FR2438166A1 - IMPROVED GAS TURBINE ENGINE - Google Patents

IMPROVED GAS TURBINE ENGINE

Info

Publication number
FR2438166A1
FR2438166A1 FR7924380A FR7924380A FR2438166A1 FR 2438166 A1 FR2438166 A1 FR 2438166A1 FR 7924380 A FR7924380 A FR 7924380A FR 7924380 A FR7924380 A FR 7924380A FR 2438166 A1 FR2438166 A1 FR 2438166A1
Authority
FR
France
Prior art keywords
temperature
fixed blades
combustion chamber
hot gas
gas turbine
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.)
Granted
Application number
FR7924380A
Other languages
French (fr)
Other versions
FR2438166B1 (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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of FR2438166A1 publication Critical patent/FR2438166A1/en
Application granted granted Critical
Publication of FR2438166B1 publication Critical patent/FR2438166B1/en
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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

MOTEUR PRESENTANT UNE REPARTITION PERIPHERIQUE PRESELECTIONNEE DE LA TEMPERATURE DES GAZ CHAUDS DANS LE PLAN DE SORTIE DE LA CHAMBRE DE COMBUSTION. IL COMPREND UNE CHEMISE INTERIEURE 48 ET UNE CHEMISE EXTERIEURE 50, DE CHAMBRE DE COMBUSTION, ET UN MOYEN DISPOSE EN AMONT DES AUBES FIXES 46, SOUS LA FORME D'OUVERTURES 78 ET 80 POUR L'ADMISSION D'AIR DANS LA CHAMBRE DE COMBUSTION DE FACON A CREER UNE REPARTITION DE LA TEMPERATURE AU NIVEAU DES AUBES FIXES TELLE QUE LES GAZ CHAUDS S'ECOULANT DANS LES ESPACES 84 LIMITES PAR LES AUBES FIXES 46 ONT UNE TEMPERATURE SUPERIEURE A LA TEMPERATURE MOYENNE D'ENTREE DANS LA TURBINE ET LES GAZ CHAUDS HEURTANT LE BORD D'ATTAQUE 82 DES AUBES FIXES 46 ETANT A UNE TEMPERATURE INFERIEURE A CETTE TEMPERATURE MOYENNE D'ENTREE. APPLICATION AUX MOTEURS D'AVION.ENGINE WITH A PRESELECTED PERIPHERAL DISTRIBUTION OF HOT GAS TEMPERATURE IN THE COMBUSTION CHAMBER EXIT PLANE. IT INCLUDES AN INTERNAL SHIRT 48 AND AN EXTERNAL SHIRT 50, OF COMBUSTION CHAMBER, AND A MEDIUM HAS FIXED BLADES 46, IN THE FORM OF OPENINGS 78 AND 80 FOR THE ADMISSION OF AIR INTO THE COMBUSTION CHAMBER OF WAY TO CREATE A TEMPERATURE DISTRIBUTION AT THE LEVEL OF THE FIXED BLADES SUCH AS THE HOT GAS FLOWING INTO THE SPACES 84 BOUNDARED BY THE FIXED BLADES 46 HAVE A TEMPERATURE GREATER THAN THE AVERAGE ENTRY TEMPERATURE INTO THE HOT GAS AND TURBINE HOT THE LEADING EDGE 82 OF THE FIXED BLADES 46 BEING A TEMPERATURE LOWER THAN THIS AVERAGE ENTRY TEMPERATURE. APPLICATION TO AIRCRAFT ENGINES.

FR7924380A 1978-10-02 1979-10-01 IMPROVED GAS TURBINE ENGINE Expired FR2438166B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US94791978A 1978-10-02 1978-10-02

Publications (2)

Publication Number Publication Date
FR2438166A1 true FR2438166A1 (en) 1980-04-30
FR2438166B1 FR2438166B1 (en) 1986-07-11

Family

ID=25486990

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7924380A Expired FR2438166B1 (en) 1978-10-02 1979-10-01 IMPROVED GAS TURBINE ENGINE

Country Status (6)

Country Link
JP (1) JPS5560625A (en)
CA (1) CA1148755A (en)
DE (1) DE2939563A1 (en)
FR (1) FR2438166B1 (en)
GB (1) GB2030653B (en)
IT (1) IT1165348B (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2727193B1 (en) * 1994-11-23 1996-12-20 Snecma TWO-HEAD COMBUSTION CHAMBER OPERATING AT FULL GAS SLOW MOTION
US7234304B2 (en) 2002-10-23 2007-06-26 Pratt & Whitney Canada Corp Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine
FR2948987B1 (en) * 2009-08-04 2011-12-09 Snecma TURBOMACHINE COMBUSTION CHAMBER HAVING IMPROVED AIR INLET ORIFICES
CN113950269A (en) * 2019-06-13 2022-01-18 株式会社爱世克私 Shoes with air-permeable layer

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB853108A (en) * 1956-03-26 1960-11-02 Power Jets Res & Dev Ltd Combustion system
GB917704A (en) * 1958-07-31 1963-02-06 Power Jets Res & Dev Ltd Combustion apparatus
GB1239559A (en) * 1966-06-27 1971-07-21

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB980363A (en) * 1961-12-04 1965-01-13 Jan Jerie Improvements in or relating to gas turbines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB853108A (en) * 1956-03-26 1960-11-02 Power Jets Res & Dev Ltd Combustion system
GB917704A (en) * 1958-07-31 1963-02-06 Power Jets Res & Dev Ltd Combustion apparatus
GB1239559A (en) * 1966-06-27 1971-07-21

Also Published As

Publication number Publication date
IT7926087A0 (en) 1979-09-28
FR2438166B1 (en) 1986-07-11
CA1148755A (en) 1983-06-28
GB2030653B (en) 1983-05-05
JPS5560625A (en) 1980-05-07
IT1165348B (en) 1987-04-22
GB2030653A (en) 1980-04-10
JPS6236142B2 (en) 1987-08-05
DE2939563A1 (en) 1980-04-17

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Legal Events

Date Code Title Description
ST Notification of lapse