[특허]Hybrid spinner nose configuration in a gas turbine engine having a bypass duct

Hybrid spinner nose configuration in a gas turbine engine having a bypass duct 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/00
출원번호	US-0864189 (1992-04-03)
발명자 / 주소	Gilchrist Alan R. (Fairfield OH) Sullivan Thomas J. (Fairfield OH) Walker Roger C. (Middletown OH)
출원인 / 주소	General Electric Company (Cincinnati OH 02)
인용정보	피인용 횟수 : 54 인용 특허 : 0

초록 ▼

A gas turbine engine has a forward rotor, a row of fan blades radially extending from the rotor, and a core turbine engine located rearwardly of the fan blades and rotor and coupled to the rotor for rotatably driving the rotor. An outer annular nacelle surrounds the rotor, fan blades and core engine. An inner annular splitter fairing is disposed rearwardly of the fan blades, surrounds the core engine, and is spaced radially inwardly from the nacelle so as to define therebetween a bypass air flow duct located outwardly from the core engine and rearwardly of the fan blades for producing thrust upon rotation of the rotor and fan blades. A hybrid shape spinner nose is attached about the rotor and projects forwardly therefrom within the nacelle and forwardly of the fan blades. The hybrid shape spinner nose has a forward substantially conical section spaced forwardly of the fan blades, a rearward substantially conical section projecting forwardly of and merging rearwardly with the fan blades, and a transition connecting the forward and rearward sections such that the spinner nose is provided with a compound, substantially conical configuration in which the slope of the forward substantially conical section is greater than the slope of an imaginary conical surface connecting a front end of the spinner nose and a leading edge of the annular splitter fairing, whereas the slope of the rearward substantially conical section is less than the slope of such imaginary conical surface.

대표청구항 ▼

In a gas turbine engine having a forward rotor, a row of circumferentially spaced fan blades attached to and extending radially outward from said rotor, a core turbine engine located rearwardly of said fan blades and rotor and being coupled to said rotor for rotatably driving said rotor, an outer annular nacelle surrounding said rotor, fan blades, and core engine, and an inner annular splitter fairing disposed rearwardly from said fan blades, surrounding said core engine and spaced radially inwardly from said nacelle so as to define therebetween a bypass air flow duct located outwardly from said core engine and rearwardly of said fan blades for producing thrust upon rotation of said rotor and fan blades therewith, a hybrid spinner nose having a central axis and being attached about said rotor and projecting forwardly therefrom and forwardly of said fan blades, said hybrid spinner nose comprising: (a) a forward nose portion spaced forwardly of said row of fan blades and terminating in a forward end; (b) a rearward nose portion projecting forwardly of and merging rearwardly with said row of fan blades; and (c) a transition located between and interconnecting said forward and rearward nose portions in a tandem arrangement with said transition as viewed along the central axis of the spinner nose being spaced approximately midway between said forward end of said forward nose portion and said row of fan blades such that the portion of said spinner nose forwardly of said row of fan blades has a compound conical configuration in which overall slope of said forward nose portion is greater than overall slope of said rearward nose portion relative to said central axis of said spinner nose.

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Hybrid spinner nose configuration in a gas turbine engine having a bypass duct 원문보기

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