 of theliner50, and further defines the transverse direction T perpendicular to the airflow direction A. For the embodiment shown, theairflow feature56 is positioned at least partially upstream of theoutlet52A of the firstfilm cooling hole44A along the airflow direction A. Moreover, for the embodiment shown, theairflow feature56 is afirst airflow feature56A and theliner50 further includes asecond airflow feature56B also positioned at least partially upstream of theoutlet52A of the firstfilm cooling hole44A along the airflow direction A. Further, for the embodiment shown, thesecond airflow feature56B is spaced from thefirst airflow feature56A along the transverse direction T.
• Referring now also toFIG. 4, providing a cross-sectional view of theliner50 depicted inFIG. 3, along Line4-4 inFIG. 3, it will be appreciated that for the embodiment shown, thefirst airflow feature56A is a protrusion on thefirst side36 of theliner50 extending into thecombustion chamber20, and further that thesecond airflow feature56B is also a protrusion on thefirst side36 of theliner50 also extending into thecombustion chamber20. For the embodiment shown, it will be appreciated that thefirst airflow feature56A defines aheight58, awidth60, and a length62 (seeFIG. 3). Theheight58 is defined in a direction perpendicular to the airflow direction A and transverse direction T relative to the surroundingsurface54 of thefirst side36 of theliner50. Thewidth60 is defined along the transverse direction T. Thelength62 is defined along the airflow direction A. For the embodiment shown, it will further be appreciated that the firstfilm cooling hole44A defines a diameter64 (FIG. 3) at theoutlet52. Thewidth60 of theairflow feature56 is greater than or equal to about 0.1 times thediameter64 and up to about six (6) times thediameter64, theheight58 of theairflow feature56 is greater than or equal to about 0.1 times thediameter64 and up to about six (6) times thediameter64, and thelength62 of theairflow feature56 is also greater than or equal to about 0.1 times thediameter64 and up to about six (6) times thediameter64. For example, one or more of thewidth60,height58, and/orlength62 may be greater than or equal to about 0.25 times thediameter64, such as greater than about 0.5 times thediameter64, such as greater than or equal to thediameter64, such as less than or equal to about five (5) times thediameter64, such as less than or equal to about four (4) times thediameter64. Notably, thesecond airflow feature56B may also define aheight58, awidth60, and alength62.Such measurements58,60,62 of thesecond airflow feature56B are, for the embodiment shown, equal to the correspondingmeasurements58,60,62 of thefirst airflow feature56A. However, in other embodiments, themeasurements58,60,62 of thesecond airflow feature56B may have any other suitable value within one or more the ranges set forth above. Further, it will be appreciated that in certain exemplary embodiments, not all of the cooling holes44 may include the same configuration of airflow features56 positioned adjacent thereto, or may not include any airflow features56 positioned adjacent thereto. For example, in certain embodiments, some cooling holes44 may include airflow features56 having different heights, widths, lengths, orientations, etc. positioned adjacent thereto. Further, in certain exemplary embodiments, each of the airflow features56 positioned adjacent to a givencooling hole44 may have the same configuration (e.g., size and shape), or alternatively may have different configurations (e.g., size and shape).
• Further, it will be appreciated that for the embodiment depicted inFIGS. 3 and 4, the firstfilm cooling hole44A is one of a plurality of film cooling holes44, and that each of the plurality of film cooling holes44 includes afirst airflow feature56A and asecond airflow feature56B configured in substantially the same manner as the first and second airflow features56A,56B positioned adjacent to theoutlet52A of the firstfilm cooling hole44A, described above. For example, the measurements of the first and second airflow features56A,56B positioned adjacent to theoutlets52 of the other cooling holes44 depicted may be substantially the same as themeasurements58,60,62 of the first and second airflow features56A,56B positioned adjacent to theoutlet52A of the firstfilm cooling hole44A.
• Further, it should be appreciated that for the embodiment depicted, theliner50 includes the airflow features56 formed integrally with abase wall portion61 of theliner50. For example, theliner50 may be formed as a single component using, e.g., 3D printing/additive manufacturing processes to form theliner50. Accordingly, in certain embodiments, the airflow features56 andbase wall portion61 may be formed integrally as a single, continuous component. However, in other exemplary embodiments, theliner50 may be formed in any other suitable manner.
• As will also be appreciated from the view depicted inFIG. 4, for the embodiment depicted, the airflow features56 each define an aerodynamic profile. As used herein, the term “aerodynamic profile” refers generally to including no sharp or jagged edges exposed to an airflow thereover (e.g., only rounded edges having a radius approximately equal to or greater than the smallest dimension theairflow feature56, such as the smallest of its height, width, or length). Further, as is seen inFIG. 4, each of the airflow features56 defines a perimeter shape. For the embodiment depicted, the perimeter shape of eachairflow feature56 is substantially an ellipse, a circle, or an oval, and more specifically still, for the embodiment depicted, is substantially a circle.
