US20210010386A1 - Geared turbofan with four star/planetary gear reduction - Google Patents
Geared turbofan with four star/planetary gear reduction Download PDFInfo
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- US20210010386A1 US20210010386A1 US17/038,028 US202017038028A US2021010386A1 US 20210010386 A1 US20210010386 A1 US 20210010386A1 US 202017038028 A US202017038028 A US 202017038028A US 2021010386 A1 US2021010386 A1 US 2021010386A1
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- fan
- gear
- rotor
- turbofan engine
- ratio
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- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/12—Combinations with mechanical gearing
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- 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
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- 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
- F01D25/18—Lubricating arrangements
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H1/00—Toothed gearings for conveying rotary motion
- F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/0467—Elements of gearings to be lubricated, cooled or heated
- F16H57/0479—Gears or bearings on planet carriers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/048—Type of gearings to be lubricated, cooled or heated
- F16H57/0482—Gearings with gears having orbital motion
- F16H57/0486—Gearings with gears having orbital motion with fixed gear ratio
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- 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
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- 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
- F05D2240/00—Components
- F05D2240/50—Bearings
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- 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
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- 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
- F05D2260/98—Lubrication
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/0467—Elements of gearings to be lubricated, cooled or heated
- F16H57/0469—Bearings or seals
- F16H57/0471—Bearing
Definitions
- This application relates to a geared gas turbine engine, wherein a gear reduction is provided with only four star gears.
- Gas turbine engines typically include a fan delivering air into a bypass duct as bypass air and into a compressor.
- the air delivered into the compressor is mixed with fuel and ignited. Products of this combustion pass downstream over turbine rotors driving them to rotate.
- the turbine rotors in turn, drive the compressor and fan rotors.
- a fan rotor was driven at the same speed as a fan drive turbine rotor. This somewhat limited the design of the gas turbine engine. It was desirable that the fan rotate at a slower speed and have an increased diameter. However, it was also desirable that the turbine rotate at faster speeds. Thus, compromises had to be made.
- the gear reductions utilized today have utilized epicyclic planetary or star gear reductions. These gear reductions have always utilized at least five star gears between a sun gear and a ring gear. This has limited the available gear ratios.
- a turbofan engine assembly includes a nacelle and a turbofan engine.
- the turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades.
- a turbine rotor drives the fan rotor.
- An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor.
- the epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear.
- a gear ratio of the gear reduction is greater than 3.06.
- the fan drive turbine drives the sun gear to, in turn, drive the fan rotor.
- a bypass ratio is defined as a volume of air delivered by the fan into a bypass duct inward of the nacelle compared to a volume of air delivered into a compressor.
- the bypass ratio is greater than or equal to 12.0.
- the sun gear defines a sun gear center axis and a top dead center point is defined at a vertically uppermost location of the ring gear.
- a center point of a top two of the four intermediate gears are at a spacing angle from a line drawn between the top dead center point and the sun gear center axis. The spacing angle is at least 30 degrees.
- the spacing angle is 45 degrees.
- the intermediate gears are star gears.
- the gear ratio is greater than or equal to 4.0.
- the gear ratio is greater than or equal to 4.2.
- the gear ratio is less than or equal to 4.4.
- the gear ratio is greater than or equal to 4.0.
- the gear ratio is greater than or equal to 4.2
- the gear ratio is less than or equal to 4.4.
- At least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- At least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- the turbine rotor has greater than or equal to three stages.
- At least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- the turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5.
- the pressure ratio is pressure measured prior to the inlet as related to pressure at the outlet prior to an exhaust nozzle.
- the fan has a low fan pressure ratio of less than 1.45 measured across the fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).
- a turbofan engine assembly in another featured embodiment, includes a nacelle and a turbofan engine.
- the turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades.
- a turbine rotor drives the fan rotor.
- An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor.
- the epicyclic gear reduction includes a ring gear, a sun gear, and no more than four intermediate gears that engage the sun gear and the ring gear.
- the fan drive turbine drives the sun gear to, in turn, drive the fan rotor.
- a bypass ratio is defined as a volume of air delivered by the fan into a bypass duct inward of the nacelle compared to a volume of air delivered into a compressor.
- the bypass ratio is greater than or equal to 12.0.
- the turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5.
- the pressure ratio is pressure measured prior to the inlet as related to pressure at the outlet prior to an exhaust nozzle.
- the fan has a low fan pressure ratio of less than 1.45 measured across the fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).
