FR1605526A - Combustion burner for supersonic jet engine - has diffuser in sleeve with divergent sides to increase flow velocity in burner - Google Patents

Combustion burner for supersonic jet engine - has diffuser in sleeve with divergent sides to increase flow velocity in burner

Info

Publication number
FR1605526A
FR1605526A FR883462A FR883462A FR1605526A FR 1605526 A FR1605526 A FR 1605526A FR 883462 A FR883462 A FR 883462A FR 883462 A FR883462 A FR 883462A FR 1605526 A FR1605526 A FR 1605526A
Authority
FR
France
Prior art keywords
burner
diffuser
sleeve
flow velocity
mach
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
FR883462A
Other languages
French (fr)
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 filed Critical
Priority to FR883462A priority Critical patent/FR1605526A/en
Application granted granted Critical
Publication of FR1605526A publication Critical patent/FR1605526A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/12—Injection-induction jet engines

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Abstract

The burner for supersonic speed engines has an internal diffuser of one diameter at one end and an outer cylinder of another diameter. The air flow in the large cylinder travels at a speed corresponding to Mach 1. The diffuser has an increasing diameter. The speed in the diffuser increases to a value Mach 1 and the speed in the outside ring is reduced to a speed of Mach E such that Mach E Mach 1.
FR883462A 1961-12-29 1961-12-29 Combustion burner for supersonic jet engine - has diffuser in sleeve with divergent sides to increase flow velocity in burner Expired FR1605526A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR883462A FR1605526A (en) 1961-12-29 1961-12-29 Combustion burner for supersonic jet engine - has diffuser in sleeve with divergent sides to increase flow velocity in burner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR883462A FR1605526A (en) 1961-12-29 1961-12-29 Combustion burner for supersonic jet engine - has diffuser in sleeve with divergent sides to increase flow velocity in burner

Publications (1)

Publication Number Publication Date
FR1605526A true FR1605526A (en) 1978-11-03

Family

ID=8769679

Family Applications (1)

Application Number Title Priority Date Filing Date
FR883462A Expired FR1605526A (en) 1961-12-29 1961-12-29 Combustion burner for supersonic jet engine - has diffuser in sleeve with divergent sides to increase flow velocity in burner

Country Status (1)

Country Link
FR (1) FR1605526A (en)

Similar Documents

Publication Publication Date Title
GB629276A (en) Improvements in or relating to jet propulsion engines
GB984817A (en) Silencing device for gas currents
GB1114026A (en) Fuel injector for gas turbine engines
GB1009323A (en) Rocket motor with exhaust nozzle closure device
GB924331A (en) Improved combined turbo-jet-ram-jet-engine
GB1296108A (en)
FR1605526A (en) Combustion burner for supersonic jet engine - has diffuser in sleeve with divergent sides to increase flow velocity in burner
GB795652A (en) Improvements in or relating to gas-turbine jet propulsion engines
GB1026996A (en) Supersonic intake for a jet propulsion engine
FR2257789A1 (en) Propulsive unit for missile - has jet and rocket with coaxial discharges axially displaced from each other
GB895872A (en) Jet propulsion engines
GB1009170A (en) Improvements in or relating to devices for augmenting the momentum of a flow of fluid
GB908120A (en) Improvements in or relating to jet propulsion nozzles
GB1001645A (en) Improvements in or relating to thermopropulsive jet engines of periodic combustion type
FR998465A (en) Adjustable air intake and gas pressure relief tubes for projectile or vehicle jet thrusters
GB1119608A (en) Jet pipe with variable effective flow cross-sectional area for a gas turbine engine
FR1452021A (en) Arrangements and method of regulating post-combustion jet engines with adjustable nozzle
GB1008574A (en) Improvements in or relating to a rocket
GB984955A (en) Nozzle for a jet engine
GB923975A (en) Improvements in gas turbine jet propulsion engines
GB1025520A (en) Improvements in and relating to exhaust assemblies for internal combustion engines
GB717880A (en) Device for fitting to exhaust systems for internal combustion engines of motor vehicles
GB862560A (en) Improvements in or relating to the silencing of the exhaust jet from combustion engines
GB1050895A (en)
GB1134390A (en) Fuel injector for gas turbine engines