BE774197A - Systeme de combustion pour conduits de derivation de moteurs d'avion - Google Patents

Systeme de combustion pour conduits de derivation de moteurs d'avion

Info

Publication number
BE774197A
BE774197A BE774197A BE774197A BE774197A BE 774197 A BE774197 A BE 774197A BE 774197 A BE774197 A BE 774197A BE 774197 A BE774197 A BE 774197A BE 774197 A BE774197 A BE 774197A
Authority
BE
Belgium
Prior art keywords
combustion system
aircraft engine
engine bypass
bypass
aircraft
Prior art date
Application number
BE774197A
Other languages
English (en)
Inventor
T N Hull
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of BE774197A publication Critical patent/BE774197A/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/11—Heating the by-pass flow by means of burners or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
BE774197A 1971-01-22 1971-10-20 Systeme de combustion pour conduits de derivation de moteurs d'avion BE774197A (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10886771A 1971-01-22 1971-01-22

Publications (1)

Publication Number Publication Date
BE774197A true BE774197A (fr) 1972-02-14

Family

ID=22324511

Family Applications (1)

Application Number Title Priority Date Filing Date
BE774197A BE774197A (fr) 1971-01-22 1971-10-20 Systeme de combustion pour conduits de derivation de moteurs d'avion

Country Status (4)

Country Link
US (1) US3693354A (fr)
BE (1) BE774197A (fr)
DE (1) DE2152442A1 (fr)
FR (1) FR2156480A1 (fr)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4527390A (en) * 1977-10-25 1985-07-09 General Motors Corporation Low loss duct burner
US5311735A (en) * 1993-05-10 1994-05-17 General Electric Company Ramjet bypass duct and preburner configuration
US5771680A (en) * 1995-12-21 1998-06-30 General Electric Company Stiffened composite structures and method of making thereof
AU2002250133A1 (en) * 2001-02-16 2002-09-04 Hamilton Sundstrand Corporation Improved aircraft system architecture
US7188467B2 (en) * 2004-09-30 2007-03-13 General Electric Company Methods and apparatus for assembling a gas turbine engine
FR2902831B1 (fr) * 2006-06-27 2010-10-22 Airbus France Turboreacteur pour aeronef
US7770381B2 (en) * 2006-12-18 2010-08-10 General Electric Company Duct burning mixed flow turbofan and method of operation
US8127528B2 (en) * 2008-02-26 2012-03-06 United Technologies Corporation Auxiliary propulsor for a variable cycle gas turbine engine
US9126374B2 (en) 2010-09-28 2015-09-08 Russell B. Hanson Iso-grid composite component
US9222410B2 (en) 2011-04-13 2015-12-29 General Electric Company Power plant
US10619855B2 (en) * 2012-09-06 2020-04-14 United Technologies Corporation Fuel delivery system with a cavity coupled fuel injector
RU2641191C1 (ru) * 2016-12-26 2018-01-16 Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)" Форсажная камера двухконтурного турбореактивного двигателя
US11421883B2 (en) 2020-09-11 2022-08-23 Raytheon Technologies Corporation Fuel injector assembly with a helical swirler passage for a turbine engine
US11754287B2 (en) 2020-09-11 2023-09-12 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11220979B1 (en) * 2020-11-10 2022-01-11 Mountain Aerospace Research Solutions, Inc. Liquid-cooled air-breathing rocket engine
US11649964B2 (en) 2020-12-01 2023-05-16 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11808455B2 (en) 2021-11-24 2023-11-07 Rtx Corporation Gas turbine engine combustor with integral fuel conduit(s)
US11846249B1 (en) 2022-09-02 2023-12-19 Rtx Corporation Gas turbine engine with integral bypass duct
US12116934B2 (en) 2023-02-10 2024-10-15 Rtx Corporation Turbine engine fuel injector with oxygen circuit
US12535214B2 (en) 2024-04-19 2026-01-27 Rtx Corporation Attaching powerplant structures together using fuel injector bolts

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3340689A (en) * 1967-09-12 Turbojet bypass engine
DE768035C (de) * 1937-12-09 1955-05-26 Messerschmitt Boelkow Blohm Regelvorrichtung fuer umlaufende Verdichter, insbesondere Axialverdichter von Flugturbinen
FR977495A (fr) * 1942-07-23 1951-04-02 Procédé pour améliorer le rendement des propulseurs à réaction et dispositif pour la mise en oeuvre de ce procédé
US3054900A (en) * 1954-07-06 1962-09-18 Itt Solid-state radiation amplifier
DE1084980B (de) * 1954-08-03 1960-07-07 Snecma Rueckstossantrieb
GB1069033A (en) * 1965-01-30 1967-05-17 Rolls Royce Improvements in or relating to gas turbine jet propulsion engines
US3295325A (en) * 1965-04-29 1967-01-03 United Aircraft Corp Jet engine afterburner flameholder
US3338051A (en) * 1965-05-28 1967-08-29 United Aircraft Corp High velocity ram induction burner
GB1170255A (en) * 1966-07-01 1969-11-12 Rolls Royce Combustion Apparatus.

Also Published As

Publication number Publication date
US3693354A (en) 1972-09-26
DE2152442A1 (de) 1972-08-03
FR2156480A1 (fr) 1973-06-01

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