$\require{mediawiki-texvc}$
  • 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Shape of gas passage in axial-flow gas turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-009/04   
미국특허분류(USC) 415/191; 415/208.2; 416/223R; 416/DIG.2
출원번호 US-0103503 (2008-04-15)
등록번호 US-8192154 (2012-06-05)
우선권정보 DE-10 2007 020 025 (2007-04-27)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Birch, Stewart, Kolasch & Birch, LLP
인용정보 피인용 횟수 : 6  인용 특허 : 15
초록

An axial-flow gas turbine engine includes a plurality of inlet guide vanes (V) which are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct) of a turbine. The inner peripheral wall (Ch) of the gas passage includes inner peripheral concave portions (Cc1 and Cc3) on an upstream side, and inner peripheral convex portions (Cv1 and Cv3) on a downstream side. The outer peripheral wall (Ct) of the gas passage includes outer peripheral convex portions (Cv2 and Cv4) on an upstream side, and o...

대표
청구항

1. A shape of a gas passage in an axial-flow gas turbine engine in which a plurality of inlet guide vanes (V) are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct), comprising: said inner peripheral wall (Ch) between a leading edge (LE) and a trailing edge (TE) of the inlet guide vane (V) comprises: an inner peripheral concave portion (Cc1) curved into a concave shape in a radial direction on an upstream side of a fluid flow direction; andan inner peripheral convex portion (Cv1) cu...

이 특허에 인용된 특허 (15)

  1. Harvey,Neil W.. Axial compressor blading. USP2008047354243.
  2. Jacobsson, Rolf Alexis. Axial flow turbine type rotor machine for elastic fluid operation. USP2004036705834.
  3. Harvey Neil W,GBX ; Rose Martin G,GBX. Bladed ducting for turbomachinery. USP2001096283713.
  4. Stevens Leonard W. (East Hampton CT). Coolable stator assembly for a gas turbine engine. USP1988014720236.
  5. Staubach, J. Brent; Wagner, Joel H.; Aggarwala, Andrew S.. Endwall shape for use in turbomachinery. USP2003126669445.
  6. Guemmer,Volker. Fluid flow machine (turbomachine) with increased rotor-stator ratio. USP2006037011495.
  7. Decker, John J.; Breeze-Stringfellow, Andrew. Fluted compressor flowpath. USP2003056561761.
  8. Orlando,Robert Joseph; Moniz,Thomas Ory; Lee,Ching Pang; Cherry,David Glenn; Beacock,Robert John; Clifford,William Larson; Carson,Scott Michael. Forward tilted turbine nozzle. USP2009037510371.
  9. Kawarada, Satoshi; Sonoda, Toyotaka. Gas turbine engine. USP2005016837679.
  10. Rose Martin G. (Derby GB2). Gas turbine engine turbine. USP1995115466123.
  11. Plemmons Larry W. (Fairfield OH) Bobo Melvin (Cincinnati OH) Wilds Alan P. (Danvers MA) Liotta Gary C. (Beverly MA). Gas turbine vane assembly seal and support system. USP1992095149250.
  12. Hoeger Martin,DEX ; Schmidt-Eisenlohr Uwe,DEX. Rotary turbomachine having a transonic compressor stage. USP2000016017186.
  13. Corcokios Nicholas (Palm Beach Gardens FL). Stator vane cluster. USP1980034194869.
  14. Matsuda Minoru,JPX. Turbine nozzle and moving blade of axial-flow turbine. USP2000106126394.
  15. Aotsuka, Mizuho; Hamazaki, Hiroshi; Takahashi, Akira; Tanimitsu, Haruyuki. Wall configuration of axial-flow machine, and gas turbine engine. USP2010047690890.