US20130186058A1 - Geared turbomachine fan and compressor rotation - Google Patents
Geared turbomachine fan and compressor rotationDownload PDFInfo
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- US20130186058A1 US20130186058A1US13/356,940US201213356940AUS2013186058A1US 20130186058 A1US20130186058 A1US 20130186058A1US 201213356940 AUS201213356940 AUS 201213356940AUS 2013186058 A1US2013186058 A1US 2013186058A1
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- turbomachine
- bypass ratio
- rotor
- geared
- fan
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- 238000002485combustion reactionMethods0.000description4
- 239000000446fuelSubstances0.000description4
- 230000008901benefitEffects0.000description3
- 238000006073displacement reactionMethods0.000description2
- 230000003068static effectEffects0.000description2
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Classifications
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/166—Sliding contact bearing
- F01D25/168—Sliding contact bearing for axial load mainly
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/40—Transmission of power
- F05D2260/403—Transmission of power through the shape of the drive components
- F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
- F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- This disclosurerelates to a geared turbomachine having a compressor rotor and a fan rotor that rotate together.
- Turbomachinessuch as gas turbine engines, typically include a fan section, a turbine section, a compressor section, and a combustor section. Turbomachines may employ a geared architecture connecting the fan section and the turbine section.
- the compressor sectiontypically includes at least a high-pressure compressor and a low-pressure compressor.
- the compressorsinclude rotors that rotate separately from a rotor of fan.
- various recent engine architectureshave been proposed in which the fan rotates in a first direction and at a first speed as compared to a low pressure compressor which rotates in the opposite direction and at a higher speed. These recent engine architectures can also be improved.
- a high-bypass ratio geared turbomachinecomprises a compressor section of a high-bypass ratio geared turbomachine, the compressor section providing at least a low-pressure compressor and a high-pressure compressor, wherein a rotor of the low-pressure compressor rotates together with a rotor of a fan.
- the rotor of the low pressure compressor and the rotor of the fanmay rotate at the same speed and in the same direction.
- the high-bypass ratio geared turbomachinemay have a fan bypass ratio greater than about 8.
- the high-bypass ratio geared turbomachinemay have an overall compression ratio greater than about 40.
- the high-pressure compressormay have a pressure ratio greater than about 20.
- the fanmay include a shaft that is rotatably supported by a plurality of tapered bearings.
- the high-bypass ratio geared turbomachinemay include a turbine shaft that rotates a geared architecture to rotate the rotor of the low-pressure compressor and the rotor of the fan.
- At least one thrust bearingmay rotatably support the turbine shaft, and the at least one thrust bearing may be located axially between the geared architecture and a turbine secured to the turbine shaft.
- the at least one thrust bearingmay be a bi-directional tapered bearing.
- the shaftmay be a low-pressure turbine shaft.
- the geared architecturemay be a planetary geared architecture.
- a high-bypass ratio turbomachinecomprises a fan rotor that rotates together with an compressor rotor at a first speed in a turbomachine having a high-bypass ratio, wherein the fan rotor and the compressor rotor are driven by a shaft that rotates at a second speed different than the first speed.
- the shaftmay rotate a geared architecture to rotate the fan rotor and the compressor rotor.
- the compressor rotormay be axially forward of a fan frame extending radially across a fan bypass flow path.
- the fan rotor and the compressor rotormay rotate at the same speed.
- the high-bypass ratio geared turbomachinemay include a high-pressure turbine, a combustor section, and a low-pressure turbine arranged axially sequentially within the geared turbomachine.
- exclusively axial compressorsmay provide compression in the geared turbomachine.
- the compressormay be a low-pressure compressor.
- a method of operating a high-bypass ratio turbomachinecomprises rotating a geared architecture with a first shaft, rotating a second shaft with the geared architecture, and rotating a fan rotor and a compressor rotor with the second shaft.
- the turbomachinemay have a fan bypass ratio greater than 8.
- FIG. 1shows a highly schematic view of a portion of an example turbomachine.