• Notably, however, in other exemplary embodiments, one or more of the airflow features56 may define one or more sharp edges, and may have any other suitable perimeter shape. For example, inclusion of sharp edges may be desirable to generate turbulence and increase airflow mixing.
• Additionally, it will be appreciated that in other exemplary embodiments, the airflow feature(s)56 may have any other suitable configuration for modifying an airflow provided through anoutlet52 of afilm cooling hole44. For example, referring now toFIG. 5, providing a cross-sectional view of aliner50 in accordance with another exemplary embodiment of the present disclosure, it will be appreciated that in other example embodiments, one or both of thefirst airflow feature56A andsecond airflow feature56B may instead be configured as an indentation on thefirst side36 of theliner50. Specifically, for the embodiment ofFIG. 5, both of thefirst airflow feature56A and thesecond airflow feature56B are configured as indentations in thefirst side36 of theliner50. It will be appreciated that the first and second airflow features56A,56B ofFIG. 5 may define aheight58, awidth60, and a length62 (similar to thefeatures56A,56B described above with reference toFIG. 4). Thelength62 and thewidth60 may be defined in the same manner as thelength62 and thewidth60 of the first and second airflow features56A,56B described above with reference toFIG. 4. Further, theheights58 of the first and second airflow features56A,56B ofFIG. 5, configured as indentations, are similarly defined in a direction perpendicular to the airflow direction A and transverse direction T, relative to a surroundingsurface54 of thefirst side36 of theliner50.
• It will be appreciated, however, that in still other exemplary embodiments of the present disclosure, one of thefirst airflow feature56A andsecond airflow feature56B may be configured as a protrusion, and the other of thefirst airflow feature56A and thesecond airflow feature56B may be configured as an indentation. Moreover, it will be appreciated that in still other exemplary embodiments, theliner50 may not include both of thefirst airflow feature56A and thesecond airflow feature56B positioned adjacent to theoutlets52 of the film cooling holes44. For example, referring now toFIGS. 6 and 7, each providing a plan view of afirst side36 of aliner50 in accordance with other exemplary embodiments of the present disclosure, it will be appreciated that in certain exemplary embodiments, theliner50 may only include asingle airflow feature56 positioned adjacent to anoutlet52 of each of the respective film cooling holes44 in the location of thefirst airflow feature56A inFIG. 3 (seeFIG. 7) or in the location of thesecond airflow feature56B inFIG. 3 (seeFIG. 6). Accordingly, in each of these embodiments, it will be appreciated that eachairflow feature56 included is offset from theoutlet52 of the respectivefilm cooling hole44 along the transverse direction T. However, in other embodiments, eachairflow feature56 may instead be substantially aligned with theoutlet52 of the respectivefilm cooling hole44 along the transverse direction T.
• Aliner50 including airflow features56 configured in accordance with one or more of these embodiments may assist with the cooling of theliner50, as will be discussed in greater detail below.
• Moreover, referring now toFIG. 8, providing a plan view of afirst side36 of aliner50 in accordance with yet another example embodiment of the present disclosure, it will be appreciated that in still other exemplary embodiments, the airflow feature(s)56 may be positioned at any other suitable location adjacent to theoutlet52A of the firstfilm cooling hole44A (and further adjacent to theoutlets52 of each of the plurality of film cooling holes44). Specifically, for the embodiment ofFIG. 8, it will be appreciated that theliner50 includes anairflow feature56 on thefirst side36 of theliner50 adjacent to theoutlet52 of thefilm cooling hole44, and more specifically, adjacent to theoutlet52A of the firstfilm cooling hole44A, positioned at least partially downstream of theoutlet52A of the firstfilm cooling hole44A along the airflow direction A. More specifically, for the embodiment ofFIG. 8, theairflow feature56 is afirst airflow feature56A and theliner50 further includes asecond airflow feature56B also positioned at least partially downstream of theoutlet52A along the airflow direction A, with thesecond airflow feature56B spaced from thefirst airflow feature56A along the transverse direction T. In at least certain exemplary embodiments, thefirst airflow feature56A and thesecond airflow feature56B on theliner50 may be protrusions on thefirst side36 of theliner50 extending into the combustion chamber20 (similar to the embodiment depicted inFIG. 4). However, in other embodiments, thefirst airflow feature56A and thesecond airflow feature56B on theliner50 may each be indentations on thefirst side36 of the liner50 (similar to the embodiment depicted inFIG. 5). Alternatively, still, in other embodiments, one of thefirst airflow feature56A and thesecond airflow feature56B may be configured as a protrusion extending into thecombustion chamber20 and the other of thefirst airflow feature56A and thesecond airflow feature56B may be configured as an indentation on thefirst side36 of theliner50.
