Three stream, variable area, vectorable nozzle
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-003/077
F02K-001/12
F02K-001/15
F02K-003/075
F02K-003/115
F02K-001/80
출원번호
US-0209687
(2014-03-13)
등록번호
US-9845768
(2017-12-19)
발명자
/ 주소
Pesyna, Kenneth M.
Pierluissi, Anthony F.
Lerg, Bryan H.
Moore, Justin N.
출원인 / 주소
Rolls-Royce North American Technologies, Inc.
대리인 / 주소
Fishman Stewart PLLC
인용정보
피인용 횟수 :
0인용 특허 :
18
초록▼
An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream o
An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream of air is peeled off of the first stream to form a low pressure fan bypass air stream. The third stream of air traverses along the engine casing and is passed over a flap assembly to aid in cooling. The flaps are operable converge/diverge to control the multiple streams of air.
대표청구항▼
1. A gas turbine engine having an exhaust nozzle, the engine comprising: a fan operable to direct intake air to an intake portion of the gas turbine engine, the intake air is separated into multiple streams of air throughout the engine and downstream from a low pressure compressor and a high pressur
1. A gas turbine engine having an exhaust nozzle, the engine comprising: a fan operable to direct intake air to an intake portion of the gas turbine engine, the intake air is separated into multiple streams of air throughout the engine and downstream from a low pressure compressor and a high pressure compressor of the gas turbine engine, the multiple streams of air include:a first stream of air that is directed to a core of the gas turbine engine;a second stream of air that is partitioned from the first stream of air, the second stream of air traverses a length of the engine, wherein the first and second streams of air rejoin prior to passing through a turbine of the gas turbine engine;a third stream of air that is separated from the second stream of air, the third stream of air traverses the length of the engine and is injectable to a plenum of a nozzle assembly; andthe gas turbine engine further comprising the nozzle assembly that is selectively operable to control the flow of the first, second and third streams of air in order to accommodate varying flight operating demands, the nozzle assembly including a primary convergent flap and a secondary divergent flap that is attached to the primary convergent flap, the primary convergent flap pivotal inwardly and outwardly to define a throat area of the exhaust nozzle, and the secondary divergent flap pivotably attached to the primary convergent flap, the secondary divergent flap pivotable to control a flow rate of the third stream of air. 2. The gas turbine engine as claimed in claim 1, further comprising a heat exchanger located in fluid communication with the third stream of air during operation of the gas turbine engine. 3. The gas turbine engine as claimed in claim 1, further comprising a heat exchanger duct that is located within the third stream of air during operation of the gas turbine engine. 4. The gas turbine engine as claimed in claim 1, wherein the nozzle assembly includes at least one flap train, the flap train includes the primary convergent flap and the secondary divergent flap. 5. The gas turbine as claimed in claim 4, wherein the nozzle assembly includes a fixed cone that circumscribes a plurality of dynamic flap trains that include the at least one flap train. 6. The gas turbine engine as claimed in claim 1, wherein the primary convergent flap and the secondary divergent flaps are actuatable flaps that control a flow of air between the third stream of air and a core exit stream of air that is comprised of the first stream of air and the second stream of air. 7. The gas turbine engine as claimed in claim 6, wherein one of the actuable flaps is operable to engage an inner surface of a cone of the nozzle assembly, the one actuable flap positionable to an open position and to a closed position, wherein when the one actuable flap is positioned to the open position, the third stream of air flows into the plenum of the nozzle assembly, and when the one actuable flap is positioned to the closed position, the third stream of air is shut off. 8. The gas turbine engine as claimed in claim 1, wherein the nozzle assembly includes a flap system having the primary convergent and the secondary divergent flaps that may be controlled by an operator, the flap system configured to operate in one of a cruise mode, a maximum mode, or a military mode. 9. The gas turbine engine as claimed in claim 1, further comprising a plurality of channels that extend axially along a surface of the nozzle, each channel is operable to direct the third stream of air towards the plenum of the nozzle assembly. 10. The gas turbine engine as claimed in claim 1, further comprising a third airstream channel that extends axially and near an outer surface of the engine, the third airstream channel directs the third stream of air towards an exit of the nozzle. 