$\require{mediawiki-texvc}$
  • 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"
쳇봇 이모티콘
안녕하세요!
ScienceON 챗봇입니다.
궁금한 것은 저에게 물어봐주세요.

특허 상세정보

Expander-cycle, turbine-drive, regenerative rocket engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-009/00   
미국특허분류(USC) 60/259 ; 60/260 ; 60/267
출원번호 US-0725150 (1985-04-22)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 24  인용 특허 : 3
초록

A heat-regenerative, expander-cycle, turbine-drive rocket engine 26 in which heated oxidizer gas is used to drive the fuel and oxidizer turbines 16 and 20. The hot exhaust gas from the oxidizer turbine 20 is passed through a heat-donor coil 36 of a heat exchanger 24 where it passes heat to the oxidizer flowing through a donee coil 34 to preheat the oxidizer liquid and gasify it before it is passed through the cooling jacket 28 of the rocket engine 26 where it cools the engine 26 and is itself heated to a higher temperature. The oxidizer, e.g., N2O4, is b...

대표
청구항

In a heat-regenerative, expander-cycle turbine drive for a rocket engine having a combustor, an oxidizer tank, an oxidizer turbine, an oxidizer pump and a cooling jacket around said engine, wherein oxidizer fluid, being of the type described by the general formula NxOy where x and y are integers, is passed from the oxidizer tank through the oxidizer pump, through the cooling jacket where the oxidizer fluid is heated to a high temperature, and through the oxidizer turbine as a driving fluid, the improvement comprising: a heat-exchanger having a heat-donor...

이 특허를 인용한 특허 피인용횟수: 24

  1. Fisher, Steven C.. Bi-propellant injector with flame-holding zone igniter. USP2005076918243.
  2. Fisher, Steven C.. Coaxial ignition assembly. USP2012028122703.
  3. Knight, Andrew F.. Cool gas generator and ultra-safe rocket engine. USP2005116968673.
  4. Kretschmer, Joachim. Device for supplying fuel for a rocket propulsion unit and heat exchanger to be used in said device. USP2003036536208.
  5. Hewitt, Ross A.. Diversion of combustion gas within a rocket engine to preheat fuel. USP2004106799417.
  6. Greene,William D.. Dual expander cycle rocket engine with an intermediate, closed-cycle heat exchanger. USP2008097418814.
  7. Hewitt, Ross A.. Expander cycle rocket engine with staged combustion and heat exchange. USP2004126832471.
  8. Kline, Korey R.; Smith, Kevin W.; Cesaroni, Anthony Joseph. Flame holder for a hybrid rocket motor. USP2004056739121.
  9. Kline, Korey R.; Smith, Kevin W.. Hybrid rocket motor having a precombustion chamber. USP2004016679049.
  10. Kline, Korey R.; Smith, Kevin W.. Hybrid rocket motor having a precombustion chamber. USP2004116820412.
  11. Kline, Korey R.; Smith, Kevin W.; Bales, Thomas O.. Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent. USP2004026684625.
  12. Kline, Korey R.; Smith, Kevin W.; Schmidt, Eric E.; Bales, Thomas O.. Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent. USP2003116640536.
  13. Connell Donald R. ; Cuffe Jeremy P. B.. Liquid oxygen gasifying system for rocket engines. USP1999075918460.
  14. Brown, William S.; Walczuk, Thomas M.; Noble, Rodney; Dodd, Frederick. Low velocity injector manifold for hypergolic rocket engine. USP2016089404441.
  15. Nelson Steven D. ; Sipes William J. ; Hoffmaster David K.. Mems synthesized divert propulsion system. USP2001016178741.
  16. Erickson,Christopher M; Lobitz,James R; Bissell,William. Method and apparatus for a rocket engine power cycle. USP2007057216477.
  17. Hewitt, Ross A.. Nozzle with spiral internal cooling channels. USP2004106802179.
  18. Greason, Jeffrey K.; DeLong, Daniel L.; Jones, Douglas B.. Partial superheat cycle for operating a pump in a rocket system. USP2010087784268.
  19. Bussing Thomas R. A.. Pulse detonation electrical power generation apparatus with water injection. USP2000056062018.
  20. Balepin, Vladimir V.. Rocket engine. USP2004086769242.
  21. Bichler, Peter; Immich, Hans; Kretschmer, Joachim; Schmidt, Gunther. Rocket engine combustion chamber with enhanced heat transfer to cooling jacket. USP2003106637188.
  22. Erickson, Christopher M.; Lobitz, James R.; Bissell, William R.; Hanks, David E.; Brown, Corey D.. Rocket engine power cycle. USP2011087997060.
  23. Fisher, Steven C.; Brodeur, Tim. Sequence diagram system. USP2014058731745.
  24. Le Bouar, Gaelle; Petit, Richard. Turbopump. USP2015119194333.