FR1285627A - Groupe moteur à turbine à gaz - Google Patents

Groupe moteur à turbine à gaz

Info

Publication number
FR1285627A
FR1285627A FR857575A FR857575A FR1285627A FR 1285627 A FR1285627 A FR 1285627A FR 857575 A FR857575 A FR 857575A FR 857575 A FR857575 A FR 857575A FR 1285627 A FR1285627 A FR 1285627A
Authority
FR
France
Prior art keywords
gas turbine
turbine engine
engine group
group
gas
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
FR857575A
Other languages
English (en)
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.)
Bristol Siddeley Engines Ltd
Original Assignee
De Havilland Engine Co Ltd
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 De Havilland Engine Co Ltd filed Critical De Havilland Engine Co Ltd
Priority to FR857575A priority Critical patent/FR1285627A/fr
Application granted granted Critical
Publication of FR1285627A publication Critical patent/FR1285627A/fr
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/52—Toroidal combustion chambers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • 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
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/062—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with aft fan
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
FR857575A 1961-03-31 1961-03-31 Groupe moteur à turbine à gaz Expired FR1285627A (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR857575A FR1285627A (fr) 1961-03-31 1961-03-31 Groupe moteur à turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR857575A FR1285627A (fr) 1961-03-31 1961-03-31 Groupe moteur à turbine à gaz

Publications (1)

Publication Number Publication Date
FR1285627A true FR1285627A (fr) 1962-02-23

Family

ID=8752238

Family Applications (1)

Application Number Title Priority Date Filing Date
FR857575A Expired FR1285627A (fr) 1961-03-31 1961-03-31 Groupe moteur à turbine à gaz

Country Status (1)

Country Link
FR (1) FR1285627A (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1233660B (de) * 1963-01-31 1967-02-02 Rolls Royce Ringfoermige Verbrennungsanlage fuer Gasturbinenstrahltriebwerke
DE1234096B (de) * 1962-11-14 1967-02-09 Saurer Ag Adolph Gasturbinenanlage
DE1256483B (de) * 1963-12-03 1967-12-14 Rolls Royce Gasturbinenstrahltriebwerk
FR2948735A1 (fr) * 2009-07-30 2011-02-04 Turbomeca Diffuseur d'air en sortie d'un compresseur centrifuge de turbomachine avec canal de retour a 180°
DE102011113784A1 (de) * 2011-09-17 2013-06-27 Diyan Petrov Petrov Scheibenform Turbokompressor

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1234096B (de) * 1962-11-14 1967-02-09 Saurer Ag Adolph Gasturbinenanlage
DE1233660B (de) * 1963-01-31 1967-02-02 Rolls Royce Ringfoermige Verbrennungsanlage fuer Gasturbinenstrahltriebwerke
DE1256483B (de) * 1963-12-03 1967-12-14 Rolls Royce Gasturbinenstrahltriebwerk
FR2948735A1 (fr) * 2009-07-30 2011-02-04 Turbomeca Diffuseur d'air en sortie d'un compresseur centrifuge de turbomachine avec canal de retour a 180°
DE102011113784A1 (de) * 2011-09-17 2013-06-27 Diyan Petrov Petrov Scheibenform Turbokompressor

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