- the sun gear defines a sun gear center axis and a top dead center point is defined at a vertically uppermost location of the ring gear.
- a center point of a top two of the four intermediate gears is at a spacing angle from a line drawn between the top dead center point and the sun gear center axis. The spacing angle is at least 15 degrees.
- the spacing angle is at least 30 degrees.
- the gear reduction has a gear ratio between the speed of a drive input to the sun gear, and an output speed of the fan rotor and the gear ratio being greater than or equal to 2.6.
- the gear ratio is greater than or equal to 3.06.
- the intermediate gears are star gears.
- the gear ratio is less than or equal to 4.4.
- the fan drive turbine has three or four stages of blades.
- At least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- the fan drive turbine has three or four stages of blades.
- the fan drive turbine having three or four stages of blades.
- At least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- At least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- the bypass ratio is greater than or equal to 14.0.
- the bypass ratio is greater than or equal to 14.0.
- FIG. 1 shows a schematic view of an embodiment of a gas turbine engine.
- FIG. 2A schematically shows an embodiment of a gas turbine engine incorporating an embodiment of a gear reduction.
- FIG. 2B schematically shows a gear arrangement within an embodiment of an epicyclic gear reduction.
- FIG. 1 schematically illustrates a gas turbine engine 20 .
- the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22 , a compressor section 24 , a combustor section 26 and a turbine section 28 .
- Alternative engines might include an augmentor section (not shown) among other systems or features.
- the fan section 22 drives air along a bypass flow path B in a bypass duct defined within a nacelle 15
- the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28 .
- the exemplary 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 structure 36 via several bearing systems 38 . It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.
- the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42 , a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46 .
- the inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30 .
- the high speed spool 32 includes an outer shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high) pressure turbine 54 .
- a combustor 56 is arranged in exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54 .
- a mid-turbine frame 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46 .
- the mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28 .
- the inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
- the core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52 , mixed and burned with fuel in the combustor 56 , then expanded over the high pressure turbine 54 and low pressure turbine 46 .
- the mid-turbine frame 57 includes airfoils 59 which are in the core airflow path C.
- the turbines 46 , 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
- gear system 48 may be located aft of combustor section 26 or even aft of turbine section 28
- fan section 22 may be positioned forward or aft of the location of gear system 48 .
- the engine 20 in one example is a high-bypass geared aircraft engine.
- the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10)
- the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3
- the low pressure turbine 46 has a pressure ratio that is greater than about five.
- the engine 20 bypass ratio is greater than about ten (10:1)
- the fan diameter is significantly larger than that of the low pressure compressor 44
- the low pressure turbine 46 has a pressure ratio that is greater than about five 5:1.
- Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle.
- the geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.
- the fan section 22 of the engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (10,668 meters).
- TFCT Thrust Specific Fuel Consumption
- Low fan pressure ratio is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.
- the low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45.
- Low corrected fan tip speed is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)] 0.5 .
- the “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 meters/second).
- FIG. 2A shows a gas turbine engine 100 having a fan drive turbine 102 including three stages of blades 104 , 106 and 108 .
- An optional fourth stage 110 is also shown.
- the fan drive turbine will preferably utilize at least three and sometimes four stages. Stated another way, the fan drive turbine has greater than or equal to three stages.
- a gear reduction 112 is included between the fan drive turbine 102 and a fan rotor 113 .
- the fan drive turbine 102 may be similar to the low pressure turbine as utilized in FIG. 1 , and also directly drives a low pressure compressor stage.
- the engine 100 may include three turbine rotors with a high pressure turbine rotor driving a high pressure compressor, an intermediate pressure turbine rotor driving an intermediate pressure compressor, and a low pressure turbine rotor being the fan drive turbine.
- FIG. 2B shows details of the gear reduction 112 .
- a ring gear 114 (shown partially) surrounds four intermediate gears 116 A, 116 B, 116 C, and 116 D, which can be either star (shown) or planetary gears.
- a sun gear 120 which is driven by the fan drive turbine 102 , is positioned within the star gears 116 A- 116 D.
- Journal bearings 118 mount the star gears 116 A- 116 D.
- the gear reduction is connected to drive the fan rotor in a manner as known in the art.
- gear ratios that are much higher than available with the prior art five stage (or more) gear reductions can be achieved.
- a five star gearbox has a limited gear ratio of about 3.06. This limits how fast the fan drive turbine can rotate and how slow the fan rotor can rotate.
