WO2008082335A1 - A power transmission device for a gas turbine engine - Google Patents

A power transmission device for a gas turbine engine Download PDF

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Publication number
WO2008082335A1
WO2008082335A1 PCT/SE2006/001517 SE2006001517W WO2008082335A1 WO 2008082335 A1 WO2008082335 A1 WO 2008082335A1 SE 2006001517 W SE2006001517 W SE 2006001517W WO 2008082335 A1 WO2008082335 A1 WO 2008082335A1
Authority
WO
WIPO (PCT)
Prior art keywords
power transmission
pressure shaft
transmission device
high pressure
gas turbine
Prior art date
Application number
PCT/SE2006/001517
Other languages
French (fr)
Inventor
Bertil JÖNSSON
Original Assignee
Volvo Aero Corporation
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Volvo Aero Corporation filed Critical Volvo Aero Corporation
Priority to PCT/SE2006/001517 priority Critical patent/WO2008082335A1/en
Publication of WO2008082335A1 publication Critical patent/WO2008082335A1/en

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Classifications

    • 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • 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
    • 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
    • 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
    • F16H2200/00—Transmissions for multiple ratios
    • F16H2200/003—Transmissions for multiple ratios characterised by the number of forward speeds
    • F16H2200/0034—Transmissions for multiple ratios characterised by the number of forward speeds the gear ratios comprising two forward speeds
    • 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
    • F16H2200/00—Transmissions for multiple ratios
    • F16H2200/20—Transmissions using gears with orbital motion
    • F16H2200/2002—Transmissions using gears with orbital motion characterised by the number of sets of orbital gears
    • F16H2200/2005—Transmissions using gears with orbital motion characterised by the number of sets of orbital gears with one sets of orbital gears
    • 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
    • F16H2200/00—Transmissions for multiple ratios
    • F16H2200/20—Transmissions using gears with orbital motion
    • F16H2200/203—Transmissions using gears with orbital motion characterised by the engaging friction means not of the freewheel type, e.g. friction clutches or brakes
    • F16H2200/2033—Transmissions using gears with orbital motion characterised by the engaging friction means not of the freewheel type, e.g. friction clutches or brakes with one engaging means