- FIG. 2shows a schematic view of another example turbomachine.
- an example geared turbomachine 10includes a first shaft 11 that provides a rotating input to a geared architecture 12 .
- Rotating the geared architecture 12rotates a second shaft 13 .
- the example geared architecture 12has a gear ratio that causes the second shaft 13 to rotate at a slower speed than the first shaft 11 .
- a compressor rotor 14 and a fan rotor 15are coupled to the second shaft 13 .
- Rotating the second shaft 13rotates the rotors 14 and 15 at the same rotational speed and in the same direction.
- the compressor rotor 14forms a portion of an axial compressor.
- FIG. 2schematically illustrates another example turbomachine, which is a gas turbine engine 20 in this example.
- the gas turbine engine 20is a two-spool turbofan gas turbine engine that generally includes a fan section 22 , a compressor section 24 , a combustion section 26 , and a turbine section 28 .
- Other examplesmay include an augmentor section (not shown) among other systems or features.
- the fan section 22drives air along a bypass flowpath while the compressor section 24 drives air along a core flowpath.
- Compressed air from the compressor section 24communicates through the combustion section 26 .
- the products of combustionexpand through the turbine section 28 .
- the example engine 20generally includes a low-speed spool 30 and a high-speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 .
- turbofan gas turbine enginedepicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans. That is, the teachings may be applied to other types of turbomachines and turbine engines including three-spool architectures.
- the low-speed spool 30 and the high-speed spool 32are rotatably supported by several bearing systems 38 a - 38 d. It should be understood that various bearing systems 38 a - 38 d at various locations may alternatively, or additionally, be provided.
- the low-speed spool 30generally includes an inner shaft 40 that interconnects a geared architecture 48 and a low-pressure turbine rotor 46 .
- the inner shaft 40is a turbine shaft in this example as the inner shaft 40 is connected directly to the low-pressure turbine rotor 46 .
- Rotating the geared architecture 48rotatably drives a fan rotor 42 and a low-pressure compressor rotor 44 at a lower speed than the low-speed spool 30 .
- the high-speed spool 32includes an outer shaft 50 that interconnects a high-pressure compressor rotor 52 and high-pressure turbine rotor 54 .
- the low-pressure compressor rotor 44 and the high-pressure compressor rotor 52are both rotors of axial compressors, and there are no other types of compressors within the compressor section 24 of the engine 20 .
- the combustion section 26includes a circumferentially distributed array of combustors 56 generally arranged axially between the high-pressure compressor rotor 52 and the high-pressure turbine rotor 54 .
- a mid-turbine frame 58 of the engine static structure 36is generally arranged axially between the high-pressure turbine rotor 54 and the low-pressure turbine rotor 46 .
- the mid-turbine frame 58supports the bearing systems 38 c and 38 d in the turbine section 28 .
- the mid-turbine frame 58includes airfoils 60 within the path of the core airflow.
- the inner shaft 40 and the outer shaft 50are concentric and rotate via the bearing systems 38 b - 38 d about the engine central longitudinal axis A, which is collinear with the longitudinal axes of the inner shaft 40 and the outer shaft 50 .
- the core airflowis compressed by the compressor section 24 , mixed and burned with fuel in the combustors 56 , then expanded within the turbine section 28 .
- the high-pressure turbine rotor 54 and the low-pressure turbine rotor 46rotatably drive the respective high-speed spool 32 and low-speed spool 30 in response to the expansion.
- the engine 20is a high-bypass geared aircraft engine.
- the engine 20has a fan bypass ratio that is greater than about six (6:1).
- the engine 20has a fan bypass ratio that is greater than about eight (8:1).
- the overall compression ratio of such the example engine 20is greater than 40 (40:1) in some examples, and the pressure ratio of the high-pressure compressor is greater than 20 (20:1).
- the geared architecture 48 of the example engine 20includes an epicyclic gear train, such as a planetary geared architecture or other geared architecture.
- the example epicyclic gear trainhas a gear reduction ratio of greater than about 2.3 (2.3:1).
