[특허]System and method for cooling a turbine engine assembly

GENERAL ELECTRIC COMPANY

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특허 상세정보

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System and method for cooling a turbine engine assembly

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/18 F02C-003/04
출원번호	US-0056003 (2016-02-29)
등록번호	US-10125687 (2018-11-13)
발명자 / 주소	Hoefler, Florian Stefan Clancy, Cathal Peter, Andrew Maxwell
출원인 / 주소	GENERAL ELECTRIC COMPANY
대리인 / 주소	GE Global Patent Operation
인용정보	피인용 횟수 : 0 인용 특허 : 11

초록
▼

A turbine engine assembly includes a core compressor configured to discharge a first airflow at a first temperature and a first pressure. The turbine engine assembly also includes a cooling system turbine configured to receive the first airflow at the first temperature and the first pressure and discharge a second airflow at a second pressure less than the first pressure. The turbine engine assembly further includes a heat exchanger configured to receive the second airflow and discharge a third airflow at a second temperature less than the first temperature. The turbine engine assembly also includes a cooling system compressor rotatably coupled to the cooling system turbine. The cooling system compressor is configured to receive the third airflow and discharge a fourth airflow at a third pressure greater than the first pressure.

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청구항
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1. A turbine engine assembly comprising: a core compressor configured to discharge a first airflow at a first temperature and a first pressure;a cooling system turbine configured to receive the first airflow at the first temperature and the first pressure and discharge a second airflow at a second pressure less than the first pressure;a heat exchanger configured to receive the second airflow and discharge a third airflow at a second temperature less than the first temperature; anda cooling system compressor rotatably coupled to said cooling system turbine, said cooling system compressor configured to receive the third airflow and discharge a fourth airflow at a third pressure greater than the first pressure. 2. The turbine engine assembly in accordance with claim 1 further comprising at least one control mechanism to control a flow of fluids through said turbine engine assembly, said at least one control mechanism comprising at least one of the following: a valve, variable geometry, and a variable speed controller. 3. The turbine engine assembly in accordance with claim 1 further comprising a recuperator coupled to said cooling system turbine and said cooling system compressor, said recuperator configured to facilitate heat transfer from the second airflow to the fourth airflow. 4. The turbine engine assembly in accordance with claim 1, wherein said core compressor is a high pressure compressor, said turbine engine assembly further comprising a high pressure turbine rotatably coupled to said high pressure compressor and at least one combustor coupled in flow communication with said high pressure compressor and said high pressure turbine. 5. The turbine engine assembly in accordance with claim 4, wherein at least one of the following is configured to receive the fourth airflow: said high pressure compressor, said combustor, and said high pressure turbine. 6. The turbine engine assembly in accordance with claim 4 further comprising a low pressure compressor and a low pressure turbine rotatably coupled to said low pressure compressor, wherein said low pressure turbine is configured to receive the fourth airflow. 7. The turbine engine assembly in accordance with claim 1 further comprising a shaft extending between and drivingly coupling said cooling system turbine to said cooling system compressor such that rotation of said cooling system turbine induces rotation of said cooling system compressor. 8. The turbine engine assembly in accordance with claim 7, wherein the first airflow provides an inlet airflow for said cooling system turbine, said cooling system turbine configured to operate without additional inlet airflow. 9. A cooling system for a turbine engine assembly, said cooling system comprising: a cooling system turbine configured to receive a first airflow at a first pressure and a first temperature and discharge a second airflow at a second pressure less than the first pressure;a heat exchanger configured to receive the second airflow and discharge a third airflow at a second temperature less than the first temperature;a cooling system compressor rotatably coupled to said cooling system turbine, said cooling system compressor configured to receive the third airflow and discharge a fourth airflow at a third pressure greater than the first pressure; anda conduit coupled in flow communication with said cooling system compressor and configured to direct the fourth airflow towards the turbine engine assembly for cooling the turbine engine assembly. 10. The cooling system in accordance with claim 9, wherein the turbine engine assembly includes at least one of a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine, wherein said cooling system compressor is separate from the high pressure compressor and said cooling system turbine is separate from the high pressure turbine and the low pressure turbine, said conduit configured to direct the fourth airflow towards at least one of the following components of the turbine engine assembly: the high pressure compressor, the combustor, the high pressure turbine, and the low pressure turbine. 11. The cooling system in accordance with claim 9 further comprising a recuperator coupled to said cooling system turbine and said cooling system compressor, said recuperator configured to facilitate heat transfer between the second airflow and the fourth airflow. 12. The cooling system in accordance with claim 9 further comprising at least one control mechanism to control a flow of fluids through said cooling system, said at least one control mechanism comprising at least one of the following: a valve, variable geometry, and a variable speed controller. 13. The cooling system in accordance with claim 9 further comprising a shaft extending between and coupling said cooling system turbine to said cooling system compressor such that rotation of said cooling system turbine induces rotation of said cooling system compressor. 14. The cooling system in accordance with claim 13, wherein the first airflow provides an inlet airflow for said cooling system turbine, said cooling system turbine configured to operate without additional inlet airflow. 15. A method of cooling a turbine engine assembly, said method comprising: rotating a core turbine to induce rotation of a core compressor coupled to the core turbine;discharging a first airflow from the core compressor at a first temperature and a first pressure;directing the first airflow toward a cooling system turbine;discharging from the cooling system turbine a second airflow at a second pressure less than the first pressure;directing the second airflow towards a heat exchanger;discharging from the heat exchanger a third airflow at a second temperature less than the first temperature;directing the third airflow toward a cooling system compressor rotatably coupled to the cooling system turbine; anddischarging from the cooling system compressor a fourth airflow at a third pressure greater than the first pressure. 16. The method in accordance with claim 15 further comprising directing the fourth airflow to at least one of the following: the core turbine, the core compressor, a combustor, and a low pressure turbine coupled to a low pressure compressor. 17. The method in accordance with claim 15, wherein discharging the fourth airflow at a third pressure greater than the first pressure comprises discharging the fourth airflow at the third pressure greater than the first pressure and the third temperature greater than the second temperature. 18. The method in accordance with claim 15 further comprising transferring heat between the second airflow and the fourth airflow. 19. The method in accordance with claim 15, wherein directing the first airflow to the cooling system turbine provides an inlet airflow to the cooling system turbine, said cooling system turbine configured to operate without additional inlet airflow. 20. The method in accordance with claim 15 further comprising discharging a fifth airflow from the core compressor and igniting the fifth airflow to induce rotation of the core turbine.

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System and method for cooling a turbine engine assembly

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System and method for cooling a turbine engine assembly

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