Definitions

  • the present invention relates to a power transmission device for a gas turbine engine comprising a low pressure shaft and a high pressure shaft, wherein the high pressure shaft is arranged concentric to the low pressure shaft.
  • the power transmission device further comprises an accessory unit comprising at least one electric machine adapted for a gas turbine engine starting operation and/or for generating electrical power.
  • the invention also relates to a gas turbine engine comprising the power transmission device and an aeroplane comprising the gas turbine engine.
  • the low pressure shaft is adapted to drive a low pressure compressor or fan in the gas turbine engine and the high pressure shaft is adapted to drive a high pressure compressor in the gas turbine engine.
  • the gas turbine engine may be a turbojet or turbofan engine.
  • the accessory unit comprises an accessory gearbox which is adapted to drive further ancillary services both of the turbine engines themselves and of the aeroplane for which they provide propulsion.
  • Such aeroplane ancillary services comprises ancillary machines such as generators, fuel pumps, fuel flow governors, oil pumps, centrifugal breathers, etc.
  • ancillary machines such as generators, fuel pumps, fuel flow governors, oil pumps, centrifugal breathers, etc.
  • the high pressure shaft that, by tradition, has been the shaft from which said power is extracted, will not be able to deliver all of said power alone, due to the fact that a large mechanical power extraction has a negative effect on the operation of the high pressure shaft as it is likely to cause pumping of the compressor, in particular when the engine is running at low speed.
  • PRIOR ART US 5,103,631 discloses a differential gear assembly suitable for providing power take off from a gas turbine engine, comprising first and second power input gears which drive a plurality of idler gears rotatably mounted on a common cage structure.
  • the idler gears are grouped in meshing pairs so that one idler gear of each pair is additionally in meshing engagement with one of the power input gears and the other idler gear of each pair is additionally in meshing engagement with the other of the power input gears.
  • the first and second power input gears drive the common cage structure at the mean speed of the power input gears and the common cage structure in turn drives a single power output shaft.
  • US 5,103,631 discloses a device that uses a planetary gear for the purpose of retrieving power from both LP-shaft and HP-shaft and transfer it to an accessory gearbox. US 5,103,631 also discloses the possibility of providing a different division of torque split between the two power input shafts, by modifying the gear assembly so that one of the gears is of larger diameter than the other. It is also mentioned that any use of input gears which are not of the same diameter would necessitate the appropriate repositioning of the idler gears .
  • US patent application No. 2006/0034696 discloses a twin-spool turbojet engine with a differential with a first planetary pinion driven by the shaft of the high pressure spool, and a second planetary pinion driven by the shaft of the low pressure spool, said planetary pinions driving satellite pinions mounted in a cage by which the ancillary machines are driven.
  • a step down gear mechanism connected to the high pressure shaft upstream the differential as seen in the power drive train direction, the mechanical transmission ratio between the high pressure shaft and the first planetary pinion of the differential gear, and the transmission ratio between the low pressure shaft and the second planetary pinion of the differential gear are such that the power extraction distribution between the high pressure spool and the low pressure spool is appropriately distributed for the different operation conditions (rotational speeds) of the engine.
  • the power extraction distribution between the high pressure spool and the low pressure spool at idle speed is between 80%/20% and 20%/80%.
  • a primary purpose of the invention is to achieve a power transmission device for a gas turbine engine, which creates conditions for extracting a larger proportion of the power and preferably all power required by the ancillary machines from the low pressure shaft.
  • the power transmission device comprises a transmission unit operatively connected to the low pressure shaft and adapted for power transmission from the low pressure shaft to the accessory unit, that the transmission unit is positioned non-concentric with the low pressure shaft, that a first transmission means is operatively connected for power transmission from the low pressure shaft to the transmission unit, and that a second transmission means is operatively connected for power transmission from the accessory unit to the high pressure shaft in a manner bypassing the transmission unit.
  • bypassing should be interpreted as functionally (or operationally) bypassing the transmission unit in that the transmission unit does not effect the power transmission path from the accessory unit to the high pressure shaft.
  • the second transmission means is configured so that the power transmission path in its entirety extends externally of the transmission unit.
  • the second transmission means is arranged in parallel to the first transmission means and the transmission unit.
  • a starting operation may be performed using the high pressure shaft, while power off take may be performed from the low pressure shaft.
  • the power transmission device creates conditions for a minimum of structural modification and additional parts of the gas turbine engine. More specifically, only one connection is required to the low pressure shaft and only one connection is required to the high pressure shaft.
  • each of the first and second transmission means comprises a tower shaft extending out of a gas turbine engine housing, which houses the low pressure shaft and the high pressure shaft.
  • the transmission unit may be located externally of the gas turbine engine housing, wherein service is facilitated.
  • the device comprises means for operatively connecting and disconnecting, respectively at least one of said electric machines adapted for the gas turbine engine starting operation to the high pressure shaft.
  • the connection means is adapted to automatically disconnect said at least one of said electric machines from operational connection with the high pressure shaft when a speed of the high pressure shaft exceeds a predetermined limit value.
  • the connection means is passive in the respect that no control means is required for its activation. This creates conditions for a reliable operation.
  • the predetermined limit value corresponds to a maximum speed for a gas turbine engine starting operation.
  • the second transmission means is operatively connected for power transmission from at least one of said electric machines adapted for the gas turbine engine starting operation to the high pressure shaft and also for power transmission from the high pressure shaft to the accessory unit.
  • the second transmission means is adapted for a two-way power transmission.
  • the transmission unit comprises a gear changing mechanism adapted to change between at least two gears for said power transmission from the low pressure shaft to the accessory unit.
  • This is especially advantageous due to the large operational speed range of the low pressure shaft.
  • this embodiment creates conditions for power transmission from the low speed shaft over substantially the complete operational speed range of the low pressure shaft.
  • the complete operational speed range of the low pressure shaft corresponds to a self-sustained operation of the gas turbine engine comprising idling, a medium and higher operational speed range.
  • FIG 1 is a schematic illustration of a gas turbine engine in the form of an aircraft engine
  • FIG 2 is a schematic illustration of a first embodiment of a power transmission device for the gas turbine engine
  • FIG 3 is a schematic illustration of a second embodiment of a power transmission device for the gas turbine engine
  • FIG 4 and 5 show an example of a gear set in the power transmission device.
  • Fig. 1 is an oversight view of a gas turbine engine 1 according to the invention provided with a power transmission device 2 according to the invention.
  • the gas turbine engine 1 shown in fig. 1 is of conventional construction and comprises, in axial flow series, an air intake 3, low pressure compressor 4, high pressure compressor 5, combustion equipment 6, high pressure turbine 7, low pressure turbine 8 and an exhaust outlet 9.
  • the high pressure compressor is driven by the high pressure turbine via a first hollow high pressure shaft 10.
  • the low pressure compressor is driven by the low pressure turbine via a second hollow low pressure shaft 11 which is coaxially disposed within the high pressure shaft 10.
  • the gas turbine 1 operates in the conventional manner whereby air drawn in through the air intake 3 is compressed by the low pressure compressor before passing into the high pressure compressor where it is compressed further. The compressed air then flows into the combustion equipment 6 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through the high and low pressure turbines 7, 8 before being exhausted to the atmosphere through the exhaust nozzle 9.
  • the power transmission device 2 comprises a transmission unit 13 (see figure 2) , which is adapted to transfer power from the low pressure shaft 11 to an accessory unit 12 during engine operation, said accessory unit 12 being located on the outside of the engine 1.