- the low-pressure turbine pressure ratiois pressure measured prior to inlet of low-pressure turbine as related to the pressure at the outlet of the low-pressure turbine (and prior to an exhausting from the engine 20 ).
- the bypass ratio of the engine 20is greater than about ten (10:1)
- the fan diameteris significantly larger than that of the low pressure compressor
- the low-pressure turbinehas a pressure ratio that is greater than about 5 (5:1).
- the geared architecture 48 of this embodimentis an epicyclic gear train with a gear reduction ratio of greater than about 2.5 (2.5:1). Examples of the geared architecture 48 include star architectures and planetary architectures. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present disclosure is applicable to other gas turbine engines including direct drive turbofans.
- a significant amount of thrustis provided by the bypass flow B due to the high bypass ratio.
- the fan section 22 of the engine 20is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet. This flight condition, with the engine 20 at its best fuel consumption, is also known as bucket cruise Thrust Specific Fuel Consumption (TSFC).
- TSFCThrust Specific Fuel Consumption
- Fan Pressure Ratiois the pressure ratio across a blade of the fan section 22 (without the use of a Fan Exit Guide Vane system).
- the low Fan Pressure Ratio according to one non-limiting embodiment of the example engine 20is less than 1.45 (1.45:1).
- Low Corrected Fan Tip Speedis the actual fan tip speed divided by an industry standard temperature correction of “T”/518.7 0.5 .
- Trepresents the ambient temperature in degrees Rankine.
- the Low Corrected Fan Tip Speed according to one non-limiting embodiment of the example engine 20is less than about 1150 fps (351 m/s).
- the fan rotor 42 and the low-pressure compressor rotor 44are directly connected to a shaft 62 .
- One axial end of the shaft 62is directly connected to a carrier gear 64 of the geared architecture 48 .
- the fan rotor 42 and the low-pressure compressor rotor 44rotate at the same speed and in the same direction with the shaft 62 when the shaft 62 is driven by the carrier gear 64 of the geared architecture 48 .
- the shaft 62is rotated together with the carrier gear 64 when the geared architecture 48 is rotatably driven by the inner shaft 40 of the low-speed spool 30 .
- the shaft 62is considered a fan shaft in this example, because the fan rotor 42 is connected to the shaft 62 .
- Rotating the fan rotor 42 and the low-pressure compressor rotor 44 with the shaft 62facilitates positioning the low-pressure compressor of the compressor section 24 relatively axially close to the fan section 22 .
- the low-pressure compressor rotor 44(and thus the low-pressure compressor) is axially forward of a fan frame 68 in this example.
- the fan frame 68extends radially across a fan bypass passage of the engine 20 .
- the fan frame 68supports an outer duct 70 of the engine 20 relative to an engine core.
- Bearings 38 arotatably support the shaft 62 .
- the bearings 38 aare tapered in this example. Tapered bearings mounted as shown in FIG. 2 will react to the fan 42 thrust loads as well as any radial or moment loads applied to shaft 62 which come from fan 42 .
- bearings 38 acan be a ball and roller bearing combination. This combination will also react any thrust, radial or moment loads from the fan 42 to the shaft 62 .
- One skilled in the art and having the benefit of this disclosuremay arrive at other bearing configurations that support reaction loads applied to shaft 62
- bearings 38 brotatably support the low-speed spool 30 near the geared architecture 48 .
- the bearings 38 bare thrust bearings in this example.
- the bearings 38 bare bi-directional tapered thrust bearings.
- the bearings 38 bare ball thrust bearings.
- example bearings 38 bare located axially between the geared architecture 48 and the low-pressure turbine rotor 46 , and are positioned axially closer to the geared architecture 48 than the low-pressure turbine rotor 46 .
- Positioning the bearings 38 b in this areahas some performance advantages in the unlikely event that the inner shaft 40 fractures. After such a fracture of the inner shaft 40 , axially displacing the low-pressure turbine rotor 46 relative to other portions of the engine 20 is often desired. The axial displacement after a fracture will cause the low-pressure turbine rotor 46 to desirably clash.
- Fractures of the inner shaft 40 that are axially forward of the bearings 38 bmay not result in clash because the bearings 38 b (which are thrust bearings) hold the axial position of the fractured portion.
- Positioning the bearings 38 b axially near the geared architecture 48increases the axial locations aft the bearings 38 b, and thus the potential fracture locations of the inner shaft 40 that will result in clash.
- the bearing 38 c and 38 din this example, would permit axial displacement after a fracture.
- the torsional strength of the inner shaft 40is less than the torsional strength of the other drive shaft within the engine 20 (including the geared architecture 48 ).
- the inner shaft 40will fail before other areas of the engine 20 .
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Abstract
Description
- This disclosure relates to a geared turbomachine having a compressor rotor and a fan rotor that rotate together.
- Turbomachines, such as gas turbine engines, typically include a fan section, a turbine section, a compressor section, and a combustor section. Turbomachines may employ a geared architecture connecting the fan section and the turbine section. The compressor section typically includes at least a high-pressure compressor and a low-pressure compressor. The compressors include rotors that rotate separately from a rotor of fan. To maximize performance of such turbomachines, various recent engine architectures have been proposed in which the fan rotates in a first direction and at a first speed as compared to a low pressure compressor which rotates in the opposite direction and at a higher speed. These recent engine architectures can also be improved.
- A high-bypass ratio geared turbomachine according to an exemplary aspect of the present disclosure comprises a compressor section of a high-bypass ratio geared turbomachine, the compressor section providing at least a low-pressure compressor and a high-pressure compressor, wherein a rotor of the low-pressure compressor rotates together with a rotor of a fan.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the rotor of the low pressure compressor and the rotor of the fan may rotate at the same speed and in the same direction.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the high-bypass ratio geared turbomachine may have a fan bypass ratio greater than about 8.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the high-bypass ratio geared turbomachine may have an overall compression ratio greater than about 40.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the high-pressure compressor may have a pressure ratio greater than about 20.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the fan may include a shaft that is rotatably supported by a plurality of tapered bearings.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the high-bypass ratio geared turbomachine may include a turbine shaft that rotates a geared architecture to rotate the rotor of the low-pressure compressor and the rotor of the fan.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, at least one thrust bearing may rotatably support the turbine shaft, and the at least one thrust bearing may be located axially between the geared architecture and a turbine secured to the turbine shaft.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the at least one thrust bearing may be a bi-directional tapered bearing.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the shaft may be a low-pressure turbine shaft.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the geared architecture may be a planetary geared architecture.
- A high-bypass ratio turbomachine according to another exemplary aspect of the present disclosure comprises a fan rotor that rotates together with an compressor rotor at a first speed in a turbomachine having a high-bypass ratio, wherein the fan rotor and the compressor rotor are driven by a shaft that rotates at a second speed different than the first speed.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the shaft may rotate a geared architecture to rotate the fan rotor and the compressor rotor.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the compressor rotor may be axially forward of a fan frame extending radially across a fan bypass flow path.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the fan rotor and the compressor rotor may rotate at the same speed.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the high-bypass ratio geared turbomachine may include a high-pressure turbine, a combustor section, and a low-pressure turbine arranged axially sequentially within the geared turbomachine.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, exclusively axial compressors may provide compression in the geared turbomachine.
- In a further non-limiting embodiment of any of the foregoing high-bypass ratio geared turbomachine embodiments, the compressor may be a low-pressure compressor.
- A method of operating a high-bypass ratio turbomachine according to an exemplary aspect of the present disclosure comprises rotating a geared architecture with a first shaft, rotating a second shaft with the geared architecture, and rotating a fan rotor and a compressor rotor with the second shaft.
- In a further non-limiting embodiment of any of the foregoing methods of operating a high-bypass ratio geared turbomachine, the turbomachine may have a fan bypass ratio greater than 8.
- The various features and advantages of the disclosed examples will become apparent to those skilled in the art from the detailed description. The figures that accompany the detailed description can be briefly described as follows:
FIG. 1 shows a highly schematic view of a portion of an example turbomachine.FIG. 2 shows a schematic view of another example turbomachine.- Referring to
FIG. 1 , an example gearedturbomachine 10 includes afirst shaft 11 that provides a rotating input to a gearedarchitecture 12. Rotating the gearedarchitecture 12 rotates a second shaft13. The example gearedarchitecture 12 has a gear ratio that causes the second shaft13 to rotate at a slower speed than thefirst shaft 11. - A
compressor rotor 14 and afan rotor 15 are coupled to the second shaft13. Rotating the second shaft13 rotates therotors compressor rotor 14 forms a portion of an axial compressor. FIG. 2 schematically illustrates another example turbomachine, which is agas turbine engine 20 in this example. Thegas turbine engine 20 is a two-spool turbofan gas turbine engine that generally includes afan section 22, acompressor section 24, acombustion section 26, and aturbine section 28. Other examples may include an augmentor section (not shown) among other systems or features.- In the
example engine 20, thefan section 22 drives air along a bypass flowpath while thecompressor section 24 drives air along a core flowpath. Compressed air from thecompressor section 24 communicates through thecombustion section 26. The products of combustion expand through theturbine section 28. - The
example engine 20 generally includes a low-speed spool 30 and a high-speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure36. - Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans. That is, the teachings may be applied to other types of turbomachines and turbine engines including three-spool architectures.
- The low-
speed spool 30 and the high-speed spool 32 are rotatably supported by several bearing systems38a-38d.It should be understood that various bearing systems38a-38dat various locations may alternatively, or additionally, be provided. - The low-
speed spool 30 generally includes aninner shaft 40 that interconnects a gearedarchitecture 48 and a low-pressure turbine rotor 46. Theinner shaft 40 is a turbine shaft in this example as theinner shaft 40 is connected directly to the low-pressure turbine rotor 46. Rotating the gearedarchitecture 48 rotatably drives afan rotor 42 and a low-pressure compressor rotor 44 at a lower speed than the low-speed spool 30. - The high-
speed spool 32 includes anouter shaft 50 that interconnects a high-pressure compressor rotor 52 and high-pressure turbine rotor 54. - In this example, the low-
pressure compressor rotor 44 and the high-pressure compressor rotor 52 are both rotors of axial compressors, and there are no other types of compressors within thecompressor section 24 of theengine 20. - The
combustion section 26 includes a circumferentially distributed array ofcombustors 56 generally arranged axially between the high-pressure compressor rotor 52 and the high-pressure turbine rotor 54. - A mid-turbine frame58 of the engine static structure36 is generally arranged axially between the high-
pressure turbine rotor 54 and the low-pressure turbine rotor 46. The mid-turbine frame58 supports thebearing systems turbine section 28. The mid-turbine frame58 includesairfoils 60 within the path of the core airflow. - The
inner shaft 40 and theouter shaft 50 are concentric and rotate via thebearing systems 38b-38dabout the engine central longitudinal axis A, which is collinear with the longitudinal axes of theinner shaft 40 and theouter shaft 50. - In the
example engine 20, the core airflow is compressed by thecompressor section 24, mixed and burned with fuel in thecombustors 56, then expanded within theturbine section 28. The high-pressure turbine rotor 54 and the low-pressure turbine rotor 46 rotatably drive the respective high-speed spool 32 and low-speed spool 30 in response to the expansion. - In some non-limiting examples, the
engine 20 is a high-bypass geared aircraft engine. In a further example, theengine 20 has a fan bypass ratio that is greater than about six (6:1). In a still further example, theengine 20 has a fan bypass ratio that is greater than about eight (8:1). The overall compression ratio of such theexample engine 20 is greater than 40 (40:1) in some examples, and the pressure ratio of the high-pressure compressor is greater than 20 (20:1). - The geared
architecture 48 of theexample engine 20 includes an epicyclic gear train, such as a planetary geared architecture or other geared architecture. The example epicyclic gear train has a gear reduction ratio of greater than about 2.3 (2.3:1). - The low-pressure turbine pressure ratio is pressure measured prior to inlet of low-pressure turbine as related to the pressure at the outlet of the low-pressure turbine (and prior to an exhausting from the engine20). In one non-limiting embodiment, the bypass ratio of the