• Further, as with the embodiments described above, it will be appreciated that in still other exemplary embodiments theliner50 may not include both thefirst airflow feature56A and thesecond airflow feature56B adjacent to thefirst outlet52A of the firstfilm cooling hole44A. For example, referring now also toFIGS. 9 and 10, each providing a plan view of afirst side36 of theliner50 in accordance with additional exemplary embodiments of the present disclosure, it will be appreciated that in certain exemplary embodiments, theliner50 may only include asingle airflow feature56 positioned adjacent to theoutlet52A of the firstfilm cooling hole44A in the location of thefirst airflow feature56A inFIG. 8 (seeFIG. 10) or in the location of thesecond airflow feature56B inFIG. 8 (seeFIG. 9). Accordingly, in each of these embodiments, it will be appreciated that theairflow feature56 included is offset from theoutlet52A of the firstfilm cooling hole44A along the transverse direction T and located at least partially downstream of theoutlet52A of the firstfilm cooling hole44A. However, in other embodiments, theairflow feature56 may instead be substantially aligned with theoutlet52A of the firstfilm cooling hole44A along the transverse direction T.
• Notably, in each of the embodiments described above with reference toFIGS. 8 through 10, theliners50 include airflow feature(s)56 positioned adjacent to theoutlets52 of each of the plurality of film cooling holes44, with each of these airflow feature(s)56 configured in substantially the same manner as the airflow feature(s)56 described above as being positioned adjacent to theoutlet52A of the firstfilm cooling hole44A.
• Aliner50 including airflow features56 configured in accordance with one or more of these embodiments may assist with the cooling of theliner50, as will be discussed in greater detail below.
• Referring now toFIG. 11, a plan view of afirst side36 of aliner50 in accordance with yet another exemplary embodiment of the present disclosure is provided. The embodiment ofFIG. 11 may be configured in a similar manner to one or more theexemplary liners50 described above with reference to, e.g.,FIGS. 2 through 10. For example, theexemplary liner50 ofFIG. 11 defines afilm cooling hole44, and more specifically, a firstfilm cooling hole44A having anoutlet52A on afirst side36 thereof. In addition, theliner50 includes afirst airflow feature56A and asecond airflow feature56B, with the first and second airflow features56A,56B positioned adjacent to theoutlet52A of the firstfilm cooling hole44A and position at least partially upstream of theoutlet52A along an airflow direction A. Additionally, the first and second airflow features56A,56B are spaced from one another along the transverse direction T.
• Moreover, for the embodiment ofFIG. 11, theliner50 further includes athird airflow feature56C and afourth airflow feature56D. Thethird airflow feature56C and thefourth airflow feature56D are each positioned at least partially downstream of theoutlet52A of the firstfilm cooling hole44A along the airflow direction A and are similarly spaced from one another along the transverse direction T. Accordingly, for the embodiment depicted, theliner50 includes two airflow features56 position at least partially upstream of theoutlet52A of the firstfilm cooling hole44A and at least two airflow features56 positioned at least partially downstream of theoutlet52A of the firstfilm cooling hole44A.
• It will be appreciated that in at least certain embodiments, at least one of thefirst airflow feature56A, thesecond airflow feature56B, thethird airflow feature56C, and thefourth airflow feature56D is a protrusion extending into thecombustion chamber20, such as the exemplary airflow features56 depicted inFIG. 4. For example, in certain exemplary embodiments, each of thefirst airflow feature56A,second airflow feature56B,third airflow feature56C, andfourth airflow feature56D may be configured as protrusions extending into thecombustion chamber20. Additionally, or alternatively however, in other exemplary embodiments at least one of thefirst airflow feature56A, thesecond airflow feature56B, thethird airflow feature56C, and thefourth airflow feature56D may be an indentation on thefirst side36 of theliner50, such as the exemplary airflow features56 depicted inFIG. 5. For example, in certain exemplary embodiments, each of thefirst airflow feature56A,second airflow feature56B,third airflow feature56C, andfourth airflow feature56D may be configured as indentations on thefirst side36 of theliner50.
• Moreover, referring now toFIG. 12, providing a plan view of afirst side36 of aliner50 in accordance with yet another example embodiment of the present disclosure, it will be appreciated that in still other exemplary embodiments, the airflow feature(s)56 may be positioned at any other suitable location adjacent to theoutlet52A of the firstfilm cooling hole44A. Specifically, for the embodiment ofFIG. 12, it will be appreciated that the liner50 includes an airflow feature56 on the first side36 of the liner50 adjacent to the outlet52 of the film cooling hole44, and more specifically, adjacent to the outlet52A of the first film cooling hole44A, substantially aligned with the outlet52A of the first film cooling hole44A along the transverse direction T. More specifically, for the embodiment ofFIG. 12, the airflow feature56 is a first airflow feature56A and the liner50 further includes a second airflow feature56B also substantially aligned with the outlet52A along the transverse direction T, with the second airflow feature56B positioned on an opposite side of the outlet52A from the first airflow feature56A along the transverse direction T. It will be appreciated, that as used herein, the term “substantially aligned with,” along the transverse direction T, refers to a center point along the airflow direction A of the airflow feature56 (i.e., half of the length62) being aligned with a center point of the outlet52 of the film cooling hole44 to which it is positioned adjacent to along the transverse direction T, or spaced no more than 0.5 times the diameter64 of the outlet52 from alignment with the center point of the outlet52 along the transverse direction T.
