Turbofan engine with variable exhaust cooling
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-001/38
B64D-033/04
F02K-001/48
F02K-003/077
F02K-001/34
출원번호
US-0293963
(2014-06-02)
등록번호
US-9574518
(2017-02-21)
발명자
/ 주소
Moore, Matthew D.
Marques, Edward C.
출원인 / 주소
The Boeing Company
대리인 / 주소
DASCENZO Intellectual Property Law, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
28
초록▼
Disclosed aircraft and turbofan engines have an active configuration (corresponding to flight, etc.) and an idle configuration (corresponding to ground idle). Turbofan engines comprise a core engine, a nacelle, a bypass duct therebetween, and a bypass splitter shell that extends at least partially b
Disclosed aircraft and turbofan engines have an active configuration (corresponding to flight, etc.) and an idle configuration (corresponding to ground idle). Turbofan engines comprise a core engine, a nacelle, a bypass duct therebetween, and a bypass splitter shell that extends at least partially between the nacelle and the core engine to define peripheral and interstitial bypass ducts. Bypass flow in the bypass duct splits into peripheral bypass flow and interstitial bypass flow. The relatively cool, slow interstitial bypass flow is directed into relatively hot, fast core exhaust flow from the core engine and into a mixed exhaust duct at least partially defined by the bypass splitter shell. The bypass splitter shell may be selectively positioned to increase (in the idle configuration) or to decrease (in the active configuration) the relative flow of the interstitial bypass flow, thereby cooling and/or slowing the mixed exhaust flow in the idle configuration.
대표청구항▼
1. A turbofan engine comprising: a core engine with a core engine shroud and a core exhaust duct;a nacelle radially surrounding at least a fore portion of the core engine;a bypass duct defined between the nacelle and the core engine shroud;a bypass splitter shell substantially coaxial with the nacel
1. A turbofan engine comprising: a core engine with a core engine shroud and a core exhaust duct;a nacelle radially surrounding at least a fore portion of the core engine;a bypass duct defined between the nacelle and the core engine shroud;a bypass splitter shell substantially coaxial with the nacelle and the core engine, wherein the bypass splitter shell includes a trailing edge outside of the nacelle and a leading edge that extends into the bypass duct to define a peripheral bypass duct between the bypass splitter shell and the nacelle, and to define an interstitial bypass duct between the bypass splitter shell and the core engine shroud; andan actuator coupled to the bypass splitter shell and configured to axially translate the bypass splitter shell between an idle configuration with a first inlet area of the interstitial bypass duct and an active configuration with a second inlet area of the interstitial bypass duct, wherein the first inlet area is greater than the second inlet area;wherein the turbofan engine includes an idle state wherein the core engine is operating at ground idle speed and the turbofan engine is in the idle configuration. 2. The turbofan engine of claim 1, wherein a position of the leading edge of the bypass splitter shell in the active configuration is forward of a position of the leading edge of the bypass splitter shell in the idle configuration. 3. The turbofan engine of claim 1, wherein the bypass splitter shell defines, in the idle configuration, a third inlet area of the peripheral bypass duct and defines, in the active configuration, a fourth inlet area of the peripheral bypass duct, wherein the third inlet area is less than the fourth inlet area. 4. The turbofan engine of claim 1, wherein the bypass splitter shell defines a mixed exhaust duct positioned to receive flow from the interstitial bypass duct and flow from the core exhaust duct. 5. The turbofan engine of claim 1, wherein the idle configuration is configured to produce, while the turbofan engine is in the idle state, a mixed exhaust flow from a combination of flow through the interstitial bypass duct and flow through the core exhaust duct, and wherein the mixed exhaust flow has an average temperature of less than 80° C. 6. The turbofan engine of claim 1, wherein the core exhaust duct includes a lobed mixer that is configured to direct at least a portion of exhaust from the core engine into air flow from the interstitial bypass duct. 7. The turbofan engine of claim 6, wherein the lobed mixer includes a mixer cuff pivotally coupled to the core exhaust duct and movably coupled to the bypass splitter shell. 8. The turbofan engine of claim 6, wherein the lobed mixer includes a mixer cuff, and wherein an open volume of the mixer cuff is greater in the idle configuration than in the active configuration. 