- gear ratios of greater than 2.6 and up to about 4.4 can be achieved.
- a gear ratio of greater than or equal to about 4.0 is achieved.
- a gear ratio of greater than or equal to about 4.2 is achieved.
- the fan drive turbine is provided with three or four stages and can turn much faster than a turbine driving the prior epicyclic gear reductions utilizing five or more star gears.
- the fan drive turbine 102 can turn 37 percent faster than an example fan drive turbine in a gas turbine engine having an epicyclic gear reduction with five or more star gears.
- bypass ratios of greater than or equal to about 10.0 can be achieved.
- bypass ratios of greater than or equal to about 12.0 and even 14.0 may be achieved.
- An auxiliary oil circuit is shown schematically at 121 .
- This oil circuit will provide oil to the journal bearings 118 whenever there is rotation of the fan rotor. Thus, during windmilling oil will be provided.
- a primary oil supply system 122 there is also a primary oil supply system 122 .
- the details of circuits 121 and 122 may be as known.
- the center point C of the top gears 116 A and 116 C are spaced by 45 degrees from a top dead center point TDC. It is known that the greatest stresses induced between the gears 114 and 116 would be at the top dead center point TDC. Thus, spacing the gears from that point reduces the challenges the gears will face. Stated otherwise, the center point of the star gears measured from a center point SC of the sun gear is spaced from the top dead center TDC by an angle of at least about 15 degrees. In embodiments, the spacing angle is at least about 30 degrees. As mentioned, in one embodiment, the spacing angle is 45 degrees.
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Abstract
A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.
Description
- This application is a continuation of U.S. application Ser. No. 16/173,051 filed Oct. 29, 2018, which is a continuation of U.S. application Ser. No. 14/935,673 filed on Dec. 1, 2015, now U.S. Pat. No. 10,508,562 granted on Dec. 17, 2019.
- This application relates to a geared gas turbine engine, wherein a gear reduction is provided with only four star gears.
- Gas turbine engines are known and typically include a fan delivering air into a bypass duct as bypass air and into a compressor. The air delivered into the compressor is mixed with fuel and ignited. Products of this combustion pass downstream over turbine rotors driving them to rotate. The turbine rotors, in turn, drive the compressor and fan rotors.
- Historically, a fan rotor was driven at the same speed as a fan drive turbine rotor. This somewhat limited the design of the gas turbine engine. It was desirable that the fan rotate at a slower speed and have an increased diameter. However, it was also desirable that the turbine rotate at faster speeds. Thus, compromises had to be made.
- More recently, a gear reduction has been incorporated between the fan drive turbine and the fan rotor. This has allowed the size of the fan rotor to increase. At the same time, the turbine rotor can rotate at increased speed.
- The gear reductions utilized today have utilized epicyclic planetary or star gear reductions. These gear reductions have always utilized at least five star gears between a sun gear and a ring gear. This has limited the available gear ratios.
- In a featured embodiment, a turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor. A bypass ratio is defined as a volume of air delivered by the fan into a bypass duct inward of the nacelle compared to a volume of air delivered into a compressor. The bypass ratio is greater than or equal to 12.0. The sun gear defines a sun gear center axis and a top dead center point is defined at a vertically uppermost location of the ring gear. A center point of a top two of the four intermediate gears are at a spacing angle from a line drawn between the top dead center point and the sun gear center axis. The spacing angle is at least 30 degrees.
- In another embodiment according to the previous embodiment, the spacing angle is 45 degrees.
- In another embodiment according to any of the previous embodiments, the intermediate gears are star gears.
- In another embodiment according to any of the previous embodiments, the gear ratio is greater than or equal to 4.0.
- In another embodiment according to any of the previous embodiments, the gear ratio is greater than or equal to 4.2.
- In another embodiment according to any of the previous embodiments, the gear ratio is less than or equal to 4.4.
- In another embodiment according to any of the previous embodiments, the gear ratio is greater than or equal to 4.0.
- In another embodiment according to any of the previous embodiments, the gear ratio is greater than or equal to 4.2
- In another embodiment according to any of the previous embodiments, the gear ratio is less than or equal to 4.4.
- In another embodiment according to any of the previous embodiments, at least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- In another embodiment according to any of the previous embodiments, at least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- In another embodiment according to any of the previous embodiments, the turbine rotor has greater than or equal to three stages.