11. The gas turbine engine as claimed in claim 10, further comprising a heat exchanger. 12. The gas turbine engine as claimed in claim 10, further comprising a conditioned air duct system for transferring conditioned air to the plenum of the nozzle assembly. 13. The gas turbine engine as claimed in claim 1, wherein the third stream includes a fan bypass air portion and a conditioned air portion, each said portion traverses an annular duct. 14. The gas turbine engine as claimed in claim 1, wherein the first and second streams of air combine rejoin downstream of a combustor of the gas turbine engine. 15. The gas turbine engine as claimed in claim 14, wherein the first stream of air passes into the combustor and the second stream of air bypasses the combustor. 16. An exhaust nozzle for an engine comprising: a fan that generates first, second, and third streams of air, wherein the first and second streams of air diverge downstream of at least one compressor of the engine;the first stream of air that exits a core of the engine;the second stream of air that traverses a length of the nozzle and is directed to a plenum of the nozzle, wherein the first and second streams of air combine rejoin downstream of a combustor of the engine and prior to passing through a turbine of the engine; andthe third stream of air is separated from the second stream of air, the third stream of air traverses the length of the engine and is injectable to the plenum of the nozzle, the third stream of air includes fan bypass air and is conditioned by a heat exchanger, the exhaust nozzle including a primary convergent flap and a secondary divergent flap that is attached to the primary convergent flap, the primary convergent flap pivotal inwardly and outwardly to define a throat area of the exhaust nozzle, and the secondary divergent flap pivotably attached to the primary convergent flap, the secondary divergent flap pivotable to control a flow rate of the third stream of air. 17. The exhaust nozzle as claimed in claim 16, further comprising a nozzle assembly that is selectively operable to control the flow of the first, second and third streams of air in order to accommodate varying flight operating demands. 18. The exhaust nozzle as claimed in claim 16, further comprising a flap train system having both the primary convergent and secondary divergent flaps for controlling a flow of air through the nozzle. 19. A method of transferring air through a gas turbine engine comprising: providing a first duct, a second duct, and a third duct;providing a fan to induce air into each of said ducts;providing a mechanical flap system of an exhaust nozzle;motivating the fan to cause first, second and third streams of air to be pushed through said first, second and third ducts, respectively, wherein the first and second streams of air diverge downstream of at least one compressor of the engine, the first stream of air that exits a core of the engine, the second stream of air that traverses a length of the exhaust nozzle and is directed to a plenum of the exhaust nozzle, and the third stream of air is separated from the second stream of air, the third stream of air traverses the length of the engine and is injectable to the plenum of the nozzle;combusting the first stream of air to form a combusted stream of air and then rejoining the combusted stream of air with the second stream of air to form a core outlet air stream prior to passing through a turbine of the engine;separating the air in the third duct into an air stream conditioned by a heat exchanger and into a bypass air stream; andmanipulating the mechanical flap system to control the flow of the core outlet stream, the conditioned air stream, and the bypass air stream, the mechanical flap system of the exhaust nozzle including a primary convergent flap and a secondary divergent flap that is attached to the primary convergent flap, the primary convergent flap pivotal inwardly and outwardly to define a throat area of the exhaust nozzle, and the secondary divergent flap pivotably attached to the primary convergent flap, the secondary divergent flap pivotable to control a flow rate of the third stream of air. 20. The method as claimed in claim 19, further comprising the step of passing air through the heat exchanger, the heat exchanger is operable to generate conditioned air that forms the conditioned air stream.
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이 특허에 인용된 특허 (18)
Wakeman Thomas G. (West Chester OH), Compact air-to-air heat exchanger for jet engine application.
Glickstein Marvin R. (North Palm Beach FL) Dixon James T. (Jupiter FL) Podolsky Donald M. (Jupiter FL), High pressure air source for aircraft and engine requirements.
Griffin James G. (West Hartford CT) Singer Irwin D. (Glastonbury CT) Summers Roger L. (Lafayette IN), Lubrication cooling system for aircraft engine accessory.
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