US20180163968A1

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Info

Publication number: US20180163968A1
Application number: US15/378,291
Authority: US
Inventors: Donald Mark Bailey; David William Cihlar; Lucas John Stoia
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2016-12-14
Filing date: 2016-12-14
Publication date: 2018-06-14

Abstract

A combustor includes an inlet flow conditioner having a sleeve and a conditioner plate. The conditioner plate defines a plurality of apertures. The sleeve extends axially from the conditioner plate to a forward plate of a nozzle segment. The sleeve, the conditioner plate and the forward plate define an inlet flow plenum. The inlet flow plenum is in fluid communication with an inlet of a tube that defines a premix passage of the nozzle segment.

Description

FIELD OF THE TECHNOLOGY

The present invention generally involves a combustor for a gas turbine. More specifically, the invention relates to a system for mitigating non-uniform flow upstream from an inlet to a premix passage of a fuel nozzle.

BACKGROUND

During operation of a gas turbine engine, pressurized air from a compressor flows into a head end volume defined within the combustor. The pressurized air flows from the head end volume into an inlet to a corresponding premix passage of a respective fuel nozzle. Fuel is injected into the flow of pressurized air within the premix passage where it mixes with the pressurized air so as to provide a fuel and air mixture to a combustion zone or chamber defined downstream from the fuel nozzle. The flow of pressurized air is typically non-uniform as it approaches the inlet to the respective fuel nozzle which may be undesirable for efficient combustor operations.

BRIEF DESCRIPTION OF THE TECHNOLOGY

Aspects and advantages are set forth below in the following description, or may be obvious from the description, or may be learned through practice.

One embodiment of the present disclosure is a combustor. The combustor includes an inlet flow conditioner having a sleeve and a conditioner plate. The conditioner plate defines a plurality of apertures. The sleeve extends axially from the conditioner plate to a forward plate of a nozzle segment. The sleeve, the conditioner plate and the forward plate define an inlet flow plenum. The inlet flow plenum is in fluid communication with an inlet of a tube that defines a premix passage of the nozzle segment.

Another embodiment of the present disclosure is a combustor. The combustor includes an inlet flow conditioner including a sleeve and a conditioner plate. The conditioner plate defines a plurality of apertures. The sleeve extends axially from the conditioner plate to a forward plate of a fuel nozzle and forms an inlet flow plenum therein. The inlet flow plenum is in fluid communication with a plurality of premix passages which is defined by a plurality of tubes of the fuel nozzle.

Those of ordinary skill in the art will better appreciate the features and aspects of such embodiments, and others, upon review of the specification.

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of the of various embodiments, including the best mode thereof to one skilled in the art, is set forth more particularly in the remainder of the specification, including reference to the accompanying figures, in which:

FIG. 1 is a functional block diagram of an exemplary gas turbine that may incorporate various embodiments of the present disclosure;

FIG. 2 is a simplified cross-section side view of an exemplary combustor as may incorporate various embodiments of the present disclosure;

FIG. 3 is an upstream view of an exemplary fuel nozzle assembly according to at least one embodiment of the present disclosure;

FIG. 4 is a cross-sectioned perspective view of an exemplary nozzle segment according to at least one embodiment of the present disclosure;

FIG. 5 is a perspective view of an exemplary conditioner plate according to at least one embodiment of the present disclosure;

FIG. 6 is a cross-sectioned perspective view of an exemplary fuel nozzle according to at least one embodiment of the present disclosure; and

FIG. 7 is a perspective view of an exemplary conditioner plate according to at least one embodiment of the present disclosure.

DETAILED DESCRIPTION

Reference will now be made in detail to present embodiments of the disclosure, 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 disclosure.

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 “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 term “radially” refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component, the term “axially” refers to the relative direction that is substantially parallel and/or coaxially aligned to an axial centerline of a particular component, and the term “circumferentially” refers to the relative direction that extends around the axial centerline of a particular component.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.