  • the accessory unit 12 comprises an accessory gearbox 31 and is adapted to drive different ancillary machines, such as generators and oil or fuel hydraulic pumps . More specifically, the accessory unit 12 comprises at least one electric machine 29,30 adapted for a gas turbine engine starting operation and for generating electrical power. However, during start up of the engine 1, the power transfer direction is reversed, whereby power is transferred from a generator in the accessory unit 12 to the high pressure shaft 10.
  • the device according to the invention is set in an operation mode by which power is transferred from the low pressure shaft 11 to the accessory unit 12 through said transmission unit 13.
  • Figure 2 shows the power transmission device 2 according to a first embodiment.
  • the high pressure shaft 10 and the low pressure shaft 11 are counter-rotating.
  • the transmission unit 13 is arranged externally of a gas turbine engine housing 15, which accommodates at least part of the low pressure shaft.
  • the transmission unit 13 is operatively connected to the low pressure shaft 11 and adapted for power transmission from the low pressure shaft 11 to the accessory unit 12.
  • the transmission unit 13 is configured for changing gears. More specifically, the transmission unit 13 is a step gear transmission.
  • the transmission unit 13 comprises a gear changing mechanism 14 adapted to change between at least two gears for transmitting power from the low pressure shaft 11 to the accessory unit 12 over substantially the complete operational speed range of the low pressure shaft.
  • a first transmission means 18 is operatively connected for power transmission from the low pressure shaft 11 to the externally located accessory unit 12 via the externally located transmission unit 13.
  • the first transmission means 18 comprises a first tower shaft 19. More specifically, the first tower shaft 19 is connected to the gear changing mechanism 14 in the transmission unit 13 and the low pressure shaft 11, respectively, via bevel gears 27,28.
  • a second transmission means 32 is operatively connected for power transmission from the accessory unit 12 to the high pressure shaft 10.
  • the second transmission means 32 comprises a second tower shaft 38.
  • the second tower shaft 38 is connected to the accessory unit 12 and the high pressure shaft 10, respectively, via bevel gears 34,35.
  • the first and second transmission means 18,32 are arranged at a distance from each other in an axial direction 20 of the gas turbine engine 1.
  • the tower shafts 19,38 extend substantially at right angles with the gas turbine rotational axis 20.
  • the accessory unit 12 is arranged externally of the gas turbine engine housing 15. Further, the tower shafts 19,38 extends through two separate holes in the casing 15 in order to connect the externally located accessory unit 12 with the low and high pressure shafts 10,11.
  • the device 2 further comprises means 16 for operatively connecting and disconnecting, respectively the accessory unit 12 to the high pressure shaft 10.
  • the connection means 16 is adapted to automatically disconnect the accessory unit 12 from operational connection with the high pressure shaft 10 when a speed of the high pressure shaft exceeds a predetermined limit value, which corresponds to a maximum speed for a gas turbine engine starting operation.
  • the connection means 16 comprises a clutch.
  • the high pressure shaft clutch 16 is formed by a freewheel mechanism.
  • the high pressure shaft clutch 16 is arranged externally of the housing 15 and preferably directly on an output shaft of the accessory unit 12, i.e upstream of the second tower shaft in the power transmission direction during a starting operation.
  • the accessory unit 12 is operatively connected to the high pressure shaft 10 in a manner bypassing the transmission unit 13.
  • the transmission unit 13 is adapted to transmit at least 50%, preferably at least 80% and especially 100% of the required power for the components/machines in the accessory unit 12 from the low pressure shaft 11 over substantially the complete operational speed range of the low pressure shaft.
  • the transmission unit 13 comprises a gear set 21 arranged between the low pressure shaft 11 and the accessory unit 12.
  • the gear changing mechanism 14 is adapted for connecting and disconnecting, respectively, the gear set 21 from being drivingly connected to the accessory unit 12. More specifically, the transmission unit 13 comprises an intermediate power transmission shaft 17, which is drivingly connected between the bevel gear 27 and the accessory unit 12.
  • the gear set 21 is in direct operational connection with the intermediate power transmission shaft 17. Further, the gear changing mechanism 14 is also in direct operational connection with the intermediate power transmission shaft 17.
  • the gear changing mechanism 14 comprises a clutch.
  • the clutch 14 is a one-way clutch in the form of a free-wheeling clutch.
  • the gear changing mechanism 14 In a low speed range, the gear changing mechanism 14 is disengaged from the low pressure shaft 11, wherein power is transmitted from the low pressure shaft 11 to the accessory unit 12 via the gear set 21. In a high speed range, the gear changing mechanism 14 is engaged, wherein power is transmitted from the low pressure shaft 11 to the accessory unit 12 via the tower shaft and the gear changing mechanism 14.
  • the gear set 21 is a differential gear in the form of an epicyclic gear, see fig. 4-5.
  • Means 23 is arranged for activating the gear set 21.
  • the activation means 23 comprises a clutch. 24, or brake, which is adapted to operationally connect an input gear member 101 to a stationary part 25, or wall, in the transmission unit.
  • the clutch is a multi-plate clutch.
  • the clutch 24 is the only active means in the device 2 in the respect that it is the only means that is actively controlled during operation.
  • a stationary arranged hydraulic piston may be used for application of the clutch, wherein oil supply and drainage may be arranged easily and reliably.
  • the differential gear member to be locked may be a sun gear in the differential gear 21.
  • the differential gear 21 comprises at least one pair of idler gears 102,103, see figure 4, which are arranged in meshing engagement with each other.
  • a first idler gear 102 is in meshing engagement with the input gear member 101.
  • a second idler gear 103 is in meshing engagement with an output gear member 104.
  • the idler gears 102,103 are rotatably mounted in a differential gear casing 105.
  • the differential gear casing 105 comprises means 106 for rotationalIy rigidly connecting the casing 105 to the intermediate power transmission shaft 17.
  • Said connection means 106 comprises a plurality of circumferentialIy spaced radial drive spokes 106.
  • the spokes 106 are arranged axialIy between the input gear member 101 and the output gear member 104.
  • the accessory unit 12 comprises two electric machines 29,30 adapted for a starting operation and for generating electrical power. These electric machines 29,30 are in the following referred to as a Starter/Generator, or S/G.
  • one or both S/G 29,30 is controlled to drive the high pressure shaft 10 via the free-wheeling clutch 16.
  • the low pressure , shaft 11 is however not driven since the clutch 24 for the gear set 21 is not activated and the clutch 14 is free-wheeling.
  • a predetermined speed limit value a maximum speed for the starting operation
  • the S/G is switched to an electric power generating state, the gear set 21 is activated via the clutch 24 and the one-way clutch 14 is free-wheeling.
  • the multi-plate clutch 24 is released in a manner with controlled slip, wherein the low pressure shaft 11 drives the accessory unit 12 via the intermediate shaft 17 and the clutch 14. This operation is continued in a higher operational speed range (comprising a maximum speed) .
  • the multi-plate clutch 24 When the speed of the low pressure shaft is reduced to a predetermined limit value, the multi-plate clutch 24 is actuated in a manner with controlled slip, the one-way- clutch 14 is automatically released and will freewheel, wherein the low pressure shaft 11 drives the accessory unit 12 via the intermediate shaft 17 and the gear set 21.
  • the first and second transmission means 18,32 may be arranged in a coaxial (concentric) relationship. More precisely, the first tower shaft 19 may be arranged concentric to the second tower shaft 38. In this way, only one hole is required in the casing 15 for the two tower shafts in order to connect the externally located accessory unit 12 with the low and high pressure shafts 10,11.
  • the gear set may be of a different type and/or design than the disclosed differential gear.
  • the differential gear may be replaced by a planetary gear.
  • a planetary gear may be of a design in which the ring gear is locked in order to activate the gear.
  • the planet carrier may form an input (and is rotationally rigidly connected to the intermediate power transmission shaft) while the sun gear forms an output.
  • the high pressure shaft 10 and the low pressure shaft 11 are counter-rotating.
  • the invention is however applicable also in gas turbines where the shafts rotate in the same direction.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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Abstract