- In another embodiment according to any of the previous embodiments, at least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- In another embodiment according to any of the previous embodiments, the turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5. The pressure ratio is pressure measured prior to the inlet as related to pressure at the outlet prior to an exhaust nozzle.
- In another embodiment according to any of the previous embodiments, the fan has a low fan pressure ratio of less than 1.45 measured across the fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).
- In another featured embodiment, a turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and no more than four intermediate gears that engage the sun gear and the ring gear. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor. A bypass ratio is defined as a volume of air delivered by the fan into a bypass duct inward of the nacelle compared to a volume of air delivered into a compressor. The bypass ratio is greater than or equal to 12.0. The turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5. The pressure ratio is pressure measured prior to the inlet as related to pressure at the outlet prior to an exhaust nozzle. The fan has a low fan pressure ratio of less than 1.45 measured across the fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).
- In another embodiment according to the previous embodiment, the sun gear defines a sun gear center axis and a top dead center point is defined at a vertically uppermost location of the ring gear. A center point of a top two of the four intermediate gears is at a spacing angle from a line drawn between the top dead center point and the sun gear center axis. The spacing angle is at least 15 degrees.
- In another embodiment according to any of the previous embodiments, wherein the spacing angle is at least 30 degrees.
- In another embodiment according to any of the previous embodiments, the gear reduction has a gear ratio between the speed of a drive input to the sun gear, and an output speed of the fan rotor and the gear ratio being greater than or equal to 2.6.
- In another embodiment according to any of the previous embodiments, the gear ratio is greater than or equal to 3.06.
- In another embodiment according to any of the previous embodiments, the intermediate gears are star gears.
- In another embodiment according to any of the previous embodiments, the gear ratio is less than or equal to 4.4.
- In another embodiment according to any of the previous embodiments, the fan drive turbine has three or four stages of blades.
- In another embodiment according to any of the previous embodiments, at least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- In another embodiment according to any of the previous embodiments, the fan drive turbine has three or four stages of blades.
- In another embodiment according to any of the previous embodiments, the fan drive turbine having three or four stages of blades.
- In another embodiment according to any of the previous embodiments, at least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- In another embodiment according to any of the previous embodiments, at least one blade row in the turbine rotor has blades formed of a directionally solidified material.
- In another embodiment according to any of the previous embodiments, the bypass ratio is greater than or equal to 14.0.
- In another embodiment according to any of the previous embodiments, the bypass ratio is greater than or equal to 14.0.
- These and other features may be best understood from the following drawings and specification.
-
FIG. 1 shows a schematic view of an embodiment of a gas turbine engine. -
FIG. 2A schematically shows an embodiment of a gas turbine engine incorporating an embodiment of a gear reduction. -
FIG. 2B schematically shows a gear arrangement within an embodiment of an epicyclic gear reduction. -
FIG. 1 schematically illustrates agas turbine engine 20. Thegas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates afan section 22, acompressor section 24, acombustor section 26 and aturbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. Thefan section 22 drives air along a bypass flow path B in a bypass duct defined within anacelle 15, while thecompressor section 24 drives air along a core flow path C for compression and communication into thecombustor section 26 then expansion through theturbine section 28. 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 two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures. - The
exemplary engine 20 generally includes alow speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an enginestatic structure 36 viaseveral bearing systems 38. It should be understood that various bearingsystems 38 at various locations may alternatively or additionally be provided, and the location of bearingsystems 38 may be varied as appropriate to the application. - The
low speed spool 30 generally includes aninner shaft 40 that interconnects afan 42, a first (or low)pressure compressor 44 and a first (or low)pressure turbine 46. Theinner shaft 40 is connected to thefan 42 through a speed change mechanism, which in exemplarygas turbine engine 20 is illustrated as a gearedarchitecture 48 to drive thefan 42 at a lower speed than thelow speed spool 30. Thehigh speed spool 32 includes anouter shaft 50 that interconnects a second (or high)pressure compressor 52 and a second (or high)pressure turbine 54. Acombustor 56 is arranged inexemplary gas turbine 20 between thehigh pressure compressor 52 and thehigh pressure turbine 54. Amid-turbine frame 57 of the enginestatic structure 36 is arranged generally between thehigh pressure turbine 54 and thelow pressure turbine 46. Themid-turbine frame 57 furthersupports bearing systems 38 in theturbine section 28. Theinner shaft 40 and theouter shaft 50 are concentric and rotate via bearingsystems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes. - The core airflow is compressed by the