• In at least certain exemplary embodiments, thefirst airflow feature56A and thesecond airflow feature56B on theliner50 may be protrusions on thefirst side36 of theliner50 extending into the combustion chamber20 (similar to the embodiment depicted inFIG. 4). However, in other embodiments, thefirst airflow feature56A and thesecond airflow feature56B on theliner50 may each be indentations on thefirst side36 of the liner50 (similar to the embodiment depicted inFIG. 5). Alternatively, still, in other embodiments, one of thefirst airflow feature56A and thesecond airflow feature56B may be configured as a protrusion extending into thecombustion chamber20 and the other of thefirst airflow feature56A and thesecond airflow feature56B may be configured as an indentation on thefirst side36 of theliner50.
• Further, as with the embodiments described above, it will be appreciated that in still other exemplary embodiments theliner50 may not include both thefirst airflow feature56A and thesecond airflow feature56B. For example, referring now also toFIGS. 13 and 14, each providing a plan view of afirst side36 of aliner50 in accordance with additional exemplary embodiments of the present disclosure, it will be appreciated that in certain exemplary embodiments, theliner50 may only include asingle airflow feature56 positioned adjacent to anoutlet52A of a firstfilm cooling hole44A in the location of thefirst airflow feature56A inFIG. 12 (seeFIG. 14) or in the location of thesecond airflow feature56B inFIG. 12 (seeFIG. 13). Accordingly, in each of these embodiments, it will be appreciated that theairflow feature56 included is substantially aligned with theoutlet52A of the firstfilm cooling hole44A along the transverse direction T. Such may assist with the cooling of theliner50, as we discussed in greater detail below.
• Notably, in each of the embodiments described above with reference toFIGS. 11 through 14, theliners50 include airflow feature(s)56 positioned adjacent to theoutlets52 of each of the plurality of film cooling holes44, with each of these airflow feature(s)56 configured in substantially the same manner as the airflow feature(s)56 described above as being positioned adjacent to theoutlet52A of the firstfilm cooling hole44A.
• Further, it will be appreciated that in still other embodiments of the present disclosure, the airflow feature(s)56 may have any other suitable shape. For example, referring now toFIGS. 15 and 16, plan views are provided offirst sides36 ofliners50 in accordance with still other exemplary embodiments the present disclosure, each including one or more airflow features56. Referring particularly toFIG. 15, theliner50 depicted defines afilm cooling hole44, more specifically, a firstfilm cooling hole44A, having anoutlet52A on thefirst side36 thereof. Additionally, theliner50 includes anairflow feature56 positioned adjacent to theoutlet52A of the firstfilm cooling hole44A on thefirst side36 of theliner50. For the embodiment shown, theairflow feature56 defines alength62 along an airflow direction A and awidth60 along a transverse direction T. However, unlike the embodiments described above, for the embodiment shown, thewidth60 of theairflow feature56 is greater than thelength62 of theairflow feature56 and up to about five (5) times thelength62 of theairflow feature56. For example, for the embodiment shown, thewidth60 of theairflow feature56 may be at least about 1.25 times thelength62 of theairflow feature56 and up to about three (3) times thelength62 of theairflow feature56. In such a manner, it will also be appreciated that for the embodiment shown, thewidth60 of theairflow feature56 is also greater than adiameter64 of thefilm cooling hole44 defined through theliner50.
• Notably, for the embodiment ofFIG. 15, theairflow feature56 is positioned at least partially upstream of theoutlet52A of the firstfilm cooling hole44A along the airflow direction A, and more specifically, positioned completely upstream of theoutlet52A of the firstfilm cooling hole44A along the airflow direction A. However, in other embodiments, theairflow feature56 may instead be positioned at any other suitable location. For example, referring particularly toFIG. 16, for the embodiment depicted, theairflow feature56 is instead positioned at least partially downstream of theoutlet52A of the firstfilm cooling hole44A along the airflow direction A, and more particularly, positioned completely downstream of theoutlet52A of the firstfilm cooling hole44A along the airflow direction A.
• Furthermore, it will be appreciated that the exemplary embodiments provided inFIGS. 15 and 16 are provided by way of example only, and that in other exemplary embodiments, theliner50 may include any suitable combination of airflow features56 positioned adjacent to anoutlet52 of afilm cooling hole44 defined by aliner50. For example, referring also toFIG. 17, providing a plan view of afirst side36 of theliner50 in accordance with yet another exemplary embodiment of the present disclosure, it will be appreciated that in at least certain exemplary embodiments, anairflow feature56 defining a relatively high aspect ratio (i.e., a relatively high ratio ofwidth60 tolength62; seeFIGS. 15 and 16) may be used in conjunction with substantially circular airflow features56, with each of these airflow features56 position at least partially upstream of afirst outlet52A of afilm cooling hole44A.