The invention relates to a power transmission device (2) for a gas turbine engine comprising a low pressure shaft (11) and a high pressure shaft (10), wherein the high pressure shaft (10) is arranged concentric to the low pressure shaft (11). The device further comprises an accessory unit (12) comprising at least one electric machine (29, 30) adapted for a gas turbine engine starting operation and/or for generating electrical power. The device (2) further comprises a transmission unit (13) operatively connected to the low pressure shaft (11) and adapted for power transmission from the low pressure shaft (11) to the accessory unit (12). The transmission unit (13) is positioned non-concentric with the low pressure shaft (11). A first transmission means (18) is operatively connected for power transmission from the low pressure shaft (11) to the transmission unit (13), and a second transmission means (32) is operatively connected for power transmission from the accessory unit (12) to the high pressure shaft in a manner bypassing the transmission unit (13).

Description

A power transmission device for a gas turbine engine
FIELD OF THE INVENTION
The present invention relates to a power transmission device for a gas turbine engine comprising a low pressure shaft and a high pressure shaft, wherein the high pressure shaft is arranged concentric to the low pressure shaft. The power transmission device further comprises an accessory unit comprising at least one electric machine adapted for a gas turbine engine starting operation and/or for generating electrical power.
The invention also relates to a gas turbine engine comprising the power transmission device and an aeroplane comprising the gas turbine engine.
The low pressure shaft is adapted to drive a low pressure compressor or fan in the gas turbine engine and the high pressure shaft is adapted to drive a high pressure compressor in the gas turbine engine. The gas turbine engine may be a turbojet or turbofan engine.
The accessory unit comprises an accessory gearbox which is adapted to drive further ancillary services both of the turbine engines themselves and of the aeroplane for which they provide propulsion. Such aeroplane ancillary services comprises ancillary machines such as generators, fuel pumps, fuel flow governors, oil pumps, centrifugal breathers, etc. The need of electric power to be used for the operation of aeroplane services will most probably drastically increase in the future. Therefore, it will be necessary to extract more power from the turbine engines . However, the high pressure shaft that, by tradition, has been the shaft from which said power is extracted, will not be able to deliver all of said power alone, due to the fact that a large mechanical power extraction has a negative effect on the operation of the high pressure shaft as it is likely to cause pumping of the compressor, in particular when the engine is running at low speed.
Accordingly, the manufacturers of aeroplane engines are considering to use also the low pressure shaft for the purpose of transferring power to the accessory gearbox.
One problem with using the low pressure shaft to extract power is the low speed and large operational speed range, which does not match the requirements of the ancillary machines. Contemporary solutions for the extraction of power from the LP-shaft include an extra system of bevel gears and shafts.
PRIOR ART US 5,103,631 discloses a differential gear assembly suitable for providing power take off from a gas turbine engine, comprising first and second power input gears which drive a plurality of idler gears rotatably mounted on a common cage structure. The idler gears are grouped in meshing pairs so that one idler gear of each pair is additionally in meshing engagement with one of the power input gears and the other idler gear of each pair is additionally in meshing engagement with the other of the power input gears. Together the first and second power input gears drive the common cage structure at the mean speed of the power input gears and the common cage structure in turn drives a single power output shaft. Accordingly, US 5,103,631 discloses a device that uses a planetary gear for the purpose of retrieving power from both LP-shaft and HP-shaft and transfer it to an accessory gearbox. US 5,103,631 also discloses the possibility of providing a different division of torque split between the two power input shafts, by modifying the gear assembly so that one of the gears is of larger diameter than the other. It is also mentioned that any use of input gears which are not of the same diameter would necessitate the appropriate repositioning of the idler gears .
US patent application No. 2006/0034696 discloses a twin-spool turbojet engine with a differential with a first planetary pinion driven by the shaft of the high pressure spool, and a second planetary pinion driven by the shaft of the low pressure spool, said planetary pinions driving satellite pinions mounted in a cage by which the ancillary machines are driven. By means of a separate transmission, a step down gear mechanism, connected to the high pressure shaft upstream the differential as seen in the power drive train direction, the mechanical transmission ratio between the high pressure shaft and the first planetary pinion of the differential gear, and the transmission ratio between the low pressure shaft and the second planetary pinion of the differential gear are such that the power extraction distribution between the high pressure spool and the low pressure spool is appropriately distributed for the different operation conditions (rotational speeds) of the engine. The power extraction distribution between the high pressure spool and the low pressure spool at idle speed is between 80%/20% and 20%/80%.
SUMMARY OF THE INVENTION A primary purpose of the invention is to achieve a power transmission device for a gas turbine engine, which creates conditions for extracting a larger proportion of the power and preferably all power required by the ancillary machines from the low pressure shaft.
This purpose is achieved in that the power transmission device comprises a transmission unit operatively connected to the low pressure shaft and adapted for power transmission from the low pressure shaft to the accessory unit, that the transmission unit is positioned non-concentric with the low pressure shaft, that a first transmission means is operatively connected for power transmission from the low pressure shaft to the transmission unit, and that a second transmission means is operatively connected for power transmission from the accessory unit to the high pressure shaft in a manner bypassing the transmission unit.
The wording "bypassing" should be interpreted as functionally (or operationally) bypassing the transmission unit in that the transmission unit does not effect the power transmission path from the accessory unit to the high pressure shaft. Preferably, the second transmission means is configured so that the power transmission path in its entirety extends externally of the transmission unit. In other words, the second transmission means is arranged in parallel to the first transmission means and the transmission unit.
By virtue of arranging the first transmission means operatively connected to the low pressure shaft and the second transmission means operatively connected to the high pressure shaft, a starting operation may be performed using the high pressure shaft, while power off take may be performed from the low pressure shaft.