low pressure compressor 44 then thehigh pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over thehigh pressure turbine 54 andlow pressure turbine 46. Themid-turbine frame 57 includesairfoils 59 which are in the core airflow path C. Theturbines low speed spool 30 andhigh speed spool 32 in response to the expansion. It will be appreciated that each of the positions of thefan section 22,compressor section 24,combustor section 26,turbine section 28, and fandrive gear system 48 may be varied. For example,gear system 48 may be located aft ofcombustor section 26 or even aft ofturbine section 28, andfan section 22 may be positioned forward or aft of the location ofgear system 48. - The
engine 20 in one example is a high-bypass geared aircraft engine. In a further example, theengine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10), the gearedarchitecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and thelow pressure turbine 46 has a pressure ratio that is greater than about five. In one disclosed embodiment, theengine 20 bypass ratio is greater than about ten (10:1), the fan diameter is significantly larger than that of thelow pressure compressor 44, and thelow pressure turbine 46 has a pressure ratio that is greater than about five 5:1.Low pressure turbine 46 pressure ratio is pressure measured prior to inlet oflow pressure turbine 46 as related to the pressure at the outlet of thelow pressure turbine 46 prior to an exhaust nozzle. The gearedarchitecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans. - A significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. The
fan section 22 of theengine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (10,668 meters). The flight condition of 0.8 Mach and 35,000 ft (10,668 meters), with the engine at its best fuel consumption—also known as “bucket cruise Thrust Specific Fuel Consumption (‘TSFCT’)”—is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point. “Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45. “Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)]0.5. The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 meters/second). -
FIG. 2A shows agas turbine engine 100 having afan drive turbine 102 including three stages ofblades fourth stage 110 is also shown. With the arrangement of this disclosure, the fan drive turbine will preferably utilize at least three and sometimes four stages. Stated another way, the fan drive turbine has greater than or equal to three stages. - A
gear reduction 112 is included between thefan drive turbine 102 and afan rotor 113. Thefan drive turbine 102 may be similar to the low pressure turbine as utilized inFIG. 1 , and also directly drives a low pressure compressor stage. Alternatively, theengine 100 may include three turbine rotors with a high pressure turbine rotor driving a high pressure compressor, an intermediate pressure turbine rotor driving an intermediate pressure compressor, and a low pressure turbine rotor being the fan drive turbine. -
FIG. 2B shows details of thegear reduction 112. A ring gear 114 (shown partially) surrounds fourintermediate gears sun gear 120, which is driven by thefan drive turbine 102, is positioned within the star gears 116A-116D.Journal bearings 118 mount the star gears 116A-116D. - As known, the gear reduction is connected to drive the fan rotor in a manner as known in the art.
- With a four star epicyclic gear reduction, gear ratios that are much higher than available with the prior art five stage (or more) gear reductions can be achieved. As an example, a five star gearbox has a limited gear ratio of about 3.06. This limits how fast the fan drive turbine can rotate and how slow the fan rotor can rotate.
- However, with the disclosed four star epicyclic gear reduction, gear ratios of greater than 2.6 and up to about 4.4 can be achieved. In one embodiment, a gear ratio of greater than or equal to about 4.0 is achieved. In another embodiment, a gear ratio of greater than or equal to about 4.2 is achieved.
- Moreover, the fan drive turbine is provided with three or four stages and can turn much faster than a turbine driving the prior epicyclic gear reductions utilizing five or more star gears. As an example, the
fan drive turbine 102 can turn 37 percent faster than an example fan drive turbine in a gas turbine engine having an epicyclic gear reduction with five or more star gears. - It is conventional wisdom that gear reductions having fewer star gears may raise some other undesirable characteristics. In particular, as the number of star gears decreases for a given ring gear diameter, the sun gear's diameter becomes smaller. Further, the sun gear has fewer teeth and may see higher gear stresses. Further, the space for the drive input shaft from the fan drive turbine into the sun gear becomes smaller. Thus, the benefits of a four star gear reduction are unexpected. Still, while utilizing four star gears provides desirable characteristics, even fewer star gears may not be desirable.
- As the
fan drive turbine 102 begins to turn more quickly, the temperatures it may see also increase. Thus, it may be desirable to form at least one row, and perhaps all of the rows, of the blades in thefan drive turbine 102 from directionally solidified blade materials. - In addition, with this arrangement, bypass ratios of greater than or equal to about 10.0 can be achieved. In addition, bypass ratios of greater than or equal to about 12.0 and even 14.0 may be achieved.
- An auxiliary oil circuit is shown schematically at 121. This oil circuit will provide oil to the
journal bearings 118 whenever there is rotation of the fan rotor. Thus, during windmilling oil will be provided. Of course, there is also a primaryoil supply system 122. The details ofcircuits - As shown in
FIG. 2B , the center point C of thetop gears gears 114 and 116 would be at the top dead center point TDC. Thus, spacing the gears from that point reduces the challenges the gears will face. Stated otherwise, the center point of the star gears measured from a center point SC of the sun gear is spaced from the top dead center TDC by an angle of at least about 15 degrees. In embodiments, the spacing angle is at least about 30 degrees. As mentioned, in one embodiment, the spacing angle is 45 degrees. - Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
Claims (20)
1. A turbofan engine comprising:
a fan including a fan rotor having fan blades, and housing enclosing said fan rotor and said blades;
a turbine rotor driving said fan rotor;
an epicyclic gear reduction positioned between said fan rotor and said turbine rotor, said epicyclic gear reduction including a ring gear, a sun gear, and four intermediate gears that engage said sun gear and said ring gear, a gear ratio of said gear reduction is greater than 3.06;
wherein said fan drive turbine drives said sun gear to, in turn, drive said fan rotor;
a bypass ratio is defined as a volume of air delivered by said fan into a bypass duct inward of said housing compared to a volume of air delivered into a compressor, said bypass ratio is greater than or equal to 12.0; and
wherein there is a primary oil supply supplying oil to journal bearings that support said intermediate gears.
2. The turbofan engine as set forth in claim 1 , wherein said gear ratio is greater than or equal to 4.0.
3. The turbofan engine as set forth in claim 2 , wherein said gear ratio is greater than or equal to 4.2.
4. The turbofan engine as set forth in claim 2 , wherein said gear ratio is less than or equal to 4.4.
5. The turbofan engine as set forth in claim 2 , wherein there is an auxiliary oil supply supplying oil to said journal bearings when there is windmilling of said fan rotor.
6. The turbofan engine as set forth in claim 1 , wherein there is an auxiliary oil supply supplying oil to said journal bearings when there is windmilling of said fan rotor.
7. The turbofan engine as set forth in claim 1 , wherein said housing is a nacelle.
8. A turbofan engine comprising:
a fan including a fan rotor having fan blades, and a housing enclosing said fan rotor and said blades;
a turbine rotor driving said fan rotor;
an epicyclic gear reduction positioned between said fan rotor and said turbine rotor, said epicyclic gear reduction including a ring gear, a sun gear, and four intermediate gears that engage said sun gear and said ring gear, a gear ratio of said gear reduction is greater than 3.06;
wherein said fan drive turbine drives said sun gear to, in turn, drive said fan rotor;
a bypass ratio is defined as a volume of air delivered by said fan into a bypass duct inward of said housing compared to a volume of air delivered into a compressor, said bypass ratio is greater than or equal to 12.0; and
wherein at least one blade row in said turbine rotor has blades formed of a directionally solidified material.
9. The turbofan engine as set forth in claim 8 , wherein said turbine rotor has greater than or equal to three stages.
10. The turbofan engine as set forth in claim 8 , wherein said turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to said inlet as related to pressure at said outlet prior to an exhaust nozzle.
11. The turbofan engine as set forth in claim 10 , wherein said turbofan has a low fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).
12. The turbofan engine as set forth in claim 8 , wherein there is a primary oil supply supplying oil to journal bearings that support said intermediate gears
13. The turbofan engine as set forth in claim 12 , wherein there is an auxiliary oil supply supplying oil to said journal bearings when there is windmilling of said fan rotor.
14. A turbofan engine comprising:
a fan including a fan rotor having fan blades, and a housing enclosing said fan rotor and said blades;
a turbine rotor driving said fan rotor; and
an epicyclic gear reduction positioned between said fan rotor and said turbine rotor, said epicyclic gear reduction including a ring gear, a sun gear, and no more than four intermediate gears that engage said sun gear and said ring gear;
wherein said fan drive turbine drives said sun gear to, in turn, drive said fan rotor;
a bypass ratio is defined as a volume of air delivered by said fan into a bypass duct inward of said housing compared to a volume of air delivered into a compressor, said bypass ratio is greater than or equal to 12.0; and
wherein said turbine rotor includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to said inlet as related to pressure at said outlet prior to an exhaust nozzle, and wherein said fan has a low fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low corrected fan tip speed of the fan rotor is less than 1150 ft/second (350.5 meters/second).
