IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0505519
(2006-08-17)
|
등록번호 |
US-7762085
(2010-08-13)
|
발명자
/ 주소 |
- Exley, John T.
- Minkkinen, George
- Hulbert, Donald
- Rudy, Michael D.
|
출원인 / 주소 |
- Teledyne Technologies Incorporated
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
10 |
초록
▼
A turbine engine particularly suited for VTOL aircraft is disclosed. According to various embodiments, the core of the turbine engine includes two spools—a low pressure (LP) spool and a high pressure (HP) spool—where the LP spool is independently mounted remote to the HP spool. The eng
A turbine engine particularly suited for VTOL aircraft is disclosed. According to various embodiments, the core of the turbine engine includes two spools—a low pressure (LP) spool and a high pressure (HP) spool—where the LP spool is independently mounted remote to the HP spool. The engine may be modulated for operation by a modulation diverter valve assembly and through the fuel flow to the engine. The power output from the engine can be modulated from high levels to low levels and vice versa through control of the air flow through the engine using the modulation diverter valve assembly. In lift mode operation both the LP and HP spools may be operational, while during the forward flight cruise mode of operation the HP spool is operational and the LP spool may or may not be operational depending upon the power required for the flight condition. For HP spool only operation, the LP spool may be shut down using the modulation diverter valve assembly and an inlet flow diverter valve assembly. The convertible configuration may be achieved by the diverter valving-enabled modulation of the engine airflow direction to produce a characteristic for one embodiment having shaft power output for the vertical lift mode to propulsive thrust output for forward flight mode.
대표청구항
▼
What is claimed is: 1. A turbine engine comprising: a low-pressure spool assembly comprising a low-pressure turbine stage and a high-power turbine stage; a high-pressure spool assembly comprising a high-pressure turbine stage and a low-power turbine stage, wherein the low-pressure spool assembly an
What is claimed is: 1. A turbine engine comprising: a low-pressure spool assembly comprising a low-pressure turbine stage and a high-power turbine stage; a high-pressure spool assembly comprising a high-pressure turbine stage and a low-power turbine stage, wherein the low-pressure spool assembly and the high-pressure spool assembly are oriented along different axes; and a modulation diverter valve assembly for modulating combusted gas flow from the high-pressure turbine stage of the high-pressure spool assembly to the high-power turbine stage of the low-pressure spool assembly and low-power turbine stage of the high-pressure spool assembly based on a mode of operation of the turbine engine. 2. The turbine engine of claim 1, wherein the low-pressure spool assembly comprises a low-pressure compressor and the high-pressure spool assembly comprises a high pressure compressor, and wherein the turbine engine further comprises a flow diverter valve assembly for directing inlet air flow to the low-pressure compressor and the high pressure compressor based on the mode of operation of the turbine engine. 3. The turbine engine of claim 2, wherein: in a first mode of operation, the modulation diverter valve assembly is for directing combusted gas flow to the high-power turbine stage; in a second mode of operation, the modulation diverter valve assembly is for directing combusted gas flow to the low-power turbine stage; and in a third mode of operation, the modulation diverter valve assembly is for directing combusted gas flow to both the low-power turbine stage and the high-power turbine stage. 4. The turbine engine of claim 3, wherein: in the first mode of operation, the flow diverter valve assembly is for directing inlet air to the low-pressure compressor of the low-pressure spool assembly; and in the second mode of operation, the modulation diverter valve assembly is for directing all of the combusted gas to the high-power turbine stage and the flow diverter valve assembly is for closing off air flow to the low-pressure compressor. 5. The turbine engine of claim 4, wherein the modulation diverter valve assembly, when the engine transitions from the first mode to the second mode of operation, is for reducing the gas flow to the high-power turbine stage so that eventually all of the gas flow is directed to the low-power turbine stage. 6. The turbine engine of claim 5, wherein the modulation diverter valve assembly comprises one valve with bi-channel flow diversion. 7. The turbine engine of claim 5, wherein the modulation diverter valve assembly comprises at least two valves. 8. The turbine engine of claim 1, wherein the modulation diverter valve assembly comprises one valve with bi-channel flow diversion. 9. The turbine engine of claim 1, wherein the modulation diverter valve assembly comprises at least two valves. 10. The turbine engine of claim 7, wherein the flow diverter valve assembly comprises at least two valves. 11. The turbine engine of claim 1, wherein the low-pressure spool assembly is oriented non-concentric to the high-pressure spool assembly. 12. The turbine engine of claim 5, wherein the low-pressure spool assembly is oriented non-concentric to the high-pressure spool assembly. 13. The turbine engine of claim 5, further comprising a cruise propulsor coupled to the high-pressure spool assembly. 14. The turbine engine of claim 13, wherein the cruise propulsor is mechanically coupled to the high-pressure spool assembly. 15. The turbine engine of claim 13, wherein the cruise propulsor is aerodynamically coupled to the high-pressure spool assembly. 16. The turbine engine of claim 13, wherein the cruise propulsor comprises at least one of a cruise fan, a propfan or a propeller. 