Further, the power transmission device creates conditions for a minimum of structural modification and additional parts of the gas turbine engine. More specifically, only one connection is required to the low pressure shaft and only one connection is required to the high pressure shaft.
Preferably, each of the first and second transmission means comprises a tower shaft extending out of a gas turbine engine housing, which houses the low pressure shaft and the high pressure shaft. In this way, the transmission unit may be located externally of the gas turbine engine housing, wherein service is facilitated.
According to a further preferred embodiment of the invention, the device comprises means for operatively connecting and disconnecting, respectively at least one of said electric machines adapted for the gas turbine engine starting operation to the high pressure shaft. In this way, the gas turbine engine may be started via the high pressure shaft. Preferably, the connection means is adapted to automatically disconnect said at least one of said electric machines from operational connection with the high pressure shaft when a speed of the high pressure shaft exceeds a predetermined limit value. Thus, the connection means is passive in the respect that no control means is required for its activation. This creates conditions for a reliable operation. Especially, the predetermined limit value corresponds to a maximum speed for a gas turbine engine starting operation.
According to a further preferred embodiment of the invention, the second transmission means is operatively connected for power transmission from at least one of said electric machines adapted for the gas turbine engine starting operation to the high pressure shaft and also for power transmission from the high pressure shaft to the accessory unit. Thus, the second transmission means is adapted for a two-way power transmission.
According to a further preferred embodiment of the invention, the transmission unit comprises a gear changing mechanism adapted to change between at least two gears for said power transmission from the low pressure shaft to the accessory unit. This is especially advantageous due to the large operational speed range of the low pressure shaft. Thus, this embodiment creates conditions for power transmission from the low speed shaft over substantially the complete operational speed range of the low pressure shaft.
The complete operational speed range of the low pressure shaft corresponds to a self-sustained operation of the gas turbine engine comprising idling, a medium and higher operational speed range. Further preferred embodiments will be apparent from the further claims, the following description and drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will be explained below, with reference to the embodiments shown on the appended drawings, wherein FIG 1 is a schematic illustration of a gas turbine engine in the form of an aircraft engine, FIG 2 is a schematic illustration of a first embodiment of a power transmission device for the gas turbine engine,
FIG 3 is a schematic illustration of a second embodiment of a power transmission device for the gas turbine engine,
FIG 4 and 5 show an example of a gear set in the power transmission device.
DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS OF THE INVENTION
Fig. 1 is an oversight view of a gas turbine engine 1 according to the invention provided with a power transmission device 2 according to the invention. The gas turbine engine 1 shown in fig. 1 is of conventional construction and comprises, in axial flow series, an air intake 3, low pressure compressor 4, high pressure compressor 5, combustion equipment 6, high pressure turbine 7, low pressure turbine 8 and an exhaust outlet 9. During operation, the high pressure compressor is driven by the high pressure turbine via a first hollow high pressure shaft 10. Similarly, the low pressure compressor is driven by the low pressure turbine via a second hollow low pressure shaft 11 which is coaxially disposed within the high pressure shaft 10.
The gas turbine 1 operates in the conventional manner whereby air drawn in through the air intake 3 is compressed by the low pressure compressor before passing into the high pressure compressor where it is compressed further. The compressed air then flows into the combustion equipment 6 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through the high and low pressure turbines 7, 8 before being exhausted to the atmosphere through the exhaust nozzle 9.
The power transmission device 2 comprises a transmission unit 13 (see figure 2) , which is adapted to transfer power from the low pressure shaft 11 to an accessory unit 12 during engine operation, said accessory unit 12 being located on the outside of the engine 1. The accessory unit 12 comprises an accessory gearbox 31 and is adapted to drive different ancillary machines, such as generators and oil or fuel hydraulic pumps . More specifically, the accessory unit 12 comprises at least one electric machine 29,30 adapted for a gas turbine engine starting operation and for generating electrical power. However, during start up of the engine 1, the power transfer direction is reversed, whereby power is transferred from a generator in the accessory unit 12 to the high pressure shaft 10. Once, by definition, the engine 1 has been started and power may be extracted from the low pressure shaft 11, the device according to the invention is set in an operation mode by which power is transferred from the low pressure shaft 11 to the accessory unit 12 through said transmission unit 13.
Figure 2 shows the power transmission device 2 according to a first embodiment. In the shown embodiment, the high pressure shaft 10 and the low pressure shaft 11 are counter-rotating. The transmission unit 13 is arranged externally of a gas turbine engine housing 15, which accommodates at least part of the low pressure shaft. The transmission unit 13 is operatively connected to the low pressure shaft 11 and adapted for power transmission from the low pressure shaft 11 to the accessory unit 12. The transmission unit 13 is configured for changing gears. More specifically, the transmission unit 13 is a step gear transmission. The transmission unit 13 comprises a gear changing mechanism 14 adapted to change between at least two gears for transmitting power from the low pressure shaft 11 to the accessory unit 12 over substantially the complete operational speed range of the low pressure shaft.
A first transmission means 18 is operatively connected for power transmission from the low pressure shaft 11 to the externally located accessory unit 12 via the externally located transmission unit 13. The first transmission means 18 comprises a first tower shaft 19. More specifically, the first tower shaft 19 is connected to the gear changing mechanism 14 in the transmission unit 13 and the low pressure shaft 11, respectively, via bevel gears 27,28.
A second transmission means 32 is operatively connected for power transmission from the accessory unit 12 to the high pressure shaft 10. The second transmission means 32 comprises a second tower shaft 38. The second tower shaft 38 is connected to the accessory unit 12 and the high pressure shaft 10, respectively, via bevel gears 34,35. The first and second transmission means 18,32 are arranged at a distance from each other in an axial direction 20 of the gas turbine engine 1. The tower shafts 19,38 extend substantially at right angles with the gas turbine rotational axis 20.
