$\require{mediawiki-texvc}$
  • 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

Simplified method and apparatus for hot-shield jet noise suppression

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/00   
미국특허분류(USC) 181/215 ; 239/26513 ; 239/26525 ; 239/26533
출원번호 US-0089693 (1979-10-30)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 18  인용 특허 : 0
초록

A method and apparatus for selectively generating a noise suppressing hot gas shield are described. A portion of the jet engine exhaust flow is selectively directed to a nozzle which at least partially surrounds the circumference of the jet engine exhaust. Prior to exiting the nozzle the flow is passed through a pressure, and therefore density, loss producing device to provide a shield flow of optimum noise suppression properties.

대표
청구항

Means for suppressing the noise of a jet engine having an exhaust duct through which passes a hot exhaust flow, comprising, means forming a shield duct open to the atmosphere at an exit end thereof at least part way around the circumference of said exhaust duct, means upstream of the exit of said shield duct for reducing the pressure of a fluid flow passing therethrough, and means for permitting at least some of said exhaust flow to enter said shield duct means, whereby said flow passes through said pressure reducing means and is then expelled to the atm...

이 특허를 인용한 특허 피인용횟수: 18

  1. Presz ; Jr. Walter M. ; Reynolds Gary. Alternating lobed mixer/ejector concept suppressor. USP1999035884472.
  2. Makowski, Maciej D.; Vasquez, David A.. Articulated diffuser and door for submerged ram air turbine power and cooling control. USP20181010094336.
  3. Lair, Jean-Pierre. Confluent exhaust nozzle. USP2005126971229.
  4. Lair, Jean-Pierre. Confluent variable exhaust nozzle. USP2004066751944.
  5. Batey J. Gary. Core flow expansion chamber device system for reduction of jet turbine engine noise. USP1998065758488.
  6. Newton Arnold C,GBX. Ducted fan gas turbine engine with variable area fan duct nozzle. USP2000066070407.
  7. Graziosi, Paolo; Kirtley, Kevin; Mani, Ramani. Fluidic chevrons and configurable thermal shield for jet noise reduction. USP2009097581692.
  8. Do, Logan H.; Krystowski, Edward A.. Gas turbine engine with variable area fan nozzle. USP2013108549834.
  9. Lair,Jean Pierre; Wolters,Gregory Thomas. Induction coupled variable nozzle. USP2006107127880.
  10. Klees Garry W. (Mercer Island WA) Wright Charles P. (Seattle WA). Internally ventilated noise suppressor with large plug nozzle. USP1985024501393.
  11. Pilon, Anthony R.. Noise reduction of supersonic jet engines. USP2013058443931.
  12. Todorovic, Predrag. Noise-reduced aircraft engine and method for reducing noise emissions of an aircraft engine. USP2012078220586.
  13. Lair, Jean-Pierre. Recessed engine nacelle. USP2005096945031.
  14. Lair, Jean-Pierre. Rotary adjustable exhaust nozzle. USP2005116966175.
  15. Zwernemann Gregory R.. Supersonic aircraft exhaust noise suppression system. USP1998105821472.
  16. Soligny Marcel R. (Chevilly Larue FRX) Duponchel Jean-Pierre D. J. (Dammarie les Lys FRX) Hoch Rene G. (La Rochette FRX). Thrust reverser and silencer assembly of turbojet engines. USP1982104353516.
  17. Presz ; Jr. Walter M.. Two-stage mixer ejector suppressor. USP1998065761900.
  18. Lair,Jean Pierre. Ventilated confluent exhaust nozzle. USP2006037010905.