GB1397296A - Combustion apparatus especially for gas turbine engines - Google Patents

Combustion apparatus especially for gas turbine engines

Info

Publication number
GB1397296A
GB1397296A GB4284272A GB4284272A GB1397296A GB 1397296 A GB1397296 A GB 1397296A GB 4284272 A GB4284272 A GB 4284272A GB 4284272 A GB4284272 A GB 4284272A GB 1397296 A GB1397296 A GB 1397296A
Authority
GB
United Kingdom
Prior art keywords
wall
air
ribs
fuel
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
GB4284272A
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of GB1397296A publication Critical patent/GB1397296A/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
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • 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)
  • Testing Of Engines (AREA)

Abstract

1397296 Gas turbine engine combustion equipment SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 15 Sept 1972 [16 Sept 1971] 42842/72 Heading FIL The invention relates to combustion apparatus for example of a gas turbine engine in which fuel and air may be passed through a hollow duct into the combustion space whereby the fuel is vaporized the air and vaporized fuel burning upon discharge from the duct to form a stream of hot gases which impinge on the wall of the combustion chamber. The wall of the combustion chamber externally of the region of impingement may be provided with cooling ribs and cooling air is directed thereon. The apparatus shown comprises an annular air casing 2a, 2b and an annular flame tube 3a, 3b disposed therein, the upstream end of the flame tube comprising a wall 7, a wall 12 spaced upstream of the wall 7 to define a space 13, and a dome portion 11 integral with the wall 12 and formed with an air inlet opening 15. A series of fuel vaporizing units 20 is supported within the walls 7 and 12 by means of sleeves 9 integral with the wall 7, each unit being of T-form and formed with inlet 24 and outlets 29, 30. Air passes into the vaporizing unit as indicated by flow arrows f 1 , Fig.1, and fuel is supplied thereto through duct 25, the air and vaporized fuel discharging from the outlets 29, 30 as indicated by arrows A, Fig.3, the mixture igniting upon discharge and the combustion gases impinging on the regions indicated at B of the wall 7. The external surface of the wall D corresponding to the regions B is formed with series of cooling ribs 31 and cooling air is directed on to the ribs as indicated by the flow arrows C, Fig.3, through openings 32 formed in the wall 12; after impinging against the ribs the cooling air discharges from the space 13 through openings 33 into the flame tube. In the first embodiment a single air flow opening 32 is associated with each set of ribs 31 whereas in a second embodiment a plurality of small openings is associated with each set of ribs.
GB4284272A 1971-09-16 1972-09-15 Combustion apparatus especially for gas turbine engines Expired GB1397296A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7133401A FR2152465B1 (en) 1971-09-16 1971-09-16

Publications (1)

Publication Number Publication Date
GB1397296A true GB1397296A (en) 1975-06-11

Family

ID=9083052

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4284272A Expired GB1397296A (en) 1971-09-16 1972-09-15 Combustion apparatus especially for gas turbine engines

Country Status (3)

Country Link
DE (1) DE2245464C2 (en)
FR (1) FR2152465B1 (en)
GB (1) GB1397296A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2161914A (en) * 1980-12-10 1986-01-22 Rolls Royce Combustion equipment for a gas turbine engine
GB2223839A (en) * 1988-10-12 1990-04-18 United Technologies Corp Gas turbine combustor bulkhead heat shield assembly

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2312654A1 (en) * 1975-05-28 1976-12-24 Snecma COMBUSTION CHAMBERS IMPROVEMENTS FOR GAS TURBINE ENGINES
GB1552132A (en) * 1975-11-29 1979-09-12 Rolls Royce Combustion chambers for gas turbine engines
GB9018013D0 (en) * 1990-08-16 1990-10-03 Rolls Royce Plc Gas turbine engine combustor
FR2896304B1 (en) * 2006-01-16 2013-01-18 Snecma TURBOMACHINE COMBUSTION CHAMBER TRANSVERSAL ANNULAR ROOF

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2974485A (en) * 1958-06-02 1961-03-14 Gen Electric Combustor for fluid fuels
GB1135670A (en) * 1966-04-20 1968-12-04 Rolls Royce Combustion chamber for a gas turbine engine
FR1569142A (en) * 1968-05-07 1969-05-30

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2161914A (en) * 1980-12-10 1986-01-22 Rolls Royce Combustion equipment for a gas turbine engine
US4610135A (en) * 1980-12-10 1986-09-09 Rolls-Royce Plc Combustion equipment for a gas turbine engine
GB2223839A (en) * 1988-10-12 1990-04-18 United Technologies Corp Gas turbine combustor bulkhead heat shield assembly

Also Published As

Publication number Publication date
FR2152465B1 (en) 1975-02-21
FR2152465A1 (en) 1973-04-27
DE2245464A1 (en) 1973-03-22
DE2245464C2 (en) 1982-05-13

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee