Method and assembly for providing an anti-icing airflow
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/02
B64D-015/04
F01D-025/10
F01D-025/30
F02C-003/04
F02C-009/18
F02C-006/08
F02C-007/047
출원번호
US-0160366
(2016-05-20)
등록번호
US-10260371
(2019-04-16)
발명자
/ 주소
Youssef, Nashed
Eleftheriou, Andreas
Alecu, Daniel
출원인 / 주소
PRATT & WHITNEY CANADA CORP.
대리인 / 주소
Norton Rose Fulbright Canada LLP
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A method for providing an anti-icing airflow, including extracting a compressed airflow from a core flow path of an engine, heating the compressed airflow, mixing the heated compressed airflow with air extracted from a bypass flow path to create the anti-icing airflow having a higher temperature and
A method for providing an anti-icing airflow, including extracting a compressed airflow from a core flow path of an engine, heating the compressed airflow, mixing the heated compressed airflow with air extracted from a bypass flow path to create the anti-icing airflow having a higher temperature and pressure than that of the air extracted from the bypass flow path, and circulating the anti-icing airflow away from the bypass flow path. Also, an assembly located at least in part inside a turbofan engine and including a heat exchanger, a flow mixing device having a first inlet in the bypass flow path, a second inlet and an outlet, a first conduit providing fluid communication between the heat exchanger and a compressed air portion of the core flow path, a second conduit providing fluid communication between the heat exchanger and the second inlet, and a third conduit in fluid communication with the outlet.
대표청구항▼
1. A method for providing an anti-icing airflow to an aircraft anti-icing system, the method comprising: extracting a compressed airflow from a core flow path of a turbofan engine;heating the compressed airflow to provide a heated compressed airflow;mixing the heated compressed airflow with air extr
1. A method for providing an anti-icing airflow to an aircraft anti-icing system, the method comprising: extracting a compressed airflow from a core flow path of a turbofan engine;heating the compressed airflow to provide a heated compressed airflow;mixing the heated compressed airflow with air extracted from a bypass flow path of the turbofan engine to create the anti-icing airflow, the anti-icing airflow having a higher temperature and pressure than that of the air extracted from the bypass flow path, wherein the heated compressed airflow is used as a motive flow to extract the air from the bypass flow path; andcirculating the anti-icing airflow away from the bypass flow path to the aircraft anti-icing system. 2. The method as defined in claim 1, wherein mixing the heated compressed airflow with the air extracted from the bypass flow path is performed at a location adjacent the bypass flow path. 3. The method as defined in claim 1, wherein the anti-icing airflow includes more air from the bypass flow path than from the core flow path. 4. The method as defined in claim 1, wherein mixing the heated compressed airflow with the air extracted from the bypass flow path is performed with a ratio of a mass flow of air extracted from the bypass flow path to a mass flow of the heated compressed airflow having a value from 0.5:1 to 2:1. 5. The method as defined in claim 1, wherein the heated compressed airflow and the air extracted from the bypass flow path are mixed in an ejector. 6. The method as defined in claim 1, wherein the compressed airflow is extracted from a combustor plenum of the turbofan engine. 7. The method as defined in claim 1, wherein the compressed airflow is heated through heat exchange with an exhaust of a turbine section of the turbofan engine. 8. The method as defined in claim 1, wherein the anti-icing airflow has a pressure of 20 psia to 30 psia. 9. An assembly for providing an anti-icing airflow to an aircraft anti-icing system, the assembly located at least in part inside a turbofan engine, the assembly comprising: a heat exchanger including an inlet, an outlet and a fluid path between the inlet and outlet, the fluid path in heat exchange relationship with a heat source;a flow mixing device having first and second inlets in fluid communication with a same outlet, the first inlet received in a bypass flow path of the turbofan engine;a first conduit providing fluid communication between the inlet of the heat exchanger and a compressed air portion of a core flow path of the turbofan engine;a second conduit providing fluid communication between the outlet of the heat exchanger and the second inlet of the flow mixing device; anda third conduit in fluid communication with the outlet of the flow mixing device for providing the anti-icing airflow to an aircraft anti-icing system. 10. The assembly as defined in claim 9, wherein the heat source of the heat exchanger is an exhaust duct of a turbine section of the turbofan engine, the fluid path including a conduit in heat exchange relationship with the exhaust duct. 11. The assembly as defined in claim 9, wherein the flow mixing device is an ejector, the first inlet defining a main inlet, the second inlet defining a motive flow inlet in use providing a motive flow driving flow through the main inlet. 12. The assembly as defined in claim 9, further comprising a valve regulating a flow through the third conduit, the valve located downstream of the flow mixing device, the fluid communication from the compressed air portion of a core flow path to the flow mixing device remaining open when the valve is closed. 13. A turbofan engine for an aircraft, the turbofan engine comprising: a core flow path and an annular bypass flow path defined around the core flow path;a combustor plenum containing a combustor, the combustor plenum in fluid communication with a downstream end of a compressor section of the core flow path;a heat exchanger including an inlet, an outlet and a fluid path between the inlet and outlet, the fluid path in heat exchange relationship with a heat source;a flow mixing device having first and second inlets in fluid communication with a same outlet, the first inlet in fluid communication with the annular bypass flow path;a first conduit providing fluid communication between the combustor plenum and the inlet of the heat exchanger;a second conduit providing fluid communication between the outlet of the heat exchanger and the second inlet of the flow mixing device; anda third conduit in fluid communication with the outlet of the flow mixing device for circulating a flow from the flow mixing device to an anti-icing system of the aircraft. 14. The engine as defined in claim 13, wherein the heat source of the heat exchanger is an exhaust duct of a turbine section of the engine, the fluid path including a conduit in heat exchange relationship with the exhaust duct. 15. The engine as defined in claim 13, wherein the flow mixing device is an ejector, the first inlet received in the bypass flow path and defining a main inlet, the second inlet defining a motive flow inlet in use providing a motive flow driving flow through the main inlet. 16. The engine as defined in claim 13, further comprising a valve regulating a flow through the third conduit. 17. The engine as defined in claim 13, wherein a relative size of the core flow path and of the bypass flow path defines a bypass ratio of 4 or less. 18. The engine as defined in claim 13, wherein a relative size of the core flow path and of the bypass flow path defines a bypass ratio of at least 1.35 and at most 1.7. 19. A method for providing an anti-icing airflow to an aircraft anti-icing system, the method comprising: extracting a compressed airflow from a combustor plenum of a turbofan engine;heating the compressed airflow to provide a heated compressed airflow;mixing the heated compressed airflow with air extracted from a bypass flow path of the turbofan engine to create the anti-icing airflow, the anti-icing airflow having a higher temperature and pressure than that of the air extracted from the bypass flow path; andcirculating the anti-icing airflow away from the bypass flow path to the aircraft anti-icing system. 20. A method for providing an anti-icing airflow to an aircraft anti-icing system, the method comprising: extracting a compressed airflow from a core flow path of a turbofan engine;heating the compressed airflow through heat exchange with an exhaust of a turbine section of the turbofan engine to provide a heated compressed airflow;mixing the heated compressed airflow with air extracted from a bypass flow path of the turbofan engine to create the anti-icing airflow, the anti-icing airflow having a higher temperature and pressure than that of the air extracted from the bypass flow path; andcirculating the anti-icing airflow away from the bypass flow path to the aircraft anti-icing system.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (4)
Cheong, Chee Yuen, Air recovery system for precooler heat-exchanger.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.