Drive shaft for remote variable vane actuation
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-017/16
F01D-017/14
F01D-009/04
F01D-017/12
F01D-025/34
F04D-029/56
출원번호
US-0079409
(2016-03-24)
등록번호
US-10190599
(2019-01-29)
발명자
/ 주소
Suciu, Gabriel L
Chandler, Jesse M
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Bachman & LaPointe, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
80
초록▼
A gas turbine engine includes an actuator, a harmonic drive driven by the actuator, an engine case containing a multiple of variable vanes, a firewall transverse to the engine case, a first temperature on one side of the firewall and a second temperature on the other side of the firewall, the first
A gas turbine engine includes an actuator, a harmonic drive driven by the actuator, an engine case containing a multiple of variable vanes, a firewall transverse to the engine case, a first temperature on one side of the firewall and a second temperature on the other side of the firewall, the first temperature different than the second temperature and a drive shaft driven by the harmonic drive, the drive shaft extends through the firewall to operate the multiple of variable vanes.
대표청구항▼
1. A gas turbine engine, comprising: an actuator;a harmonic drive driven by the actuator;an engine case containing a multiple of variable vanes;a firewall transverse to the engine case; anda drive shaft driven by the harmonic drive at a single input, the drive shaft extends through the firewall to d
1. A gas turbine engine, comprising: an actuator;a harmonic drive driven by the actuator;an engine case containing a multiple of variable vanes;a firewall transverse to the engine case; anda drive shaft driven by the harmonic drive at a single input, the drive shaft extends through the firewall to drive a multiple of outputs, each of the multiple of outputs operable to drive one stage of the multiple of variable vanes. 2. The gas turbine engine as recited in claim 1, further comprising a multiple of unison rings, each unison ring to drive a respective stage of the multiple of variable vanes, each unison ring driven by the drive shaft. 3. The gas turbine engine as recited in claim 1, wherein the harmonic drive includes a strain wave gearing mechanism. 4. The gas turbine engine as recited in claim 3, wherein the strain wave gearing mechanism includes a fixed circular spline, a flex spline attached to an output shaft, and a wave generator attached to an input shaft, the flex spline driven by the wave generator with respect to the circular spline. 5. The gas turbine engine as recited in claim 1, wherein the harmonic drive provides between a 30:1-320:1 gear ratio. 6. The gas turbine engine as recited in claim 1, wherein the actuator is an electric motor. 7. The gas turbine engine as recited in claim 1, wherein the multiple of variable vanes are within a compressor section of the gas turbine engine. 8. The gas turbine engine as recited in claim 1, wherein each of the multiple of outputs comprise a gear. 9. The gas turbine engine as recited in claim 1, wherein the drive shaft extends through the firewall parallel to an engine axis. 10. The gas turbine engine as recited in claim 1, wherein each of the multiple of outputs comprise a link. 11. The gas turbine engine as recited in claim 10, wherein each of the multiple of links are mounted to a respective bridge that is mounted to a respective unison ring, each of the multiple of links provide a relationship between vane rotation angles for each stage wherein an output differs for at least one of the stages. 12. A gas turbine engine, comprising: an actuator;a harmonic drive driven by the actuator, the harmonic drive comprising a fixed circular spline, a flex spline attached to an output shaft, and a wave generator attached to an input shaft, the flex spline driven by the wave generator with respect to the circular spline;an engine case containing a multiple of variable vanes;a firewall transverse to the engine case; anda drive shaft driven by the harmonic drive at a single input, the drive shaft extends through the firewall parallel to an engine axis to drive a multiple of outputs, each of the multiple of outputs operable to drive one stage of the multiple of variable vanes. 13. The gas turbine engine as recited in claim 12, wherein each of the multiple of outputs comprise a gear. 14. The gas turbine engine as recited in claim 13, wherein each of the multiple of gears drive a variable vane actuation arm that is mounted to a bridge mounted to a respective unison ring. 15. The gas turbine engine as recited in claim 12, wherein each of the multiple of outputs comprise a link. 16. The gas turbine engine as recited in claim 15, wherein each of the multiple of links are mounted to a respective bridge that is mounted to a respective unison ring. 17. The gas turbine engine as recited in claim 16, wherein each of the multiple of links provide a linear relationship between vane rotation angles across all stages. 18. The gas turbine engine as recited in claim 16, wherein each of the multiple of links provide a non-linear relationship between vane rotation angles across all stages. 19. The gas turbine engine as recited in claim 18, wherein each of the multiple of links provide a relationship between the vane rotation angles for each stage wherein the non-linear relationship is defined by an initial angle and a link length. 20. The gas turbine engine as recited in claim 19, wherein each of the multiple of links provide a relationship between the vane rotation angles for each stage wherein an output differs for each stage.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (80)
Agrawal, Rajendra K.; Reinhardt, Gregory E., Actuation mechanism for a convertible gas turbine propulsion system.
Karpman, Boris; Meisner, Richard P.; Lacour, Mark E., Control of engineering systems utilizing component-level dynamic mathematical model with single-input single-output estimator.
Karpman, Boris; Meisner, Richard P.; Lacour, Mark E., Design and control of engineering systems utilizing component-level dynamic mathematical model with multiple-input multiple-output estimator.
Debeneix,Pierre; Langlois,Arnaud; Boston,Erick; Leman,Alain; Garnier,Vincent; Audet,Jacques, Device for pivotally guiding variable-pitch vanes in a turbomachine.
McCaffrey, Michael G; Magge, Shankar S; Wagner, Joel H; Sabatino, Daniel R; Burge, Joseph Clayton, Gas turbine engine systems involving mechanically alterable vane throat areas.
Karpman, Boris; Meisner, Richard P.; Shade, John L., High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control.
Major, Daniel W.; Ditomasso, John C.; Champion, Nathan F., Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine.
Major, Daniel W.; Ditomasso, John C.; Champion, Nathan F., Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine.
Pekari Frederick J. (Trunbull CT) Johnson Robert E. (Stepney CT), Integrated multiplane actuator system for compressor variable vanes and air bleed valve.
Merry, Brian D.; Suciu, Gabriel L.; Brilliant, Lisa I.; Rose, Becky E.; Dong, Yuan; Balamucki, Stanley J., LPC flowpath shape with gas turbine engine shaft bearing configuration.
Karpman, Boris; Meisner, Richard P.; Lacour, Mark E., System and method for design and control of engineering systems utilizing component-level dynamic mathematical model.
Agrawal, Rajendra K.; Rajamani, Ravi; Schneider, William F.; Wood, Coy Bruce, System and method of assessing thermal energy levels of a gas turbine engine component.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.