Each example is provided by way of explanation, not limitation. In fact, it will be apparent to those skilled in the art that modifications and variations can be made without departing from the scope or spirit thereof. For instance, features illustrated or described as part of one embodiment may be used on another embodiment to yield a still further embodiment. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims and their equivalents. Although exemplary embodiments of the present disclosure will be described generally in the context of a combustor for a land based power generating gas turbine for purposes of illustration, one of ordinary skill in the art will readily appreciate that embodiments of the present disclosure may be applied to any style or type of combustor for a turbomachine and are not limited to combustors or combustion systems for land based power generating gas turbines unless specifically recited in the claims.

Referring now to the drawings,FIG. 1 illustrates a schematic diagram of anexemplary gas turbine10. Thegas turbine10 generally includes acompressor12, at least onecombustor14 disposed downstream of thecompressor12 and aturbine16 disposed downstream of thecombustor14. Additionally, thegas turbine10 may include one ormore shafts18 that couple thecompressor12 to theturbine16.

During operation,air20 flows into thecompressor12 where theair20 is progressively compressed, thus providing compressed or pressurizedair22 to thecombustor14. At least a portion of the compressedair22 is mixed with afuel24 within thecombustor14 and burned to producecombustion gases26. Thecombustion gases26 flow from thecombustor14 into theturbine16, wherein energy (kinetic and/or thermal) is transferred from thecombustion gases26 to rotor blades (not shown), thus causingshaft18 to rotate. The mechanical rotational energy may then be used for various purposes such as to power thecompressor12 and/or to generate electricity. Thecombustion gases26 may then be exhausted from thegas turbine10.

As shown inFIG. 2, thecombustor14 may be at least partially surrounded by anouter casing28 such as a compressor discharge casing. Theouter casing28 may at least partially define ahigh pressure plenum30 that at least partially surrounds various components of thecombustor14. Thehigh pressure plenum30 may be in fluid communication with the compressor12 (FIG. 1) so as to receive thecompressed air22 therefrom. Anendcover32 may be coupled to theouter casing28. One or more combustion liners orducts34 may at least partially define a combustion chamber orzone36 for combusting the fuel-air mixture and/or may at least partially define a hot gas path through thecombustor14 for directing thecombustion gases26 towards aninlet38 to theturbine16.

In particular embodiments, thecombustion liner34 is at last partially circumferentially surrounded by aflow sleeve40. Theflow sleeve40 may be formed as a single component or by multiple flow sleeve segments. Theflow sleeve40 is radially spaced from thecombustion liner34 so as to define a flow passage orannular flow passage42 therebetween. Theflow sleeve40 may define a plurality of inlets or holes44 which provide for fluid communication between theflow passage42 and thehigh pressure plenum30. In particular embodiments, theendcover32 and theouter casing28 at least partially define a head end volume orplenum46 of thecombustor14. Thehead end volume46 may be in fluid communication with thehigh pressure plenum30 via theflow passage42. In various embodiments, as shown inFIG. 2, thecombustor14 includes afuel nozzle assembly48.

FIG. 3 provides an upstream view of an exemplaryfuel nozzle assembly48 according to at least one embodiment of the present disclosure. In particular embodiments, as shown inFIG. 3, thefuel nozzle assembly48 includes a plurality ofnozzle segments100 annularly arranged about a fuel nozzle orcenter fuel nozzle200. AlthoughFIG. 3 illustrates fourindividual nozzle segments100, thecombustor14 may include two ormore nozzle segments100 and is not limited to fournozzles segments100 unless otherwise recited in the claims. For example, in an exemplary embodiment, thefuel nozzle assembly48 may include five nozzle segments annularly arranged around acenter fuel nozzle200. In other embodiments,fuel nozzle assembly48 may include just asingle fuel nozzle200. As shown inFIG. 2, each of thenozzle segments100 and/or thefuel nozzle200 may be coupled to theendcover32 via one ormore conduits50.

FIG. 4 provides a cross-sectioned perspective view of anexemplary nozzle segment100 according to at least one embodiment of the present disclosure. As shown inFIG. 4, eachnozzle segment100 of the plurality ofnozzle segments100 includes aforward plate102, anaft plate104 that is axially offset from theforward plate102 with respect to an axial centerline of thecombustor14 and anouter band106 that at least partially defines a radially outer perimeter of thenozzle segment100. Theouter band106 extends from theforward plate102 to theaft plate104. Afuel plenum108 may be at least partially defined between theforward plate102, theaft plate104 and theouter band106.