engine 20 is greater than about ten (10:1), the fan diameter is significantly larger than that of the low pressure compressor, and the low-pressure turbine has a pressure ratio that is greater than about 5 (5:1). The gearedarchitecture 48 of this embodiment is an epicyclic gear train with a gear reduction ratio of greater than about 2.5 (2.5:1). Examples of the gearedarchitecture 48 include star architectures and planetary architectures. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present disclosure is applicable to other gas turbine engines including direct drive turbofans. - In some embodiments of the
example engine 20, a significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. Thefan section 22 of theengine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet. This flight condition, with theengine 20 at its best fuel consumption, is also known as bucket cruise Thrust Specific Fuel Consumption (TSFC). TSFC is an industry standard parameter of fuel consumption per unit of thrust. - Fan Pressure Ratio is the pressure ratio across a blade of the fan section22 (without the use of a Fan Exit Guide Vane system). The low Fan Pressure Ratio according to one non-limiting embodiment of the
example engine 20 is less than 1.45 (1.45:1). - Low Corrected Fan Tip Speed is the actual fan tip speed divided by an industry standard temperature correction of “T”/518.70.5. T represents the ambient temperature in degrees Rankine. The Low Corrected Fan Tip Speed according to one non-limiting embodiment of the
example engine 20 is less than about 1150 fps (351 m/s). - In the
example engine 20, thefan rotor 42 and the low-pressure compressor rotor 44 are directly connected to ashaft 62. One axial end of theshaft 62 is directly connected to acarrier gear 64 of the gearedarchitecture 48. Thefan rotor 42 and the low-pressure compressor rotor 44 rotate at the same speed and in the same direction with theshaft 62 when theshaft 62 is driven by thecarrier gear 64 of the gearedarchitecture 48. Theshaft 62 is rotated together with thecarrier gear 64 when the gearedarchitecture 48 is rotatably driven by theinner shaft 40 of the low-speed spool 30. Theshaft 62 is considered a fan shaft in this example, because thefan rotor 42 is connected to theshaft 62. - Rotating the
fan rotor 42 and the low-pressure compressor rotor 44 with theshaft 62 facilitates positioning the low-pressure compressor of thecompressor section 24 relatively axially close to thefan section 22. The low-pressure compressor rotor44 (and thus the low-pressure compressor) is axially forward of afan frame 68 in this example. Thefan frame 68 extends radially across a fan bypass passage of theengine 20. Thefan frame 68 supports anouter duct 70 of theengine 20 relative to an engine core. Bearings 38arotatably support theshaft 62. Thebearings 38aare tapered in this example. Tapered bearings mounted as shown inFIG. 2 will react to thefan 42 thrust loads as well as any radial or moment loads applied toshaft 62 which come fromfan 42. In another example,bearings 38acan be a ball and roller bearing combination. This combination will also react any thrust, radial or moment loads from thefan 42 to theshaft 62. One skilled in the art and having the benefit of this disclosure may arrive at other bearing configurations that support reaction loads applied toshaft 62Other bearings 38brotatably support the low-speed spool 30 near the gearedarchitecture 48. Thebearings 38bare thrust bearings in this example. In one specific example, thebearings 38bare bi-directional tapered thrust bearings. In another specific example, thebearings 38bare ball thrust bearings.- Notably, the
example bearings 38bare located axially between the gearedarchitecture 48 and the low-pressure turbine rotor 46, and are positioned axially closer to the gearedarchitecture 48 than the low-pressure turbine rotor 46. - Positioning the
bearings 38bin this area has some performance advantages in the unlikely event that theinner shaft 40 fractures. After such a fracture of theinner shaft 40, axially displacing the low-pressure turbine rotor 46 relative to other portions of theengine 20 is often desired. The axial displacement after a fracture will cause the low-pressure turbine rotor 46 to desirably clash. - Fractures of the
inner shaft 40 that are axially forward of thebearings 38bmay not result in clash because thebearings 38b(which are thrust bearings) hold the axial position of the fractured portion. Positioning thebearings 38baxially near the gearedarchitecture 48 increases the axial locations aft thebearings 38b,and thus the potential fracture locations of theinner shaft 40 that will result in clash. The bearing38cand38d,in this example, would permit axial displacement after a fracture. - In some examples, the torsional strength of the
inner shaft 40 is less than the torsional strength of the other drive shaft within the engine20 (including the geared architecture48). Thus, in the event of, for example, an overload of thefan rotor 42, theinner shaft 40 will fail before other areas of theengine 20. - The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from the essence of this disclosure. Thus, the scope of legal protection given to this disclosure can only be determined by studying the following claims.
