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특허 상세정보

Method of making a rocket thrust chamber

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B23P-015/00   
미국특허분류(USC) 298/900.1 ; 209/523
출원번호 US-0293513 (1999-04-15)
발명자 / 주소
대리인 / 주소
    Skjerven Morrill MacPhersonMacPherson
인용정보 피인용 횟수 : 12  인용 특허 : 7
초록

A fabricating method for a one-piece refractory metal rocket engine chamber is described. Hollow liner sections of a platinum group metal or alloy are inserted into a chamber barrel portion to form the combustion chamber, connecting into a conical portion, a venturi throat and into a second conical portion, forming an expansion nozzle exit of the chamber. The hollow liner sections correspond to the interior shapes of the chamber portions. A refractory metal split hollow mandrel completes an assembly which is subjected to a hot isostatic pressing cycle. T...

대표
청구항

[What is claimed is:] [1.]forming a one piece hollow refractory metal thrust chamber having a barrel portion forming a combustion chamber, a first conical portion connecting the barrel portion to a venturi throat section, and a second conical portion extending downstream from the venturi throat portion and forming an expansion nozzle;positioning a first hollow metal cylindrical liner section, having a first end and a scarfed second end, in said barrel portion;positioning a second hollow metal liner section having a scarfed first end and a scarfed second ...

이 특허를 인용한 특허 피인용횟수: 12

  1. Christensen,Donald J.; Gratton,Jason A.; Woessner,George T.. Co-molding metallic-lined phenolic components. USP2009027493691.
  2. Kayser, Gregory F.; Wisner, Daniel L.; Somerville, John G.. Diffusion bonded composite material and method therefor. USP2012078225481.
  3. Nguyen, Ly D.; Woodcock, Gregory O.; Kujala, Stony. Forming and assembly method for multi-axial pivoting combustor liner in gas turbine engine. USP2005076912782.
  4. Morita,Yoshiharu. High-pressure fuel injection pipe. USP2007047204234.
  5. Usui,Masayoshi; Asada,Kikuo; Hashimoto,Yasuaki; Nishizawa,Hiroyuki; Seino,Iichiro. Joint structure of diverging branch pipe in fuel rail for internal combustion engine, diverging branch pipe and manufacture method of its diverging branch pipe. USP2007107275521.
  6. Barnes, John James; Biondo, Joseph Gerard; Gelblum, Peter Gideon; Lanam, Richard Delbert; Noelke, Charles Joseph; Wells, David Archer. Metallurgically bonded layered article having a curved surface. USP2004086777110.
  7. Lundgren, Jan. Method for manufacturing outlet nozzles for rocket engines. USP2005066907662.
  8. Lundgren, Jan. Method for manufacturing outlet nozzles for rocket engines. USP2003076591499.
  9. Lundgren, Jan. Method for manufacturing outlet nozzles for rocket engines. USP2005096945032.
  10. Bruno, Salvatore Thomas; Koch, Christopher Anthony; Mantilla, Yazdan Paul; Prasad, Sanjay B.; Wittenauer, Jerome Paul; Yaney, Deborah Lynn; Zegarski, Joseph. Net molded tantalum carbide rocket nozzle throat. USP2003016510694.
  11. Bruno, Salvatore Thomas; Koch, Christopher Anthony; Mantilla, Yazdan Paul; Prasad, Sanjay B.; Wittenauer, Jerome Paul; Yaney, Deborah Lynn; Zegarski, Joseph. Net molded tantalum carbide rocket nozzle throat and method of making. USP2004016673449.
  12. Sowa, Armin. Rocket thrust chamber. USP2004036705076.