The accessory unit 12 is arranged externally of the gas turbine engine housing 15. Further, the tower shafts 19,38 extends through two separate holes in the casing 15 in order to connect the externally located accessory unit 12 with the low and high pressure shafts 10,11.
The device 2 further comprises means 16 for operatively connecting and disconnecting, respectively the accessory unit 12 to the high pressure shaft 10. The connection means 16 is adapted to automatically disconnect the accessory unit 12 from operational connection with the high pressure shaft 10 when a speed of the high pressure shaft exceeds a predetermined limit value, which corresponds to a maximum speed for a gas turbine engine starting operation. More specifically, according to the first embodiment, the connection means 16 comprises a clutch. The high pressure shaft clutch 16 is formed by a freewheel mechanism. The high pressure shaft clutch 16 is arranged externally of the housing 15 and preferably directly on an output shaft of the accessory unit 12, i.e upstream of the second tower shaft in the power transmission direction during a starting operation. The accessory unit 12 is operatively connected to the high pressure shaft 10 in a manner bypassing the transmission unit 13. The transmission unit 13 is adapted to transmit at least 50%, preferably at least 80% and especially 100% of the required power for the components/machines in the accessory unit 12 from the low pressure shaft 11 over substantially the complete operational speed range of the low pressure shaft.
In order to transmit all, or at least substantially all power to the accessory unit 12 from the low pressure shaft 11 over substantially the complete operational speed range of the low pressure shaft 11, the transmission unit 13 comprises a gear set 21 arranged between the low pressure shaft 11 and the accessory unit 12. The gear changing mechanism 14 is adapted for connecting and disconnecting, respectively, the gear set 21 from being drivingly connected to the accessory unit 12. More specifically, the transmission unit 13 comprises an intermediate power transmission shaft 17, which is drivingly connected between the bevel gear 27 and the accessory unit 12. The gear set 21 is in direct operational connection with the intermediate power transmission shaft 17. Further, the gear changing mechanism 14 is also in direct operational connection with the intermediate power transmission shaft 17.
The gear changing mechanism 14 comprises a clutch. Preferably, the clutch 14 is a one-way clutch in the form of a free-wheeling clutch.
In a low speed range, the gear changing mechanism 14 is disengaged from the low pressure shaft 11, wherein power is transmitted from the low pressure shaft 11 to the accessory unit 12 via the gear set 21. In a high speed range, the gear changing mechanism 14 is engaged, wherein power is transmitted from the low pressure shaft 11 to the accessory unit 12 via the tower shaft and the gear changing mechanism 14.
The gear set 21 is a differential gear in the form of an epicyclic gear, see fig. 4-5. Means 23 is arranged for activating the gear set 21. The activation means 23 comprises a clutch. 24, or brake, which is adapted to operationally connect an input gear member 101 to a stationary part 25, or wall, in the transmission unit. More specifically, the clutch is a multi-plate clutch. The clutch 24 is the only active means in the device 2 in the respect that it is the only means that is actively controlled during operation. Preferably, a stationary arranged hydraulic piston may be used for application of the clutch, wherein oil supply and drainage may be arranged easily and reliably. The differential gear member to be locked may be a sun gear in the differential gear 21.
The differential gear 21 comprises at least one pair of idler gears 102,103, see figure 4, which are arranged in meshing engagement with each other. A first idler gear 102 is in meshing engagement with the input gear member 101. A second idler gear 103 is in meshing engagement with an output gear member 104. The idler gears 102,103 are rotatably mounted in a differential gear casing 105. The differential gear casing 105 comprises means 106 for rotationalIy rigidly connecting the casing 105 to the intermediate power transmission shaft 17. Said connection means 106 comprises a plurality of circumferentialIy spaced radial drive spokes 106. The spokes 106 are arranged axialIy between the input gear member 101 and the output gear member 104.
The accessory unit 12 comprises two electric machines 29,30 adapted for a starting operation and for generating electrical power. These electric machines 29,30 are in the following referred to as a Starter/Generator, or S/G.
In a starting operation, one or both S/G 29,30 is controlled to drive the high pressure shaft 10 via the free-wheeling clutch 16. The low pressure , shaft 11 is however not driven since the clutch 24 for the gear set 21 is not activated and the clutch 14 is free-wheeling. When the high pressure shaft 10 is accelerated to a predetermined speed limit value (a maximum speed for the starting operation) , the high pressure shaft clutch 16 will automatically disconnect from a driving connection and freewheel.
During idling, the S/G is switched to an electric power generating state, the gear set 21 is activated via the clutch 24 and the one-way clutch 14 is free-wheeling.
In a medium operational speed range, the multi-plate clutch 24 is released in a manner with controlled slip, wherein the low pressure shaft 11 drives the accessory unit 12 via the intermediate shaft 17 and the clutch 14. This operation is continued in a higher operational speed range (comprising a maximum speed) .
When the speed of the low pressure shaft is reduced to a predetermined limit value, the multi-plate clutch 24 is actuated in a manner with controlled slip, the one-way- clutch 14 is automatically released and will freewheel, wherein the low pressure shaft 11 drives the accessory unit 12 via the intermediate shaft 17 and the gear set 21.
The invention is not in any way limited to the above described embodiments, instead a number of alternatives and modifications are possible without departing from the scope of the following claims .
According to an alternative embodiment, the first and second transmission means 18,32 may be arranged in a coaxial (concentric) relationship. More precisely, the first tower shaft 19 may be arranged concentric to the second tower shaft 38. In this way, only one hole is required in the casing 15 for the two tower shafts in order to connect the externally located accessory unit 12 with the low and high pressure shafts 10,11.
According to a further alternative embodiment, the gear set may be of a different type and/or design than the disclosed differential gear. For example, the differential gear may be replaced by a planetary gear. Such a planetary gear may be of a design in which the ring gear is locked in order to activate the gear. Further, the planet carrier may form an input (and is rotationally rigidly connected to the intermediate power transmission shaft) while the sun gear forms an output.
In the shown embodiment, the high pressure shaft 10 and the low pressure shaft 11 are counter-rotating. The invention is however applicable also in gas turbines where the shafts rotate in the same direction.