• Notably, in each of the embodiments described above with reference toFIGS. 15 and 16, theliners50 include airflow feature(s)56 positioned adjacent to theoutlets52 of each of the plurality of film cooling holes44, with each of these airflow feature(s)56 configured in substantially the same manner as the airflow feature(s)56 described above as being positioned adjacent to theoutlet52A of the firstfilm cooling hole44A.
• In still other exemplary embodiments the present disclosure, however, theliner50 may have still other suitable configurations. For example, referring now toFIGS. 18 and 19, aliner50 in accordance with another exemplary embodiment of the present disclosure is provided.FIG. 18 provides a plan view of afirst side36 of aliner50 in accordance with yet another example embodiment of the present disclosure, andFIG. 19 provides a cross-sectional view of theexemplary liner50 ofFIG. 18, along Line19-19 inFIG. 18.
• For the embodiment ofFIGS. 18 and 19, theliner50 generally defines afilm cooling hole44 and anairflow feature56 on thefirst side36 of theliner50 adjacent to anoutlet52 of thefilm cooling hole44. Theairflow feature56 is substantially aligned with theoutlet52 of thefilm cooling hole44 along the airflow direction A. Moreover, for the embodiment ofFIGS. 18 and 19, theairflow feature56 is afirst airflow feature56A and theliner50 further includes asecond airflow feature56B, athird airflow feature56C, and afourth airflow feature56D, each substantially aligned with the outlet5A along the airflow direction A. It will be appreciated, that as used herein, the term “substantially aligned with,” along the airflow direction A, refers to a center point along the transverse direction T of the airflow feature56 (i.e., half of the width60) being aligned with a center point of theoutlet52 of thefilm cooling hole44 to which it is positioned adjacent to along the along airflow direction A, or spaced no more than 0.5 times thediameter64 of theoutlet52 from alignment with the center point of theoutlet52 along the airflow direction A.
• For the embodiment depicted, thefirst airflow feature56A and thefourth airflow feature56D of theliner50 are configured as protrusions on thefirst side36 of theliner50 extending into the combustion chamber20 (similar to the embodiment depicted inFIG. 4), while thesecond airflow feature56B and thethird airflow feature56C of theliner50 are each configured as indentations on thefirst side36 of the liner50 (similar to the embodiment depicted inFIG. 5). Further, for the embodiment shown, the first and second airflow features56A,56B are each aligned with one another along the airflow direction A, and positioned adjacent to one another along the airflow direction A (i.e., for the embodiment shown, spaced along the airflow direction A in such a manner that a downstream end of thefirst airflow feature56A meets an upstream end of thesecond airflow feature56B). Similarly, the third and fourth airflow features56C,56D are similarly aligned with one another along the airflow direction A and positioned adjacent to one another along the airflow direction A (i.e., for the embodiment shown, spaced along the airflow direction A in such a manner that a downstream end of thethird airflow feature56C meets an upstream end of thefourth airflow feature56D). Notably, although for the embodiment ofFIGS. 18 and 19 the adjacent airflow features (i.e., airflow features56A and56B, as well as airflow features56D and56D) are paired off as an indentation and a protrusion, in other embodiments, adjacent airflow features56 may each be protrusions, or may each be indentations.
• Further, it should be appreciated that other configurations are contemplated as well. For example, in other exemplary embodiments, any other suitable combination of the configurations shown in one or more of the embodiments ofFIGS. 2 through 19 may be provided. For example, in other exemplary embodiments, theliner50 may include one or more airflow features56 positioned in a similar manner to one or more the above embodiments, having a size and/or shape of an airflow feature of one or more of the above embodiments, configured as a protrusion and/or indentation, etc.
• Inclusion of aliner50 having one or more of the exemplary airflow features56 positioned adjacent to theoutlets52 of each of the plurality of film cooling holes44 defined therein may assist with cooling theliner50 during operation of the combustor and gas turbine engine within which theliner50 is installed. For example, inclusion of one or more the above exemplary airflow features56 may create a transverse pressure gradient (i.e., a pressure gradient along the transverse direction T of the hot side of the liner50) that acts as a jet deflector of the cooling airflow through the film cooling holes44. Such may therefore act to reduce a strength of a counter-rotating vortex pair that typically forms when cooling airflow is provided through film cooling holes44 to a hot side of theliner50. For example, inclusion of one or more the exemplary airflow features56 described herein may create a vortex along one side of the counter-rotating vortex pair to reduce a strength of the gas impingement within thecombustion chamber20. Such may lead to a reduced impingement of hot combustion gases into the film (i.e., the relatively cool air film on the hot side of the liner) leading to improved film cooling effectiveness along thefirst side36 of theliner50.
• This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