A plurality oftubes110 extends through theforward plate102, thefuel plenum108 and theaft plate104. Eachtube110 includes an inlet end or opening112 disposed at or upstream from theforward plate102 and an outlet end or opening114 disposed downstream and/or extending axially away from theaft plate104. In various embodiments one or more of thetubes110 includes one or more fuel ports orholes116 in fluid communication with thefuel plenum108. Eachtube110 defines a passage orpremix passage118 through therespective nozzle segment100. In operation, fuel may be supplied to thefuel plenum108 via a correspondingfluid conduit50. The fuel from thefuel plenum108 may be injected into arespective premix passage118 via fuel port(s)116 where it is mixed with thecompressed air22 from thehigh pressure plenum30. The fuel-air mixture is then injected from therespective tube110

outlet

114 into thecombustion chamber36 where it is burned to produce thecombustion gases26.

In various embodiments, as shown inFIG. 4, thenozzle segment100 includes aninlet flow conditioner120. In particular embodiments, as shown inFIG. 4, theinlet flow conditioner120 includes asleeve122 that is annularly shaped and that circumferentially surrounds a portion offluid conduit50. Thesleeve122 extends axially upstream from theforward plate102. Thesleeve122 extends circumferentially around therespective inlets112 to eachrespective tube110 of the plurality oftubes110. In particular embodiments, thesleeve122 defines a plurality of apertures or holes124 radially oriented and circumferentially spaced about thesleeve122. In particular embodiments, the plurality ofapertures124 may be uniformly spaced or distributed or may be non-uniformly spaced or distributed along thesleeve122. In particular embodiments, the plurality ofapertures124 may be uniformly sized or may be sized differently at various axial locations along thesleeve122. In particular embodiments, the plurality ofapertures124 may be uniformly shaped or may have different shapes defined at various axial locations along thesleeve122.

In particular embodiments, as shown inFIG. 4, theinlet flow conditioner120 includesconditioner plate126. In particular embodiments, thesleeve122 extends from theconditioner plate126 to theforward plate102 of thenozzle segment100. In particular embodiments, theconditioner plate126 extends radially outwardly from and at least partially circumferentially around thefluid conduit50. Theconditioner plate126, thesleeve122 and theforward plate102 at least partially define aninlet flow plenum128 therebetween. Therespective inlet112 of eachrespective tube110 is in fluid communication with theinlet flow plenum128.

FIG. 5 provides a perspective view of anexemplary conditioner plate126 according to at least one embodiment of the present disclosure. In particular embodiments, as shown inFIG. 5, theconditioner plate126 may be wedge or pie shaped. As shown inFIG. 5, theconditioner plate126 defines and/or includes a plurality ofapertures130. The plurality ofapertures130 is distributed across theconditioner plate126. The flow area of theapertures130 may be sized equally or may be sized differently with the flow area of someapertures130 being smaller or larger than the flow area ofother apertures130. For example, in one embodiment afirst aperture130 of the plurality ofapertures130 may have a first diameter or flow area D1 and asecond aperture130 of the plurality ofapertures130 may have a second diameter or flow area D2 that is less than the first diameter D1.

Although theapertures130 are illustrated inFIG. 5 as having a round shape, the particular shape of theapertures130 is not limited to round or circular unless otherwise recited in the claims. For example, one or more of theapertures130 may be oblong, square, rectangular, trapezoidal, triangular or have other shapes so as to have a desired effect on air flowing through theconditioner plate126 into theinlet flow plenum128.

FIG. 6 provides a cross-sectioned perspective view of anexemplary fuel nozzle200 according to at least one embodiment of the present disclosure. As shown inFIG. 6, eachfuel nozzle200 includes aforward plate202, anaft plate204 that is axially offset from theforward plate202 with respect to an axial centerline of thecombustor14 and anouter band206 that at least partially defines a radially outer perimeter of thefuel nozzle200. Theouter band206 extends from theforward plate202 to theaft plate204. Afuel plenum208 may be at least partially defined between theforward plate202, theaft plate204 and theouter band206.