Claims

1. A power transmission device (2) for a gas turbine engine (1) comprising a low pressure shaft (11), a high pressure shaft (10) , wherein the high pressure shaft (10) is arranged concentric to the low pressure shaft (11) , and an accessory unit
(12) comprising at least one electric machine (29,30) adapted for a gas turbine engine starting operation and/or for generating electrical power, characterized in that the power transmission device (2) comprises a transmission unit (13) operatively connected to the low pressure shaft (11) and adapted for power transmission from the low pressure shaft (11) to the accessory unit
(12), that the transmission unit (13) is positioned non-concentric with the low pressure shaft (11) , that a first transmission means (18) is operatively connected for power transmission from the low pressure shaft (11) to the transmission unit (13), and that a second transmission means (32) is operatively connected for power transmission from the accessory unit (12) to the high pressure shaft in a manner bypassing the transmission unit (13) .
2. A power transmission device according to claim 1 or 2, characterized in that the transmission unit (13) is arranged externally of a gas turbine engine housing (15) , which accommodates at least part of the low pressure shaft (11) .
3. A power transmission device according to claim 1 or 2, characterized in that the first transmission means (18) comprises a first tower shaft (19) .
4. A gas turbine engine according to any preceding claim, characterized in that the second transmission means (32) comprises a second tower shaft (38) .
5. A power transmission device according to any preceding claim, characterized in that it comprises means (16) for operatively connecting and disconnecting, respectively at least one of said electric machines (29,30) adapted for the gas turbine engine starting operation to the high pressure shaft (10) .
6. A power transmission device according to claim 5, characterized in that the connection means (16) is adapted to automatically disconnect said at least one electric machine (29,30) from operational connection with the high pressure shaft (10) when a speed of the high pressure shaft exceeds a predetermined limit value.
7. A power transmission device according to claim 6, characterized in that the predetermined limit value corresponds to a maximum speed for a gas turbine engine starting operation.
8. A power transmission device according to any one of claims 5-7, characterized in that the connection means (16) comprises a clutch.
9. A power transmission device according to claim 8, characterized in that the high pressure shaft clutch (16) is formed by a freewheel mechanism.
10. A power transmission device according to any one of claims 5-9, characterized in that the connection means (16) is arranged non-concentric with the high pressure shaft (10) .
11. A power transmission device according to any one of claims 5-10, characterized in that the connection means (16) is arranged externally of a gas turbine engine housing (15) , which accommodates at least part of the high pressure shaft (10) .
12. A power transmission device according to any one of claims 5-11, characterized in that accessory unit (12) comprises the connection means (16) .
13. A power transmission device according to any preceding claim, characterized in that the second transmission means (32) is operatively connected for power transmission from at least one of said electric machines (29,30) adapted for the gas turbine engine starting operation to the high pressure shaft (10) and also for power transmission from the high pressure shaft (10) to the accessory unit (12) .
14. A power transmission device according to one of claims 5-12 and claim 13, characterized in that at least one power consumer (33,36) in the accessory unit (12) is arranged between the connection means (16) and the high pressure shaft (10) in the power transmission path between said electric machine (29,30) adapted for the gas turbine engine starting operation and the high pressure shaft (10) .
15. A power transmission device according to any preceding claim, characterized in that the accessory unit (12) is arranged externally of a gas turbine engine housing (15) , which accommodates at least part of the high pressure shaft (10) .
16. A power transmission device according to any preceding claim, characterized in that the transmission unit (13) is adapted to transmit at least 50% of the required power for the power consumers in the accessory unit from the low pressure shaft (11) .
17. A power transmission device according to any preceding claim, characterized in that the transmission unit (13) comprises a gear changing mechanism (14) adapted to change between at least two gears for said power transmission from the low pressure shaft (11) to the accessory unit (12) .
18. A power transmission device according to claim 17, characterized in that the transmission unit (12) comprises a gear set (21) and that the gear changing mechanism (14) is adapted for connecting and disconnecting, respectively, the gear set (21) from being drivingly connected to the accessory unit (12) .
19. A power transmission device according to claim 18, characterized in that the gear set (21) is arranged on an intermediate power transmission shaft (17) in the transmission unit (13), and that the gear changing mechanism (14) is arranged in direct contact with the intermediate power transmission shaft (17) .
20. A power transmission device according to claim 18 or 19, characterized in that the gear changing mechanism (14) comprises a clutch.
21. A power transmission device according to any one of claims 18-20, characterized in that the gear set (21) is a differential gear.
22. A gas turbine engine (1), characterized in that it comprises a power transmission device (2) according to any preceding claim.
23. An aeroplane characterized in that it comprises a gas turbine engine (1) according to claim 22.
PCT/SE2006/001517 2006-12-29 2006-12-29 A power transmission device for a gas turbine engine WO2008082335A1 (en)

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Cited By (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010067172A2 (en) * 2008-12-12 2010-06-17 Norbert Bayer Apparatus and method for energy recovery on jet-powered airplanes on approach for landing
WO2011007078A1 (en) * 2009-07-17 2011-01-20 Snecma Method and system for controlling aircraft engine starter/generator
US8492920B2 (en) 2011-10-07 2013-07-23 Ge Aviation Systems Llc Apparatus for generating power from a turbine engine
EP2659111A1 (en) * 2010-12-30 2013-11-06 Rolls-Royce Corporation System, propulsion system and vehicle
US8723385B2 (en) 2011-10-07 2014-05-13 General Electric Company Generator
US8866334B2 (en) 2010-03-02 2014-10-21 Icr Turbine Engine Corporation Dispatchable power from a renewable energy facility
EP2452879A3 (en) * 2010-11-16 2014-12-24 Rolls-Royce Corporation Aircraft and propulsion system
US8984895B2 (en) 2010-07-09 2015-03-24 Icr Turbine Engine Corporation Metallic ceramic spool for a gas turbine engine
US9051873B2 (en) 2011-05-20 2015-06-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine shaft attachment
EP2320067A3 (en) * 2009-11-04 2016-03-30 Kawasaki Jukogyo Kabushiki Kaisha Aircraft starter generator
EP2644866A3 (en) * 2012-03-26 2017-04-05 Hamilton Sundstrand Corporation Multi-shaft power extraction from gas turbine engine
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EP3354881A1 (en) * 2017-01-19 2018-08-01 United Technologies Corporation Gas turbine engine dual towershaft accessory gearbox and starter generator assembly
US10094288B2 (en) 2012-07-24 2018-10-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine volute attachment for a gas turbine engine
US10100739B2 (en) 2015-05-18 2018-10-16 United Technologies Corporation Cooled cooling air system for a gas turbine engine
US10221862B2 (en) 2015-04-24 2019-03-05 United Technologies Corporation Intercooled cooling air tapped from plural locations
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US10443508B2 (en) 2015-12-14 2019-10-15 United Technologies Corporation Intercooled cooling air with auxiliary compressor control
US10480419B2 (en) 2015-04-24 2019-11-19 United Technologies Corporation Intercooled cooling air with plural heat exchangers
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US10577964B2 (en) 2017-03-31 2020-03-03 United Technologies Corporation Cooled cooling air for blade air seal through outer chamber
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US10590852B2 (en) 2017-01-19 2020-03-17 United Technologies Corporation Gas turbine engine dual towershaft accessory gearbox assembly with a transmission
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WO2020105085A1 (en) * 2018-11-19 2020-05-28 川崎重工業株式会社 Power generation device for aircraft
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US10830148B2 (en) 2015-04-24 2020-11-10 Raytheon Technologies Corporation Intercooled cooling air with dual pass heat exchanger
US10830145B2 (en) 2018-04-19 2020-11-10 Raytheon Technologies Corporation Intercooled cooling air fleet management system
EP3736422A1 (en) * 2019-05-06 2020-11-11 The Boeing Company Systems and methods for transferring mechanical power in a turbine engine
US10961911B2 (en) 2017-01-17 2021-03-30 Raytheon Technologies Corporation Injection cooled cooling air system for a gas turbine engine
US11255268B2 (en) 2018-07-31 2022-02-22 Raytheon Technologies Corporation Intercooled cooling air with selective pressure dump
EP4215737A1 (en) * 2018-09-11 2023-07-26 Raytheon Technologies Corporation Dual spool power extraction with superposition gearbox
WO2023209291A1 (en) * 2022-04-28 2023-11-02 Safran Aircraft Engines Accessory gearbox and aircraft turbine engine comprising such a box
US11808210B2 (en) 2015-02-12 2023-11-07 Rtx Corporation Intercooled cooling air with heat exchanger packaging