Claims (20)

What is claimed is:

1. A gas turbine engine combustor comprising:

a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a film cooling hole extending from the second side to the first side, the film cooling hole defining an outlet on the first side of the liner, the liner comprising an airflow feature on the first side of the of the liner adjacent to the outlet of the film cooling hole to increase a cooling of the liner.

2. The gas turbine engine ofclaim 1, wherein the combustion chamber defines an airflow direction over the outlet of the film cooling hole on the first side of the liner, and wherein the airflow feature is positioned at least partially downstream of the outlet along the airflow direction.

3. The gas turbine engine ofclaim 2, wherein the airflow feature is a first airflow feature, wherein the liner further comprises a second airflow feature also positioned at least partially downstream of the outlet along the airflow direction, wherein the combustion chamber further defines a transverse direction perpendicular to the airflow direction, and wherein the second airflow feature is spaced from the first airflow feature along the transverse direction.

4. The gas turbine engine ofclaim 3, wherein the first airflow feature is a protrusion on the first side of the liner extending into the combustion chamber, and wherein the second airflow feature is an indentation on the first side of liner.

5. The gas turbine engine ofclaim 1, wherein the combustion chamber defines an airflow direction over the outlet of the film cooling hole on the first side of the liner, and wherein the airflow feature is positioned at least partially upstream of the outlet along the airflow direction.

6. The gas turbine engine ofclaim 5, wherein the airflow feature is a first airflow feature, wherein the liner further comprises a second airflow feature also positioned at least partially upstream of the outlet along the airflow direction, wherein the combustion chamber further defines a transverse direction perpendicular to the airflow direction, and wherein the second airflow feature is spaced from the first airflow feature along the transverse direction.

7. The gas turbine engine ofclaim 6, wherein the first airflow feature is a protrusion on the first side of the liner extending into the combustion chamber, and wherein the second airflow feature is an indentation on the first side of liner.