17. The turbine engine of claim 15, further comprising: a scroll duct for ducting air from the low-pressure compressor to the high-pressure compressor; and an intercooler in the scroll duct for introducing fuel. 18. A craft comprising a turbine engine, wherein the turbine engine comprises: a low-pressure spool assembly comprising a low-pressure turbine stage and a high-power turbine stage; a high-pressure spool assembly comprising a high-pressure turbine stage and a low-power turbine stage, wherein the low-pressure spool assembly and the high-pressure spool assembly are oriented along different axes; and a modulation diverter valve assembly for modulating combusted gas flow from the high-pressure turbine stage of the high-pressure spool assembly to the high-power turbine stage of the low-pressure spool assembly and low-power turbine stage of the high-pressure spool assembly based on a mode of operation of the turbine engine. 19. The craft of claim 18, wherein the low-pressure spool assembly comprises a low-pressure compressor and the high-pressure spool assembly comprises a high pressure compressor, and further comprising a flow diverter valve assembly for directing inlet air flow to the low-pressure compressor and the high pressure compressor based on the mode of operation of the turbine engine. 20. The craft of claim 19, wherein the high-pressure spool assembly comprises a freely mounted low-power turbine assembly. 21. The craft of claim 19, wherein: in a first mode of operation, the modulation diverter valve assembly is for directing combusted gas flow to the high-power turbine stage; in a second mode of operation, the modulation diverter valve assembly is for directing combusted gas flow to the low-power turbine stage; and in a third mode of operation, the modulation diverter valve assembly is for directing combusted gas flow to both the low-power turbine stage and the high-power turbine stage. 22. The craft of claim 21, wherein: in the first mode of operation, the flow diverter valve assembly is for directing inlet air to the low-pressure compressor of the low-pressure spool assembly; and in the second mode of operation, the modulation diverter valve assembly is for directing all of the combusted gas to the high-power turbine stage and the flow diverter valve assembly is for closing off air flow to the low-pressure compressor. 23. The craft of claim 22, wherein modulation diverter valve assembly, when the engine transitions from the first mode to the second mode of operation, is for reducing the gas flow to the high-power turbine stage so that eventually all of the gas flow is directed to the low-power turbine stage. 24. The craft of claim 18, wherein the craft comprises a VTOL aircraft. 25. The craft of claim 18, wherein the craft is selected from the group consisting of an aircraft, a ground vehicle, and a ship. 26. A turbine engine comprising: a low-pressure spool assembly comprising a low-pressure compressor, a low-pressure turbine stage, and a high-power turbine stage; a high-pressure spool assembly comprising a high-pressure compressor, a combustor, a high-pressure turbine stage, and a low-power turbine stage, wherein the low-pressure spool assembly and the high-pressure spool assembly are oriented along different axes; a modulation diverter valve assembly for modulating combusted gas flow from an exit of the high-pressure turbine stage of the high-pressure spool assembly to the high-power turbine stage of the low-pressure spool assembly and the low-power turbine stage of the high-pressure spool assembly based on a mode of operation of the turbine engine, wherein, in a high-power mode of operation, the modulation diverter valve assembly is for directing a first variable amount of the combusted gas flow to the low-pressure turbine stage and, in a low power mode of operation, is for directing a second variable amount of the combusted gas flow to the low-power turbine stage; and a flow diverter valve assembly for directing inlet air flow to the low-pressure compressor and the high pressure compressor based on the mode of operation of the turbine engine, wherein, in the high-power mode of operation, the flow diverter valve assembly is for directing inlet air to the low-pressure compression system of the low-pressure spool assembly, and, in the low-power mode of operation, the flow valve assembly is for diverting inlet air to the high-pressure compression system. 27. The turbine engine of claim 1, further comprising: a cruise propulsor coupled to the high-pressure spool assembly; and a lift fan coupled to the low-pressure spool assembly. 28. The turbine engine of claim 1, further comprising: a cruise propulsor coupled to the high-pressure spool assembly; and a lift rotor coupled to the low-pressure spool assembly. 29. A turbine engine comprising: a low-pressure spool assembly comprising a first low-pressure turbine stage and a low-pressure spool power turbine stage, and wherein the low-pressure spool assembly comprises a low-pressure compressor; a high-pressure spool assembly comprising a first high-pressure turbine stage and a high-pressure spool power turbine stage, wherein the low-pressure spool assembly and the high-pressure spool assembly are oriented along different axes, and wherein the high-pressure spool assembly comprises a high pressure compressor; a combustor for combusting inlet air flow to generate a combusted gas, which is expanded through the first high-pressure turbine stage; a modulation diverter valve assembly for modulating combusted gas flow from the first high-pressure turbine stage to the low-pressure spool power turbine stage and the high-pressure spool power turbine stage based on a mode of operation of the turbine engine; and a flow diverter valve assembly for directing inlet air flow to the low-pressure compressor and the high pressure compressor based on the mode of operation of the turbine engine.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.