IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0469712
(2012-05-11)
|
등록번호 |
US-8956108
(2015-02-17)
|
발명자
/ 주소 |
- Eleftheriou, Andreas
- Menheere, David
|
출원인 / 주소 |
- Pratt & Whitney Canada Corp
|
대리인 / 주소 |
Norton Rose Fulbright Canada
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
11 |
초록
▼
An assembly for a gas turbine engine, with a gearbox including a first portion having a first input gear coupled to a rotatable turbine shaft, a first output gear, and defining a first transmission path between the first input and output gears, and a second portion having a second input gear coupled
An assembly for a gas turbine engine, with a gearbox including a first portion having a first input gear coupled to a rotatable turbine shaft, a first output gear, and defining a first transmission path between the first input and output gears, and a second portion having a second input gear coupled to the turbine shaft, a second output gear, and defining a second transmission path between the second input and output gears different from the first transmission path. A fan rotor is coupled to the first output gear and a booster rotor is coupled to the second output gear on a same side of the gearbox than the coupling between the fan rotor and the first output gear. A method of assembling a drive for a fan rotor and a booster rotor in a gas turbine engine is also disclosed.
대표청구항
▼
1. An assembly for a gas turbine engine, the assembly comprising: a gearbox including: a first portion having a first input gear coupled to a rotatable turbine shaft, a first output gear, and defining a first transmission path between the first input and output gears, anda second portion having a se
1. An assembly for a gas turbine engine, the assembly comprising: a gearbox including: a first portion having a first input gear coupled to a rotatable turbine shaft, a first output gear, and defining a first transmission path between the first input and output gears, anda second portion having a second input gear coupled to the rotatable turbine shaft, a second output gear, and defining a second transmission path between the second input and output gears different from the first transmission path;a fan rotor coupled to the first output gear; anda booster rotor coupled to the second output gear on a same side of the gearbox than the coupling between the fan rotor and the first output gear. 2. The assembly as defined in claim 1, wherein the first input gear is a sun gear, the first output gear is a ring gear, and the first transmission path is defined by a plurality of planet gears meshed with the sun and ring gears and retained by a fixed carrier. 3. The assembly as defined in claim 1, wherein the second input gear is an input face gear, the second output gear is an output face gear, and the second transmission path is defined by a plurality of circumferentially spaced pinions meshed with the input and output face gears and retained by a fixed support structure. 4. The assembly as defined in claim 3, wherein each pinion has a first diameter portion meshed with the input face gear and a second diameter portion meshed with the output face gear. 5. The assembly as defined in claim 1, wherein the second input gear is an input bevel gear, the second output gear is an output bevel gear, and the second transmission path is defined by a plurality of circumferentially spaced bevelled pinions meshed with the input and output bevel gears and retained by a fixed support structure. 6. The assembly as defined in claim 1, wherein the booster rotor is a mixed flow rotor. 7. The assembly as defined in claim 1, wherein bearings supporting the booster rotor, the fan rotor and an adjacent end of the turbine shaft are located in a same oil cavity as the gearbox. 8. The assembly as defined in claim 1, wherein the first and second transmission paths respectively define first and second transmission ratios determining a rotational speed of the second output gear which is greater than that of the first output gear. 9. The assembly as defined in claim 8, wherein the first transmission ratio has a value from 1.8:1 to 2.4:1 and the second transmission ratio has a value from 1:1 to 1:1.8. 10. The assembly as defined in claim 1, wherein the first input gear is a sun gear, the first output gear is a ring gear, the first transmission path is defined by a plurality of planet gears meshed with the sun and ring gears and retained by a fixed carrier, and the second transmission path is defined by a plurality of circumferentially spaced pinions meshed with the second input gear and with the second output gears and retained by a fixed support structure, the second output gear being annular and surrounding at least part of the first output gear. 11. A gas turbine engine comprising: a core turbine engine;a low pressure turbine rotor located downstream of the core turbine engine and in fluid communication therewith;a rotatable low pressure shaft drivingly engaged to the low pressure turbine rotor;a gearbox including: a first portion having a first input gear coupled to the low pressure shaft, a first output gear, and defining a first transmission path between the first input and output gears, anda second portion having a second input gear coupled to the low pressure shaft, a second output gear, and defining a second transmission path between the second input and output gears different from the first transmission path;a fan rotor upstream of the core engine and coupled to the first output gear; anda booster rotor between the fan rotor and the core engine and coupled to the second output gear on a same side of the gearbox than the coupling between the fan rotor and the first output gear. 12. The engine as defined in claim 11, wherein the first portion includes a planetary gear system. 13. The engine as defined in claim 11, wherein the second transmission path is defined by a plurality of circumferentially spaced pinions meshed with the second input gear and with the second output gear and retained by a fixed support structure. 14. The engine as defined in claim 13, wherein each pinion has a first diameter portion meshed with the input face gear and a second diameter portion meshed with the output face gear. 15. The engine as defined in claim 11, wherein the booster rotor is a mixed flow rotor. 16. The engine as defined in claim 11, wherein the first and second transmission paths respectively define first and second transmission ratios, the first transmission ratio having a value from 1.8:1 to 2.4:1 and the second transmission ratio having a value from 1:1 to 1:1.8. 17. The engine as defined in claim 11, wherein the first portion includes a planetary gear system, the second transmission path is defined by a plurality of circumferentially spaced pinions meshed with the second input gear and with the second output gears and retained by a fixed support structure, and the second output gear is annular and surrounds at least part of the first output gear. 18. The engine as defined in claim 11, wherein the gearbox and bearings supporting the booster rotor, the fan rotor and an adjacent end of the low pressure shaft are located in a same oil cavity. 19. A method of assembling a drive for a fan rotor and a booster rotor in a gas turbine engine, the method comprising: connecting two input gears with a low pressure shaft of the gas turbine engine;defining independent transmission path between each of the input gears and a respective one of two output gears of a same gearbox;connecting the fan rotor with one of the output gears on one side of the gearbox; andconnecting the booster rotor with the other of the output gears on the one side of the gearbox. 20. The method as defined in claim 19, further comprising inserting the gearbox in a same oil cavity containing bearings supporting the low pressure shaft, the fan rotor and the booster rotor.
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