FR1124167A - Ignition device, particularly applicable to combustion chambers of engines and thrusters - Google Patents

Ignition device, particularly applicable to combustion chambers of engines and thrusters

Info

Publication number
FR1124167A
FR1124167A FR1124167DA FR1124167A FR 1124167 A FR1124167 A FR 1124167A FR 1124167D A FR1124167D A FR 1124167DA FR 1124167 A FR1124167 A FR 1124167A
Authority
FR
France
Prior art keywords
thrusters
engines
ignition device
combustion chambers
particularly applicable
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
Other languages
French (fr)
Inventor
Franck Ferrie
Auguste Wilhelm Quick
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
Application granted granted Critical
Publication of FR1124167A publication Critical patent/FR1124167A/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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/262—Restarting after flame-out
FR1124167D 1955-03-28 1955-03-28 Ignition device, particularly applicable to combustion chambers of engines and thrusters Expired FR1124167A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1124167T 1955-03-28

Publications (1)

Publication Number Publication Date
FR1124167A true FR1124167A (en) 1956-10-05

Family

ID=9633663

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1124167D Expired FR1124167A (en) 1955-03-28 1955-03-28 Ignition device, particularly applicable to combustion chambers of engines and thrusters

Country Status (1)

Country Link
FR (1) FR1124167A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2958196A (en) * 1959-01-02 1960-11-01 Gen Electric Flame igniter for gas turbine combustor
DE1100390B (en) * 1957-01-29 1961-02-23 Bristol Siddeley Engines Ltd Continuous radiant tube burner
DE1139330B (en) * 1957-12-20 1962-11-08 Snecma Burner device for jet engines working in direct current
DE1198130B (en) * 1958-08-22 1965-08-05 Snecma Burner for ring-shaped combustion chambers
DE1208947B (en) * 1961-08-17 1966-01-13 Gen Electric Supersonic burner for supersonic air flow in a supersonic recoil engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1100390B (en) * 1957-01-29 1961-02-23 Bristol Siddeley Engines Ltd Continuous radiant tube burner
DE1139330B (en) * 1957-12-20 1962-11-08 Snecma Burner device for jet engines working in direct current
DE1198130B (en) * 1958-08-22 1965-08-05 Snecma Burner for ring-shaped combustion chambers
US2958196A (en) * 1959-01-02 1960-11-01 Gen Electric Flame igniter for gas turbine combustor
DE1208947B (en) * 1961-08-17 1966-01-13 Gen Electric Supersonic burner for supersonic air flow in a supersonic recoil engine

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