Claims (20)
1. A high-bypass ratio geared turbomachine, comprising:
a compressor section of a high-bypass ratio geared turbomachine, the compressor section providing at least a low-pressure compressor and a high-pressure compressor, wherein a rotor of the low-pressure compressor rotates together with a rotor of a fan.
2. The high-bypass ratio geared turbomachine ofclaim 1 , wherein the rotor of the low pressure compressor and the rotor of the fan rotate at the same speed and in the same direction.
3. The high-bypass ratio geared turbomachine ofclaim 1 , wherein the high-bypass ratio geared turbomachine has a fan bypass ratio greater than about 8.
4. The high-bypass ratio geared turbomachine ofclaim 1 , wherein the high-bypass ratio geared turbomachine has an overall compression ratio greater than about 40.
5. The high-bypass ratio geared turbomachine ofclaim 1 , wherein the high-pressure compressor has a pressure ratio greater than about 20.
6. The high-bypass ratio geared turbomachine ofclaim 1 , wherein the fan includes a shaft that is rotatably supported by a plurality of tapered bearings.
7. The high-bypass ratio geared turbomachine ofclaim 1 , including a turbine shaft that rotates a geared architecture to rotate the rotor of the low-pressure compressor and the rotor of the fan.
8. The high-bypass ratio geared turbomachine ofclaim 7 , wherein at least one thrust bearing rotatably supports the turbine shaft, and the at least one thrust bearing is located axially between the geared architecture and a turbine secured to the turbine shaft.
9. The high-bypass ratio geared turbomachine ofclaim 8 , wherein the at least one thrust bearing is a bi-directional tapered bearing.
10. The high-bypass ratio geared turbomachine ofclaim 7 , wherein the shaft is a low-pressure turbine shaft.
11. The high-bypass ratio geared turbomachine ofclaim 7 , wherein the geared architecture is a planetary geared architecture.
12. A high-bypass ratio turbomachine, comprising:
a fan rotor that rotates together with an compressor rotor at a first speed in a turbomachine having a high-bypass ratio, wherein the fan rotor and the compressor rotor are driven by a shaft that rotates at a second speed different than the first speed.
13. The high-bypass ratio turbomachine ofclaim 12 , wherein the shaft rotates a geared architecture to rotate the fan rotor and the compressor rotor.
14. The high-bypass ratio turbomachine ofclaim 12 , wherein the compressor rotor is axially forward of a fan frame extending radially across a fan bypass flow path.
15. The high-bypass ratio turbomachine ofclaim 12 , wherein the fan rotor and the compressor rotor rotate at the same speed.
16. The high-bypass ratio turbomachine ofclaim 12 , including a high-pressure turbine, a combustor section, and a low-pressure turbine arranged axially sequentially within the geared turbomachine.
17. The high-bypass ratio turbomachine ofclaim 12 , wherein exclusively axial compressors provide compression in the geared turbomachine.
18. The high-bypass ratio turbomachine ofclaim 12 , wherein the compressor is a low-pressure compressor.
19. A method of operating a high-bypass ratio turbomachine, comprising:
rotating a geared architecture with a first shaft;
rotating a second shaft with the geared architecture; and
rotating a fan rotor and a compressor rotor with the second shaft.
