Thermoelectric generator in turbine engine nozzles
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-006/18
F02K-001/82
F02C-006/04
H01L-035/30
F01D-015/10
F02K-001/00
F02K-003/06
F02C-007/32
출원번호
US-0397436
(2012-02-15)
등록번호
US-9388740
(2016-07-12)
발명자
/ 주소
Kwok, David W.
Huang, James P.
Mauldin, Jack W.
출원인 / 주소
The Boeing Company
대리인 / 주소
Toler Law Group, PC
인용정보
피인용 횟수 :
1인용 특허 :
8
초록▼
In one embodiment, a gas turbine engine assembly comprises an engine assembly disposed about a longitudinal axis, a core nozzle positioned adjacent the engine assembly to direct a core flow generated by the engine assembly, a fan nozzle surrounding at least a portion of the core nozzle to direct a f
In one embodiment, a gas turbine engine assembly comprises an engine assembly disposed about a longitudinal axis, a core nozzle positioned adjacent the engine assembly to direct a core flow generated by the engine assembly, a fan nozzle surrounding at least a portion of the core nozzle to direct a fan flow, wherein the core nozzle defines a plenum to receive a portion of the core stream flow from the core nozzle and a thermoelectric generator assembly positioned in the plenum. Other embodiments may be described.
대표청구항▼
1. A core nozzle for a gas turbine engine, comprising: a core nozzle wall defining a core, configured to receive a core stream of the gas turbine engine;a cowling assembly coupled to the core nozzle wall, defining a fan flow region configured to receive a fan stream of the gas turbine engine;a therm
1. A core nozzle for a gas turbine engine, comprising: a core nozzle wall defining a core, configured to receive a core stream of the gas turbine engine;a cowling assembly coupled to the core nozzle wall, defining a fan flow region configured to receive a fan stream of the gas turbine engine;a thermoelectric generator assembly positioned in a plenum;a first inlet of the plenum configured to transfer a portion of the core stream to the thermoelectric generator assembly;a second inlet of the plenum configured to transfer a portion of the fan stream to the thermoelectric generator assembly; andan outlet of the plenum configured to combine and discharge the portion of the fan stream and the portion of the core stream into the fan stream. 2. The core nozzle of claim 1, further comprising: a first heat transfer fin positioned in the plenum to transfer heat from a portion of the core stream to the thermoelectric generator assembly. 3. The core nozzle of claim 2, further comprising: a second heat transfer fin positioned in the plenum to transfer heat from the thermoelectric generator assembly to the fan stream. 4. The core nozzle of claim 3, wherein: the first heat transfer fin comprises the first inlet; andthe second heat transfer fin comprises the second inlet. 5. The core nozzle of claim 4, wherein: the thermoelectric generator assembly has a first surface positioned adjacent to the core stream and a second surface positioned adjacent the fan stream. 6. The core nozzle of claim 1, wherein the thermoelectric generator assembly comprises at least one of peaked three-dimensional surfaces or corrugated three-dimensional surfaces. 7. The core nozzle of claim 1, wherein the thermoelectric generator assembly comprises: a frame;a plurality thermoelectric generator devices mounted on the frame; anda power bus to transport energy generated by the thermoelectric generator devices. 8. A gas turbine engine assembly, comprising: an engine assembly;a core nozzle positioned adjacent the engine assembly to direct a core stream generated by the engine assembly;a fan nozzle surrounding at least a portion of the core nozzle to direct a fan stream;a thermoelectric generator assembly positioned in a plenum;a first inlet of the plenum configured to transfer a portion of the core stream to the thermoelectric generator assembly;a second inlet of the plenum configured to transfer a portion of the fan stream to the thermoelectric generator assembly; andan outlet of the plenum configured to combine and discharge the portion of the fan stream and the portion of the core stream into the fan stream. 9. The gas turbine engine assembly of claim 8, further comprising: a first heat transfer fin positioned in the plenum to transfer heat from a portion of the core stream to the thermoelectric generator assembly. 10. The gas turbine engine assembly of claim 9, further comprising: a second heat transfer fin positioned in the plenum to transfer heat from the thermoelectric generator assembly to a portion of the fan stream from the fan nozzle. 11. The gas turbine engine assembly of claim 10, wherein: the first heat transfer fin comprises the first inlet; andthe second heat transfer fin comprises the second inlet. 12. The gas turbine engine assembly of claim 11, wherein: the thermoelectric generator assembly has a first surface positioned adjacent to the core stream and a second surface positioned adjacent the fan stream. 13. The gas turbine engine assembly of claim 8, wherein the thermoelectric generator assembly comprises at least one of peaked three-dimensional surfaces or corrugated three-dimensional surfaces. 14. The gas turbine engine assembly of claim 8, wherein the thermoelectric generator assembly comprises: a frame;a plurality thermoelectric generator devices mounted on the frame; anda power bus to transport energy generated by the thermoelectric generator devices. 15. A method to generate electricity in a gas turbine engine, comprising: generating a core stream in the gas turbine engine;generating a fan stream in the gas turbine engine;transferring, via a first inlet of a plenum, a portion of the core stream from a core nozzle positioned downstream of the gas turbine engine;passing the portion of the core stream over a first surface of a thermoelectric generator assembly;transferring, via a second inlet of the plenum, a portion of the fan stream into the plenum;passing the portion of the fan stream over a second surface of the thermoelectric generator assembly; andcombining and discharging, via an outlet of the plenum, the portion of the fan stream and the portion of the core stream into the fan stream. 16. The method of claim 15, wherein the plenum is partially defined by a core nozzle wall and a cowling assembly of the core nozzle, and wherein one or more heat transfer fins transfer heat in the plenum. 17. The method of claim 16, wherein airflow velocity in the plenum is different than airflow velocity in the core stream. 18. The method of claim 15, further comprising generating electricity based on a temperature differential between the first surface of the thermoelectric generator assembly and the second surface of the thermoelectric generator assembly. 19. The method of claim 15, further comprising transporting electricity from the thermoelectric generator assembly on a power bus.
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이 특허에 인용된 특허 (8)
Vermejan Alexander E. (Mason OH) Daiber Paul C. (Cincinnati OH) Morton Scott C. (Cincinnati OH) Taylor Michelle L. (Cincinnati OH), Gas turbine engine fan cooled heat exchanger.
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