A plurality oftubes210 extends through theforward plate202, thefuel plenum208 and theaft plate204. Eachtube210 includes an inlet end or opening212 disposed at or upstream from theforward plate202 and an outlet end or opening214 disposed downstream and/or extending axially away from theaft plate204. In various embodiments one or more of thetubes210 includes one or more fuel ports orholes216 in fluid communication with thefuel plenum208. Eachtube210 defines a passage orpremix passage218 through therespective fuel nozzle200.

In operation, fuel may be supplied to thefuel plenum208 via a correspondingfluid conduit50. The fuel from thefuel plenum208 may be injected into arespective premix passage218 via fuel port(s)216 where it is mixed with thecompressed air22 from thehigh pressure plenum30. The fuel-air mixture is then injected from therespective tube210

outlet

214 into thecombustion chamber36 where it is burned to produce thecombustion gases26.

In various embodiments, as shown inFIG. 6, thefuel nozzle200 includes aninlet flow conditioner220. In particular embodiments, as shown inFIG. 6, theinlet flow conditioner220 includes asleeve222 that is annularly shaped and that circumferentially surrounds a portion offluid conduit50. Thesleeve222 extends axially upstream from theforward plate202. Thesleeve222 extends circumferentially around the respective inlet212 to eachrespective tube210 of the plurality oftubes210. In particular embodiments, thesleeve222 defines a plurality of apertures or holes224 circumferentially spaced about thesleeve222. In particular embodiments, the plurality ofapertures224 may be uniformly spaced or distributed or may be non-uniformly spaced or distributed along thesleeve222. In particular embodiments, the plurality ofapertures224 may be uniformly sized or may be sized differently at various axial locations along thesleeve222. In particular embodiments, the plurality ofapertures224 may be uniformly shaped or may have different shapes defined at various axial locations along thesleeve222.

In particular embodiments, as shown inFIG. 6, theinlet flow conditioner220 includesconditioner plate226. In particular embodiments, thesleeve222 extends from theconditioner plate226 to theforward plate202 of thefuel nozzle200. In particular embodiments, theconditioner plate226 extends radially outwardly from and at least partially circumferentially around thefluid conduit50. Theconditioner plate226, thesleeve222 and theforward plate202 at least partially define aninlet flow plenum228 therebetween. The respective inlet212 of eachrespective tube210 is in fluid communication with theinlet flow plenum228.

FIG. 7 provides a perspective view of anexemplary conditioner plate226 according to at least one embodiment of the present disclosure. As shown inFIG. 7, theconditioner plate226 defines and/or includes a plurality ofapertures230. The plurality ofapertures230 is distributed across theconditioner plate226. The flow area of theapertures230 may be sized equally or may be sized differently with the flow area of someapertures230 being smaller or larger than the flow area ofother apertures230. For example, in one embodiment afirst aperture230 of the plurality ofapertures230 may have a first diameter or flow area D1 and asecond aperture230 of the plurality ofapertures230 may have a second diameter or flow area D2 that is less than the first diameter D1

Although theapertures230 are illustrated inFIG. 7 as having a round shape, the particular shape of theapertures230 is not limited to round unless otherwise recited in the claims. For example, one or more of theapertures230 may be oblong, square, rectangular, trapezoidal, triangular or have other shapes so as to have a desired effect on air flowing through theconditioner plate226 into theinlet flow plenum228.

During operation, as shown inFIGS. 2 through 7 collectively,compressed air22 from thehigh pressure plenum30 flows from the high pressure plenum towards thehead end volume46. A portion of thecompressed air22 may flow through

apertures

124,224 defined in the

corresponding sleeve

122,222 and into the corresponding

flow distribution plenum

128,228. A portion of thecompressed air22 then flows to thehead end volume46 where it reverses direction and flows through the corresponding

apertures

130,230 of the

respective conditioning plate

126,230.

The

apertures

124,224 reduce non-uniformity of thecompressed air22 as it enters the respective

inlet flow plenums

128,228 from thehead end volume46. Thecompressed air22 having a substantially uniform flow field, enters the inlet(s)112,212 of the premix passage(s)118,218 in a substantially uniform fashion where fuel from the

respective fuel plenums

108,208 is injected into the flow of thecompressed air22 via the

fuel ports

116,216. The fuel andcompressed air22 mix within the

respective premix passages

118,218 and the mixture is then injected into theprimary combustion chamber36 where it is burned to produce combustion gases. The reduction in non-uniformity of thecompressed air22 provided by the

respective conditioner plates

126,226 as it enters the respective

inlet flow plenums

128,228 from thehead end volume46 improves mixing of the fuel and air within the

premix passages

118,218, thereby reducing overall NOx emissions of thecombustor14.