20. The method ofclaim 19 , wherein the turbomachine has a fan bypass ratio greater than 8.
Priority Applications (8)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/356,940US20130186058A1 (en) | 2012-01-24 | 2012-01-24 | Geared turbomachine fan and compressor rotation |
| PCT/US2013/021681WO2013154636A1 (en) | 2012-01-24 | 2013-01-16 | Geared turbomachine fan and compressor rotation |
| EP16171498.5AEP3085927B1 (en) | 2012-01-24 | 2013-01-16 | Rotation of a fan and a compressor of a geared turbomachine |
| EP20160895.7AEP3690215B1 (en) | 2012-01-24 | 2013-01-16 | Geared turbomachine fan and compressor rotation |
| EP13774928.9AEP2807358B1 (en) | 2012-01-24 | 2013-01-16 | Geared turbomachine fan and compressor rotation |
| US15/411,459US10584660B2 (en) | 2012-01-24 | 2017-01-20 | Geared turbomachine fan and compressor rotation |
| US16/812,636US11566587B2 (en) | 2012-01-24 | 2020-03-09 | Geared turbomachine fan and compressor rotation |
| US18/161,340US12234791B2 (en) | 2012-01-24 | 2023-01-30 | Geared turbomachine fan and compressor rotation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/356,940US20130186058A1 (en) | 2012-01-24 | 2012-01-24 | Geared turbomachine fan and compressor rotation |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US15/411,459ContinuationUS10584660B2 (en) | 2012-01-24 | 2017-01-20 | Geared turbomachine fan and compressor rotation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US20130186058A1true US20130186058A1 (en) | 2013-07-25 |
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ID=48796076
Family Applications (4)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US13/356,940AbandonedUS20130186058A1 (en) | 2012-01-24 | 2012-01-24 | Geared turbomachine fan and compressor rotation |
| US15/411,459Active2032-09-10US10584660B2 (en) | 2012-01-24 | 2017-01-20 | Geared turbomachine fan and compressor rotation |
| US16/812,636Active2033-06-14US11566587B2 (en) | 2012-01-24 | 2020-03-09 | Geared turbomachine fan and compressor rotation |
| US18/161,340ActiveUS12234791B2 (en) | 2012-01-24 | 2023-01-30 | Geared turbomachine fan and compressor rotation |
Family Applications After (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US15/411,459Active2032-09-10US10584660B2 (en) | 2012-01-24 | 2017-01-20 | Geared turbomachine fan and compressor rotation |
| US16/812,636Active2033-06-14US11566587B2 (en) | 2012-01-24 | 2020-03-09 | Geared turbomachine fan and compressor rotation |
| US18/161,340ActiveUS12234791B2 (en) | 2012-01-24 | 2023-01-30 | Geared turbomachine fan and compressor rotation |
Country Status (3)
| Country | Link |
|---|---|
| US (4) | US20130186058A1 (en) |
| EP (3) | EP3085927B1 (en) |
| WO (1) | WO2013154636A1 (en) |
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Also Published As
| Publication number | Publication date |
|---|---|
| US10584660B2 (en) | 2020-03-10 |
| EP3690215A1 (en) | 2020-08-05 |
| US20170130673A1 (en) | 2017-05-11 |
| US11566587B2 (en) | 2023-01-31 |
| US20200217273A1 (en) | 2020-07-09 |
| EP2807358A1 (en) | 2014-12-03 |
| EP3085927A1 (en) | 2016-10-26 |
| WO2013154636A1 (en) | 2013-10-17 |
| EP3690215B1 (en) | 2022-05-04 |
| EP2807358B1 (en) | 2020-05-06 |
| US20230167787A1 (en) | 2023-06-01 |
| EP2807358A4 (en) | 2015-10-21 |
| US12234791B2 (en) | 2025-02-25 |
| EP3085927B1 (en) | 2020-04-22 |
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