[특허]Fan exit guide vane platform contouring

Fan exit guide vane platform contouring 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/14 F02K-003/06 F01D-009/02
출원번호	US-0774190 (2014-03-13)
등록번호	US-10196897 (2019-02-05)
국제출원번호	PCT/US2014/025386 (2014-03-13)
국제공개번호	WO2014/197062 (2014-12-11)
발명자 / 주소	Thomas, Flavien L.
출원인 / 주소	UNITED TECHNOLOGIES CORPORATION
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 26

초록 ▼

A turbofan engine includes a fan section with a plurality of fan blades rotatable about an engine axis generating an airflow, a bypass passage through which the airflow passes, and a fan exit guide vane. The fan exit guide vane assembly includes a plurality of airfoils disposed between an inner platform wall and an outer platform wall. At least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent airfoils. The contoured surface includes at least one concave region and at least one convex region. A method of reducing secondary flow structures in bypass air flow with the turbofan is also disclosed.

대표청구항 ▼

1. A turbofan engine comprising: a fan section including a plurality of fan blades rotatable about an engine axis generating an airflow;a bypass passage through which the airflow passes; anda fan exit guide vane assembly including a plurality of airfoils disposed between an inner platform wall and an outer platform wall, wherein at least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent ones of the plurality of airfoils, and wherein the contoured surface includes at least one concave region and at least one convex region, wherein at least one of the at least one convex region and the at least one concave regions comprise a subregion with a concavity or convexity different from that of the convex or concave region. 2. The turbofan engine as recited in claim 1, wherein one of the inner and outer platform walls has an axisymmetric cross-section at a leading edge and a trailing edge of a plane defined by the adjacent ones of the plurality of airfoils, and the leading and trailing edges of the adjacent ones of the plurality of airfoils bound an axial extent of the contoured surface. 3. The turbofan engine as recited in claim 1, wherein the at least one convex region includes first and second convex regions adjacent to first and second airfoils of the plurality of airfoils, respectively. 4. The turbofan engine as recited in claim 3, wherein the first and second convex regions extend axially from near a first midchord of the first airfoil and a second midchord of the second airfoil to near trailing edges of the first and second airfoils, respectively. 5. The turbofan engine as recited in claim 1, wherein the contoured surface transitions gradually from the at least one convex region to the at least one concave region. 6. A turbofan engine comprising: a fan section including a plurality of fan blades rotatable about an engine axis generating an airflow;a bypass passage through which the airflow passes; anda fan exit guide vane assembly including a plurality of airfoils disposed between an inner platform wall and an outer platform wall, wherein at least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent ones of the plurality of airfoils, and wherein the contoured surface includes at least one concave region and at least one convex region, wherein the at least one convex region includes first and second convex regions adjacent to first and second airfoils of the plurality of airfoils, respectively, wherein the first and second convex regions extend axially from near a first midchord of the first airfoil and a second midchord of the second airfoil to near trailing edges of the first and second airfoils, respectively, wherein the at least one concave region includes a first concave region having first and second prongs. 7. The turbofan engine as recited in claim 6, wherein the at least one convex region includes a third convex region between the first and second prongs of the first concave region. 8. The turbofan engine as recited in claim 6, wherein the first and second prongs are oriented towards trailing edges of the adjacent ones of the plurality of airfoils. 9. The turbofan engine as recited in claim 8 further comprising a second concave region adjacent to a pressure side of one of the first and second airfoils. 10. The turbofan engine as recited in claim 9, further comprising a fourth convex region between the first and second concave regions.

이 특허에 인용된 특허 (26)

Harvey, Neil William; Stokes, Mark Richard; Bagshaw, David Andrew, Aerofoil members for a turbomachine.
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Allen-Bradley, Eunice; Grover, Eric A.; Praisner, Thomas J.; Wagner, Joel H., Airfoil array with an endwall protrusion and components of the array.
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Jansen Willem (Weston MA) Platt Melvin (Holliston MA), Arbitrary hub for centrifugal impellers.
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Harvey,Neil W., Axial compressor blading.
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Harvey Neil W,GBX ; Rose Martin G,GBX, Bladed ducting for turbomachinery.
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Clemen, Carsten, Bypass duct of a turbofan engine.
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Staubach, J. Brent; Wagner, Joel H.; Aggarwala, Andrew S., Endwall shape for use in turbomachinery.
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Grover, Eric A.; Praisner, Thomas J.; Modesto-Madera, Noel; Jurek, Renee J., Endwall with leading-edge hump.
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Lee,Ching Pang, Fillet energized turbine stage.
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Spear David A. (Manchester CT) Biederman Bruce P. (Meriden CT), Flow directing assembly for the compression section of a rotary machine.
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Zess, Gary A.; Wagner, Joel, Flow directing device.
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David William Crall ; John Robert Kelley ; Ian Francis Prentice ; Gregory Scott McNulty ; Michael De Wayne Toye, Fluted blisk.
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Decker, John J.; Breeze-Stringfellow, Andrew, Fluted compressor flowpath.
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Kawarada, Satoshi; Sonoda, Toyotaka, Gas turbine engine.
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Rose Martin G. (Derby GB2), Gas turbine engine turbine.
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Carter, Stephen Michael, Method and apparatus for reducing rotor assembly circumferential rim stress.
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Mark Joseph Mielke ; John Jared Decker, Method and apparatus for reducing rotor assembly circumferential rim stress.
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Siden, Gunnar L.; Bielek, Craig A.; Barr, Brian C.; Boyer, Bradley T.; Vandeputte, Thomas W.; Galie, Peter A., Methods and apparatus relating to improved turbine blade platform contours.
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Mielke, Mark J.; Rhoda, James E.; Bulman, David E.; Burns, Craig P.; Smith, Paul M.; Suffoletta, Daniel G.; Ballman, Steven M.; Zylka, Richard P.; Egan, Lawrence J., Reduced-stress compressor blisk flowpath.
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Hoeger Martin,DEX ; Schmidt-Eisenlohr Uwe,DEX, Rotary turbomachine having a transonic compressor stage.
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Tam,Anna; Lee,Ching Pang; Kirtley,Kevin Richard; Bunker,Ronald Scott; Lamson,Scott Henry; Carson,Scott Michael, Scalloped surface turbine stage.
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Gupta, Anurag; Barr, Brian Chandler; Kirtley, Kevin Richard; Tam, Anna, Scalloped surface turbine stage with trailing edge ridges.
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Sonoda, Toyotaka; Hasenjaeger, Martina, Shape of gas passage in axial-flow gas turbine engine.
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Iida, Koichiro, Turbine blade cascade end wall.
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Stuart Alan R. (Cincinnati OH), Turbofan engine bypass and exhaust system.
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Aotsuka, Mizuho; Hamazaki, Hiroshi; Takahashi, Akira; Tanimitsu, Haruyuki, Wall configuration of axial-flow machine, and gas turbine engine.
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