8. The gas turbine engine ofclaim 6, wherein the first airflow feature is a protrusion on the first side of the liner extending into the combustion chamber, and wherein the second airflow feature is also a protrusion on the first side of the liner extending into the combustion chamber.

9. The gas turbine engine ofclaim 6, wherein the liner further comprises a third airflow feature and a fourth airflow feature, wherein the third airflow feature and the fourth airflow feature are each positioned at least partially downstream of the outlet along the airflow direction and spaced from one another along the transverse direction.

10. The gas turbine engine ofclaim 9, wherein at least one of the first airflow feature, the second airflow feature, the third airflow feature, and the fourth airflow feature is a protrusion extending into the combustion chamber, and wherein at least one of the first airflow feature, the second airflow feature, the third airflow feature, and the fourth airflow feature is an indentation on the first side of liner.

11. The gas turbine engine ofclaim 1, wherein the combustion chamber defines an airflow direction over the outlet of the film cooling hole on the first side of the liner, wherein the airflow feature is a first airflow feature, wherein the liner further comprises a second airflow feature, wherein the first and second airflow features are aligned with one another and the outlet of the film cooling hole along the airflow direction, and wherein the first airflow feature is positioned adjacent to the second airflow feature along the airflow direction.

12. The gas turbine engine ofclaim 1, wherein the combustion chamber defines an airflow direction over the film cooling hole on the first side of the liner and a transverse direction perpendicular to the airflow direction, wherein the airflow feature defines a length along the airflow direction and a width along the transverse direction, and wherein the width of the airflow feature is greater than the length of the airflow feature and up to about five times the length of the airflow feature.

13. The gas turbine engine ofclaim 1, wherein the film cooling hole defines a diameter at the outlet, wherein the airflow feature defines a width and a height, wherein the width of the airflow feature is greater than or equal to about 0.1 times the diameter of the of the film cooling hole and up to about 6 times the diameter of the film cooling hole, and wherein the height of the airflow feature is greater than or equal to about 0.1 times the diameter of the film cooling hole and up to about 6 times the diameter of the film cooling hole.

14. The gas turbine engine ofclaim 1, wherein the film cooling hole is a first film cooling hole of a plurality of film cooling holes defined by the liner.

15. The gas turbine engine ofclaim 1, wherein the film cooling hole defines a substantially constant diameter along a length thereof.

16. A gas turbine engine comprising:

a combustion section comprising a combustor liner, the combustor liner defining at least in part a combustion chamber, a hot side exposed to the combustion chamber, a cold side opposite the hot side, and a plurality of film cooling holes extending from the cold side to the hot side, the plurality of film cooling holes each defining an outlet on the hot side of the liner, the liner comprising a plurality of airflow features on the hot side of the of the liner, each airflow feature of the plurality of airflow features positioned adjacent to the outlet of one of the plurality of film cooling holes to increase a cooling of the liner.

17. The gas turbine engine ofclaim 16, wherein the combustion chamber defines an airflow direction over the outlets of the plurality of film cooling holes on the hot side of the liner, and wherein the airflow features are each positioned at least partially downstream of the outlet of one of the plurality of film cooling holes along the airflow direction.

18. The gas turbine engine ofclaim 16, wherein the combustion chamber defines an airflow direction over the outlets of the plurality of film cooling holes on the hot side of the liner, and wherein the airflow features are each positioned at least partially upstream of the outlet of one of the plurality of film cooling holes along the airflow direction.

19. The gas turbine engine ofclaim 16, wherein the combustion chamber defines an airflow direction over the outlets of the plurality of film cooling holes on the hot side of the liner and a transverse direction perpendicular to the airflow direction, wherein each airflow feature defines a length along the airflow direction and a width along the transverse direction, and wherein the width of each airflow feature is greater than the length of the airflow feature and up to about five times the length of the airflow feature.

20. The gas turbine engine ofclaim 16, wherein a first film cooling hole of the plurality of film cooling holes defines a diameter at its outlet, wherein a first airflow feature of the plurality of airflow features defines a width and a height, wherein the width of the first airflow feature is greater than or equal to about 0.1 times the diameter of the of the first film cooling hole and up to about 6 times the diameter of the first film cooling hole, and wherein the height of the first airflow feature is greater than or equal to about 0.1 times the diameter of the first film cooling hole and up to about 6 times the diameter of the first film cooling hole.

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