9. The turbofan engine of claim 6, wherein the lobed mixer includes a plurality of mixer cuffs spaced around a circumference of the core exhaust duct. 10. The turbofan engine of claim 1, wherein the bypass splitter shell includes a fore portion that includes the leading edge, an aft portion that includes the trailing edge, and a central portion between the fore portion and the aft portion, wherein the central portion is configured to support the bypass splitter shell. 11. The turbofan engine of claim 10, wherein the fore portion and the aft portion are only supported by the central portion. 12. A turbofan engine comprising: a nacelle with an aft portion;a bypass splitter shell with a fore portion, wherein the bypass splitter shell is substantially coaxial with the nacelle, wherein the fore portion of the bypass splitter shell is surrounded by the aft portion of the nacelle, wherein the bypass splitter shell is configured to divert a portion of a fan bypass flow toward a core exhaust flow for mixing the portion of the fan bypass flow with the core exhaust flow; andan actuator coupled to the bypass splitter shell and configured to selectively translate the bypass splitter shell aftward to increase the portion of the fan bypass flow during ground idle operation of the turbofan engine. 13. The turbofan engine of claim 12, wherein the bypass splitter shell includes a central portion and an aft portion, wherein the central portion is configured to support the bypass splitter shell. 14. The turbofan engine of claim 12, wherein, when the actuator has translated the bypass splitter shell aftward and when the turbofan engine is operated at ground idle speed, the mass ratio of the portion of fan bypass flow to the core exhaust flow is greater than 2 and less than 5. 15. The turbofan engine of claim 12, wherein, when the actuator has translated the bypass splitter shell aftward and the turbofan engine is in an idle state, an average temperature of a mixed exhaust flow formed of the portion of fan bypass flow and core exhaust flow is less than 80° C. 16. The turbofan engine of claim 12, further comprising a lobed mixer with a mixer cuff with a mixer cuff that is configured to direct at least a portion of the core exhaust flow into the portion of the fan bypass flow. 17. A method of reducing an average temperature of aircraft engine exhaust while an aircraft is idling on the ground, the method comprising: operating an aircraft engine at ground idle speed;directing a core exhaust flow through a core exhaust duct of the aircraft engine;directing a fan bypass flow through a fan bypass duct of the aircraft engine;diverting a portion of the fan bypass flow into an interstitial bypass duct of the aircraft engine to mix the portion of the fan bypass flow with the core exhaust flow to form a first mixed exhaust flow, wherein the interstitial bypass duct is defined by a bypass splitter shell radially surrounding at least a portion of the core exhaust duct; andtranslating the bypass splitter shell aftward to increase the portion of the fan bypass flow diverted to form a second mixed exhaust flow that is cooler than the first mixed exhaust flow. 18. The method of claim 17, wherein the core exhaust duct includes a lobed mixer with a mixer cuff pivotally coupled to the core exhaust duct and movably coupled to the bypass splitter shell, and wherein the translating includes pivoting the mixer cuff. 19. The method of claim 18, wherein the pivoting increases an efficiency of mixing of the core exhaust flow and the fan bypass flow.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (28)
Nash Dudley O. (Forest Park OH), Apparatus and method for controlling fan duct flow in a gas turbine engine.
Torkelson Delbert W. (Catoosa OK) Jannetta Thomas J. (Tulsa OK) Nikkanen John P. (West Hartford CT) Webb Daniel E. (Wethersfield CT) Zysman Steven H. (Middletown CT) Colletti William D. (Cromwell CT), Fixed geometry mixer/ejector suppression system for turbofan aircraft engines.
Lord,Wesley K.; Zysman,Steven H.; Howlett,Matthew J., Fluid mixer with an integral fluid capture ducts forming auxiliary secondary chutes at the discharge end of said ducts.
Anderson, Morris G.; Jan, David K.; Zurmehly, George E.; Halfmann, Steve H.; Zollars, Christopher E., Integrated support and mixer for turbo machinery.
Sloan, Mark L.; Marques, Edward C.; Moore, Matthew D.; Bigbee-Hansen, William J., Internal mixing of a portion of fan exhaust flow and full core exhaust flow in aircraft turbofan engines.
Fletcher James C. Administrator of the National Aeronautics and Space Administration ; with respect to an invention of ( Palo Alto CA) Cheng Dah Y. (Palo Alto CA), Noise suppressor for turbo fan jet engines.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.