15. The turbofan engine as set forth in claim 14 , wherein said gear reduction having a gear ratio between the speed of a drive input to the sun gear, and an output speed of the fan rotor and said gear ratio being greater than or equal to 2.6.
16. The turbofan engine as set forth in claim 14 , wherein there is a primary oil supply supplying oil to journal bearings that support said intermediate gears
17. The turbofan engine as set forth in claim 14 , wherein there is an auxiliary oil supply supplying oil to said journal bearings when there is windmilling of said fan rotor.
18. The turbofan engine as set forth in claim 14 , wherein said gear ratio is greater than or equal to 3.06.
19. The turbofan engine as set forth in claim 18 , wherein said gear ratio is less than or equal to 4.4.
20. The turbofan engine as set forth in claim 14 , wherein said fan drive turbine having three or four stages of blades.
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US17/038,028 US20210010386A1 (en) | 2015-12-01 | 2020-09-30 | Geared turbofan with four star/planetary gear reduction |
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US14/935,673 US10508562B2 (en) | 2015-12-01 | 2015-12-01 | Geared turbofan with four star/planetary gear reduction |
US16/173,051 US10801355B2 (en) | 2015-12-01 | 2018-10-29 | Geared turbofan with four star/planetary gear reduction |
US17/038,028 US20210010386A1 (en) | 2015-12-01 | 2020-09-30 | Geared turbofan with four star/planetary gear reduction |
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US16/173,051 Continuation US10801355B2 (en) | 2015-12-01 | 2018-10-29 | Geared turbofan with four star/planetary gear reduction |
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US17/038,028 Abandoned US20210010386A1 (en) | 2015-12-01 | 2020-09-30 | Geared turbofan with four star/planetary gear reduction |
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US16/173,051 Active 2036-06-14 US10801355B2 (en) | 2015-12-01 | 2018-10-29 | Geared turbofan with four star/planetary gear reduction |
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US8727935B2 (en) * | 2012-07-30 | 2014-05-20 | United Technologies Corporation | Fan drive gear system torque frame pin retainer |
US8807916B2 (en) | 2012-09-27 | 2014-08-19 | United Technologies Corporation | Method for setting a gear ratio of a fan drive gear system of a gas turbine engine |
US8753065B2 (en) | 2012-09-27 | 2014-06-17 | United Technologies Corporation | Method for setting a gear ratio of a fan drive gear system of a gas turbine engine |
US8678743B1 (en) | 2013-02-04 | 2014-03-25 | United Technologies Corporation | Method for setting a gear ratio of a fan drive gear system of a gas turbine engine |
EP3036416B1 (en) | 2013-08-20 | 2021-08-25 | Raytheon Technologies Corporation | High thrust geared gas turbine engine |
EP3058245B1 (en) | 2013-10-15 | 2020-05-06 | FM Energie GmbH & Co. KG | Elastic bushing for a planetary bearing |
WO2015065720A1 (en) | 2013-11-01 | 2015-05-07 | United Technologies Corporation | Auxiliary oil pump for gas turbine engine gear reduction |
US20170002687A1 (en) * | 2015-07-02 | 2017-01-05 | United Technologies Corporation | Fan-drive gear system with separate scavenge pump |
US10041489B2 (en) * | 2015-10-22 | 2018-08-07 | United Technologies Corporation | Auxiliary pump and gas turbine engine oil circuit monitoring system |
US20180080411A1 (en) | 2016-09-16 | 2018-03-22 | General Electric Company | Gas turbine engine |
-
2015
- 2015-12-01 US US14/935,673 patent/US10508562B2/en active Active
-
2016
- 2016-12-01 EP EP16201810.5A patent/EP3176410A1/en active Pending
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2018
- 2018-10-29 US US16/173,051 patent/US10801355B2/en active Active
-
2020
- 2020-09-30 US US17/038,028 patent/US20210010386A1/en not_active Abandoned
Also Published As
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EP3176410A1 (en) | 2017-06-07 |
US20170152756A1 (en) | 2017-06-01 |
US10508562B2 (en) | 2019-12-17 |
US20190153887A1 (en) | 2019-05-23 |
US10801355B2 (en) | 2020-10-13 |
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