GB827744A - Improvements in or relating to apparatus for deflecting a gaseous stream flowing through an annular structure of an aircraft or aircraft engine - Google Patents

Improvements in or relating to apparatus for deflecting a gaseous stream flowing through an annular structure of an aircraft or aircraft engine

Info

Publication number
GB827744A
GB827744A GB20983/56A GB2098356A GB827744A GB 827744 A GB827744 A GB 827744A GB 20983/56 A GB20983/56 A GB 20983/56A GB 2098356 A GB2098356 A GB 2098356A GB 827744 A GB827744 A GB 827744A
Authority
GB
United Kingdom
Prior art keywords
jet
turbo
aircraft
compressor
ram
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB20983/56A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB827744A publication Critical patent/GB827744A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Turbines (AREA)

Abstract

827,744. Jet propulsion plant. SOC. NATIONALE D' ETUDE ET DE CONSTRUCTION DE MOTEURS D' AVIATION. July 6, 1956 [July 12, 1955], No. 20983/56. Class 110(3). [Also in Group XXXIII] In an aircraft power plant consisting of a turbo-jet engine located concentrically within a rain-jet 1, means is provided for deflecting the gases flowing from the ram-jet and the turbojet or the gases from the ram-jet alone when the turbo-jet is inoperative. A rain-jet 1, having an air intake 2 and a jet nozzle 4, surrounds a concentrically arranged turbo-jet propulsion unit consisting of intake 5, compressor 6 and turbine 8. The rear end of the turbo-jet casing is formed into two annular manifolds 10, 11 divided by radial partitions into four compartments each supplied with compressed air from compressor 6 through a pipe 15 and a control valve 16. Each compartment of manifold 10 is provided with a slot 13 and each partition of manifold 11 has a slot 14. By this means the gases emerging from the ram-jet and the turbo-jet may be controlled directionally by selective operation of the valves 16 to produce a deflection as indicated by the arrows f and f2. At high speeds of the aircraft when the turbo-jet is not working the manifolds may be supplied with compressed air from a source other than the compressor 6.
GB20983/56A 1955-07-12 1956-07-06 Improvements in or relating to apparatus for deflecting a gaseous stream flowing through an annular structure of an aircraft or aircraft engine Expired GB827744A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR827744X 1955-07-12

Publications (1)

Publication Number Publication Date
GB827744A true GB827744A (en) 1960-02-10

Family

ID=9283438

Family Applications (1)

Application Number Title Priority Date Filing Date
GB20983/56A Expired GB827744A (en) 1955-07-12 1956-07-06 Improvements in or relating to apparatus for deflecting a gaseous stream flowing through an annular structure of an aircraft or aircraft engine

Country Status (1)

Country Link
GB (1) GB827744A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2425516A (en) * 2005-04-29 2006-11-01 Gen Electric Jet engine thrust vectoring using fluid jets
US7424805B2 (en) 2005-04-29 2008-09-16 General Electric Company Supersonic missile turbojet engine
US7448199B2 (en) 2005-04-29 2008-11-11 General Electric Company Self powdered missile turbojet
US7475545B2 (en) 2005-04-29 2009-01-13 General Electric Company Fladed supersonic missile turbojet

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2425516A (en) * 2005-04-29 2006-11-01 Gen Electric Jet engine thrust vectoring using fluid jets
US7424805B2 (en) 2005-04-29 2008-09-16 General Electric Company Supersonic missile turbojet engine
US7448199B2 (en) 2005-04-29 2008-11-11 General Electric Company Self powdered missile turbojet
US7475545B2 (en) 2005-04-29 2009-01-13 General Electric Company Fladed supersonic missile turbojet
US7509797B2 (en) 2005-04-29 2009-03-31 General Electric Company Thrust vectoring missile turbojet
GB2425516B (en) * 2005-04-29 2010-09-15 Gen Electric Thrust vectoring missile turbojet

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