FR1248821A - Annular combustion chamber for gas turbines, in particular for airplanes and turbine equipped with said chamber or with a similar chamber - Google Patents

Annular combustion chamber for gas turbines, in particular for airplanes and turbine equipped with said chamber or with a similar chamber

Info

Publication number
FR1248821A
FR1248821A FR818768A FR818768A FR1248821A FR 1248821 A FR1248821 A FR 1248821A FR 818768 A FR818768 A FR 818768A FR 818768 A FR818768 A FR 818768A FR 1248821 A FR1248821 A FR 1248821A
Authority
FR
France
Prior art keywords
chamber
airplanes
gas turbines
similar
annular combustion
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
FR818768A
Other languages
French (fr)
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.)
ENTWICKLUNGSBAU PIRNA VEB
Original Assignee
ENTWICKLUNGSBAU PIRNA VEB
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 ENTWICKLUNGSBAU PIRNA VEB filed Critical ENTWICKLUNGSBAU PIRNA VEB
Priority to FR818768A priority Critical patent/FR1248821A/en
Application granted granted Critical
Publication of FR1248821A publication Critical patent/FR1248821A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
FR818768A 1960-02-17 1960-02-17 Annular combustion chamber for gas turbines, in particular for airplanes and turbine equipped with said chamber or with a similar chamber Expired FR1248821A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR818768A FR1248821A (en) 1960-02-17 1960-02-17 Annular combustion chamber for gas turbines, in particular for airplanes and turbine equipped with said chamber or with a similar chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR818768A FR1248821A (en) 1960-02-17 1960-02-17 Annular combustion chamber for gas turbines, in particular for airplanes and turbine equipped with said chamber or with a similar chamber

Publications (1)

Publication Number Publication Date
FR1248821A true FR1248821A (en) 1960-12-23

Family

ID=8725361

Family Applications (1)

Application Number Title Priority Date Filing Date
FR818768A Expired FR1248821A (en) 1960-02-17 1960-02-17 Annular combustion chamber for gas turbines, in particular for airplanes and turbine equipped with said chamber or with a similar chamber

Country Status (1)

Country Link
FR (1) FR1248821A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2465080A1 (en) * 1979-09-17 1981-03-20 Snecma Turbo-motor combustion chamber support - has radial pins with spherical end fitting in cup and cross pinned flanged cylindrical end
EP0178242A1 (en) * 1984-10-11 1986-04-16 United Technologies Corporation Cooling scheme for combustor vane interface

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2465080A1 (en) * 1979-09-17 1981-03-20 Snecma Turbo-motor combustion chamber support - has radial pins with spherical end fitting in cup and cross pinned flanged cylindrical end
EP0178242A1 (en) * 1984-10-11 1986-04-16 United Technologies Corporation Cooling scheme for combustor vane interface

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