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050183540A1 (en) * 2004-02-25 2005-08-25 Miller Guy W. Apparatus for driving an accessory gearbox in a gas turbine engine
US20060010875A1 (en) * 2004-07-16 2006-01-19 Mahoney Timothy D Gas turbine engine bleed air power assist system and method
US20060272313A1 (en) * 2005-06-07 2006-12-07 Honeywell International, Inc. More electric aircraft power transfer systems and methods
US20070151258A1 (en) * 2005-12-30 2007-07-05 Honeywell International, Inc. More electric aircraft starter-generator multi-speed transmission system

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050183540A1 (en) * 2004-02-25 2005-08-25 Miller Guy W. Apparatus for driving an accessory gearbox in a gas turbine engine
US20060010875A1 (en) * 2004-07-16 2006-01-19 Mahoney Timothy D Gas turbine engine bleed air power assist system and method
US20060272313A1 (en) * 2005-06-07 2006-12-07 Honeywell International, Inc. More electric aircraft power transfer systems and methods
US20070151258A1 (en) * 2005-12-30 2007-07-05 Honeywell International, Inc. More electric aircraft starter-generator multi-speed transmission system

Cited By (73)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010067172A3 (en) * 2008-12-12 2011-01-13 Norbert Bayer Apparatus and method for energy recovery on jet-powered airplanes on approach for landing
WO2010067172A2 (en) * 2008-12-12 2010-06-17 Norbert Bayer Apparatus and method for energy recovery on jet-powered airplanes on approach for landing
WO2011007078A1 (en) * 2009-07-17 2011-01-20 Snecma Method and system for controlling aircraft engine starter/generator
FR2948151A1 (en) * 2009-07-17 2011-01-21 Snecma METHOD AND SYSTEM FOR CONTROLLING AN AIRCRAFT ENGINE STARTER-GENERATOR
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US8979705B2 (en) 2009-07-17 2015-03-17 Snecma Method and system for controlling aircraft engine starter/generator
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US8866334B2 (en) 2010-03-02 2014-10-21 Icr Turbine Engine Corporation Dispatchable power from a renewable energy facility
US8984895B2 (en) 2010-07-09 2015-03-24 Icr Turbine Engine Corporation Metallic ceramic spool for a gas turbine engine
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US8955335B2 (en) 2010-12-30 2015-02-17 Rolls-Royce Corporation System, propulsion system and vehicle
US10094235B2 (en) 2010-12-30 2018-10-09 Rolls-Royce Corporation System, propulsion system and vehicle
US9051873B2 (en) 2011-05-20 2015-06-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine shaft attachment
US8723349B2 (en) 2011-10-07 2014-05-13 General Electric Company Apparatus for generating power from a turbine engine
US8723385B2 (en) 2011-10-07 2014-05-13 General Electric Company Generator
US8492920B2 (en) 2011-10-07 2013-07-23 Ge Aviation Systems Llc Apparatus for generating power from a turbine engine
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US10094288B2 (en) 2012-07-24 2018-10-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine volute attachment for a gas turbine engine
US11808210B2 (en) 2015-02-12 2023-11-07 Rtx Corporation Intercooled cooling air with heat exchanger packaging
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EP4215737A1 (en) * 2018-09-11 2023-07-26 Raytheon Technologies Corporation Dual spool power extraction with superposition gearbox
EP3628847A1 (en) * 2018-09-28 2020-04-01 United Technologies Corporation Low torque engine starting with dual spool power extraction with superposition gearbox
US10890115B2 (en) 2018-09-28 2021-01-12 Raytheon Technologies Corporation Low torque engine starting with dual spool power extraction with superposition gearbox
EP4177449A1 (en) * 2018-10-11 2023-05-10 Raytheon Technologies Corporation Accessory gearbox with superposition gearbox
EP3636898A1 (en) * 2018-10-11 2020-04-15 United Technologies Corporation Accessory gearbox with superposition gearbox
US10634064B1 (en) 2018-10-11 2020-04-28 United Technologies Corporation Accessory gearbox with superposition gearbox
EP3885564A4 (en) * 2018-11-19 2022-07-06 Kawasaki Jukogyo Kabushiki Kaisha Power generation device for aircraft
JP7220233B2 (en) 2018-11-19 2023-02-09 川崎重工業株式会社 generator for aircraft
JPWO2020105085A1 (en) * 2018-11-19 2021-11-11 川崎重工業株式会社 Power generator for aircraft
WO2020105085A1 (en) * 2018-11-19 2020-05-28 川崎重工業株式会社 Power generation device for aircraft
US11333077B2 (en) 2019-05-06 2022-05-17 The Boeing Company Systems and methods for transferring mechanical power in a turbine engine
EP3736422A1 (en) * 2019-05-06 2020-11-11 The Boeing Company Systems and methods for transferring mechanical power in a turbine engine
WO2023209291A1 (en) * 2022-04-28 2023-11-02 Safran Aircraft Engines Accessory gearbox and aircraft turbine engine comprising such a box
FR3135113A1 (en) * 2022-04-28 2023-11-03 Safran Aircraft Engines Accessory relay box and aircraft turbomachine comprising such a box

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