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 language of the claims.

Claims

What is claimed is:

1. A combustor, comprising:

an inlet flow conditioner including a sleeve and a conditioner plate defining a plurality of apertures, wherein the sleeve extends axially from the conditioner plate to a forward plate of a nozzle segment, wherein the sleeve, the conditioner plate and the forward plate define an inlet flow plenum, and wherein the inlet flow plenum is in fluid communication with an inlet of a tube that defines a premix passage of the nozzle segment.

2. The combustor as inclaim 1, further comprising a head end volume at least partially defined between an endcover and the conditioner plate, wherein the inlet flow plenum is in fluid communication with the head end volume via the plurality of apertures.

3. The combustor as inclaim 1, wherein at least one aperture of the plurality of apertures is non-round.

4. The combustor as inclaim 1, where a first aperture of the plurality of apertures has a diameter that is less than a diameter of a second aperture of the plurality of apertures.

5. The combustor as inclaim 1, wherein the conditioner plate is wedge shaped.

6. The combustor as inclaim 1, wherein the sleeve defines a plurality of holes radially oriented and circumferentially spaced around the sleeve, wherein the plurality of holes provide for fluid communication into the inlet flow plenum.

7. The combustor as inclaim 1, further comprising a fluid conduit that extends axially through the conditioner plate, wherein the fluid conduit provides fuel to the premix passage.

8. The combustor as inclaim 1, wherein the nozzle segment further comprises an aft plate axially spaced from the forward plate, an outer band that extends between the forward plate and the aft plate, and a fuel plenum defined between the forward plate and the aft plate, wherein the tube extends through the forward plate, the fuel plenum and the aft plate.

9. The combustor as inclaim 7, wherein the tube is in fluid communication with the fuel plenum.

10. A combustor, comprising:

an inlet flow conditioner including a sleeve and a conditioner plate defining a plurality of apertures, wherein the sleeve extends axially from the conditioner plate to a forward plate of a fuel nozzle forming an inlet flow plenum therein, and wherein the inlet flow plenum is in fluid communication with a plurality of premix passages defined by a plurality of tubes of the fuel nozzle.

11. The combustor as inclaim 10, further comprising a head end volume at least partially defined between an endcover and the conditioner plate, wherein the inlet flow plenum is in fluid communication with the head end volume via the plurality of apertures.

12. The combustor as inclaim 10, wherein at least one aperture of the plurality of apertures is non-round.

13. The combustor as inclaim 10, where a first aperture of the plurality of apertures has a diameter that is less than a diameter of a second aperture of the plurality of apertures.

14. The combustor as inclaim 10, wherein the conditioner plate is circular shaped.

15. The combustor as inclaim 10, wherein the sleeve defines a plurality of holes radially oriented and circumferentially spaced around the sleeve, wherein the plurality of holes provide for fluid communication into the inlet flow plenum.

16. The combustor as inclaim 10, further comprising a fluid conduit that extends axially through the conditioner plate, wherein the fluid conduit provides fuel to the fuel nozzle and each premix passage of the plurality of premix passages.

17. The combustor as inclaim 10, wherein the fuel nozzle further comprises an aft plate axially spaced from the forward plate, an outer band that extends between the forward plate and the aft plate, and a fuel plenum defined between the forward plate and the aft plate, wherein the tube extends through the forward plate, the fuel plenum and the aft plate.

18. The combustor as inclaim 17, wherein each tube is in fluid communication with the fuel plenum.

19. The combustor as inclaim 10, further comparing a plurality of nozzle segments annularly arranged around the fuel nozzle, wherein each nozzle segment includes a sleeve and a conditioner plate defining a plurality of apertures, wherein the sleeve extends axially from the conditioner plate to a forward plate, wherein the sleeve, the conditioner plate and the forward plate define an inlet flow plenum, and wherein the inlet flow plenum is in fluid communication with a plurality of premix passages defined by a plurality of tubes of the nozzle segment.