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특허 상세정보

Central body of a turbojet nozzle

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/00   
미국특허분류(USC) 060/770; 181/213
출원번호 US-0690381 (2007-03-23)
등록번호 US7891195 (2011-02-08)
우선권정보 FR-2006-6 02580(2006-03-24)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
인용정보 피인용 횟수 : 10  인용 특허 : 15
초록

A device for attenuating acoustical noise from an exhaust nozzle of a turbojet is disclosed. The turbojet exhaust nozzle includes a central body defining the inner surface of the primary gas flow path. The central body includes an outer wall defining one, and only one, resonator cavity. The single resonator cavity is in fluid communication with the primary gas flow path via orifices through at least one upstream portion of the outer wall. The single resonator cavity and plurality of orifices compose a Helmholtz resonator.

대표
청구항

The invention claimed is: 1. A central body disposed within an outer casing of a turbojet gas exhaust nozzle, defining a primary gas stream flow path therebetween, comprising:a first wall forming a first cavity, the first wall disposed between the first cavity and the primary gas stream flow path, and the first wall and the first cavity disposed downstream of a final turbine stage; anda plurality of orifices through at least one upstream portion of the first wall,wherein the plurality of orifices are in fluid communication with the first cavity and the p...

이 특허에 인용된 특허 (15)

  1. Wasif,Samer P.; Johnson,Clifford E.. Acoustic resonator with impingement cooling tubes. USP2008087413053.
  2. Wynosky Thomas A. (Madison CT). Acoustical turbine engine tail pipe plug. USP1980124240519.
  3. Jakob Keller CH; Georg Keller CH; Vera Keller CH. Combustion chamber for a gas turbine. USP2002036351947.
  4. Lowrie ; Brian W.. Duct linings. USP1978104122672.
  5. Webb Lee F. (Russells Point OH). Hush kit for jet engine. USP1997015592813.
  6. Campbell,Thomas A.; Voll,William A.; Diamond,John A.. Integrated axially varying engine muffler, and associated methods and systems. USP2007097267297.
  7. Sattinger, Stanley S.. Method of suppressing combustion instabilities using a resonator adopting counter-bored holes. USP2009067549506.
  8. Czachor, Robert P.. Methods and apparatus for minimizing thermal stresses in a centerbody. USP2003076584766.
  9. Sattinger, Stanley S.; Darling, Douglas Dean; Holbert, Roy Kyle; Kepes, William E.. Modular resonators for suppressing combustion instabilities in gas turbine power plants. USP2003036530221.
  10. Streib Richard A. (Ellington CT). Muffler plug for gas turbine power plant. USP1981034258822.
  11. Tseo Gudin (San Diego CA). Slanted cavity resonator. USP1977124064961.
  12. Kishi Kimihiro (Komaki JPX). Sound absorbing apparatus for a supersonic jet propelling engine. USP1997085655361.
  13. Snyder Stephen J. (West Hills CA). Sound attenuating laminate installation for jet aircraft engines. USP1990084947958.
  14. Herman Gerald T. (Seattle WA). Turbojet engine nozzle for attenuating core and turbine noise. USP1979024137992.
  15. Lair, Jean-Pierre. Variable area plug nozzle. USP2005016845607.