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특허 상세정보

Dual zone combustor fuel injection

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-003/05    F23R-003/34   
미국특허분류(USC) 60/3936 ; 60/746 ; 60/760
출원번호 US-0652010 (1991-02-07)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 17  인용 특허 : 0
초록

In order to facilitate operation in a wide variety of operating conditions, and to enhance altitude starting capability while eliminating start injectors, a radial turbine engine (10) includes dual fuel injection zones (24 and 26). The radial turbine engine (10) also includes a turbine wheel (12) coupled to a rotary compressor (14) for axially driven movement, an annular nozzle (16) for directing gases of combustion radially at the turbine wheel (12), and an annular combustor (15). The annular combustor (15) defines an annular combustion space disposed a...

대표
청구항

A radial turbine engine, comprising: a turbine wheel coupled to a rotary compressor for axially driven movement thereof; an annular nozzle for directing gases of combustion radially at said turbine wheel; an annular combustor defining an annular combustion space disposed about said turbine wheel and in fluid communication with both said compressor and said nozzle, said combustor receiving fuel and air in said combustion space to generate said gases of combustion, said annular combustor being defined by an annular outer wall, an annular inner wall, and a ...

이 특허를 인용한 특허 피인용횟수: 17

  1. Teets, J. Michael. Annular combustor for use with an energy system. USP2005016845621.
  2. Shah Nipulkumar. Combustor for a gas turbine engine. USP1998055746048.
  3. Seymour Jeffrey L.. Gas turbine engine. USP1998035727378.
  4. Willis, Jeffrey W.; Pont, Guillermo; Toby, Benjamin E.; McKeirnan, Jr., Robert D.. Gas turbine engine having a multi-stage multi-plane combustion system. USP2004026684642.
  5. Snyder, Timothy S.; Burd, Steven W.; McKinney, Randal G.; Titterton, George F.; Wong, Joey. Gas turbine engine systems and methods involving enhanced fuel dispersion. USP2015089115897.
  6. Snyder, Timothy S.; Burd, Steven W.; McKinney, Randal G.; Titterton, III, George F.. Gas turbine engine systems and methods involving enhanced fuel dispersion. USP20180910066836.
  7. Venkataraman, Krishna Kumar; Davis, Jr., Lewis Berkley. Late lean injection control strategy. USP2014048683808.
  8. Venkataraman, Krishna Kumar; Terry, Jason Charles. Late lean injection for fuel flexibility. USP2014048701418.
  9. Venkataraman, Krishna Kumar; Terry, Jason Charles; Velkur, Chetan Babu; Karim, Hasan. Late lean injection fuel staging configurations. USP2014048707707.
  10. Venkataraman, Krishna Kumar; Washam, Roy Marshall; Karim, Hasan; Terry, Jason Charles; Davis, Jr., Lewis Berkley. Late lean injection system configuration. USP2014048701383.
  11. Davis, Jr., Lewis Berkley; Venkataraman, Krishna Kumar; Ziminsky, Willy Steve; Myers, Geoffrey David. Late lean injection with adjustable air splits. USP2012098275533.
  12. Davis, Jr., Lewis Berkley; Venkataraman, Krishna Kumar; Ziminsky, Willy Steve; Terry, Jason Charles. Late lean injection with expanded fuel flexibility. USP2014048701382.
  13. Jeffery W. Willis ; Guillermo Pont ; Benjamin E. Toby ; Robert D. McKeirnan, Jr.. Multi-stage multi-plane combustion system for a gas turbine engine. USP2002096453658.
  14. Teets, Joseph Michael. Radially staged RQL combustor with tangential fuel-air premixers. USP2014048701416.
  15. Mehring, Carsten Ralf; Peffley, James. Symmetric fuel injection for turbine combustor. USP2015069062609.
  16. Shekleton Jack R. ; Rodgers Colin. Turbine including a stored energy combustor. USP1999075927066.
  17. Hawie, Eduardo; Davenport, Nigel. Two-stage combustor for gas turbine engine. USP2016019243802.