GB1410137A - Gas turbine engines - Google Patents

Gas turbine engines

Info

Publication number
GB1410137A
GB1410137A GB5099673A GB5099673A GB1410137A GB 1410137 A GB1410137 A GB 1410137A GB 5099673 A GB5099673 A GB 5099673A GB 5099673 A GB5099673 A GB 5099673A GB 1410137 A GB1410137 A GB 1410137A
Authority
GB
United Kingdom
Prior art keywords
skin
skins
wall
chamber
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.)
Expired
Application number
GB5099673A
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.)
Avco Corp
Original Assignee
Avco Corp
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 Avco Corp filed Critical Avco Corp
Priority to GB5099673A priority Critical patent/GB1410137A/en
Priority to FR7341289A priority patent/FR2251706B1/fr
Publication of GB1410137A publication Critical patent/GB1410137A/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
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/54—Reverse-flow combustion chambers
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1410137 Gas turbine engine combustion equipment AVCO CORP 2 Nov 1973 50996/73 Heading F1L The invention relates to a gas turbine engine and to means for cooling the wall of a duct thereof through which hot gases from the combustion section flow. The engine shown comprises a reverse flow type combustion chamber the gases discharging through an annular outlet of U-shape defined between an outer wall 30 and an inner wall 28. The outer wall is formed by an outer skin 38 and an inner skin 39 which are spaced apart to define a chamber 42 through which cooling air is arranged to flow. The skins 38, 39 are connected at their outer ends to a ring member 40, and are connected together at their inner ends. The skins are spaced apart by means of dimples 56 formed on the outer skin 38, cooling air flowing into the chamber 42 between the skins through openings 54 in the outer skin, and discharging into the gas flow through openings 55 in the inner skin. In Fig.3 the cooling air chamber is again formed by inner and outer skins 64, 62 but an intermediate skin 66 is disposed therebetween, the dimples 76 being formed in this embodiment on the intermediate skin.
GB5099673A 1973-11-02 1973-11-02 Gas turbine engines Expired GB1410137A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB5099673A GB1410137A (en) 1973-11-02 1973-11-02 Gas turbine engines
FR7341289A FR2251706B1 (en) 1973-11-02 1973-11-20

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB5099673A GB1410137A (en) 1973-11-02 1973-11-02 Gas turbine engines
FR7341289A FR2251706B1 (en) 1973-11-02 1973-11-20

Publications (1)

Publication Number Publication Date
GB1410137A true GB1410137A (en) 1975-10-15

Family

ID=26218036

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5099673A Expired GB1410137A (en) 1973-11-02 1973-11-02 Gas turbine engines

Country Status (2)

Country Link
FR (1) FR2251706B1 (en)
GB (1) GB1410137A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2624954A1 (en) * 1987-12-18 1989-06-23 Rolls Royce Plc COMBUSTION CHAMBER STRUCTURE FOR A GAS TURBINE ENGINE
EP1426558A2 (en) * 2002-11-22 2004-06-09 General Electric Company Gas turbine transition piece with dimpled surface and cooling method for such a transition piece

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2624954A1 (en) * 1987-12-18 1989-06-23 Rolls Royce Plc COMBUSTION CHAMBER STRUCTURE FOR A GAS TURBINE ENGINE
GB2219653A (en) * 1987-12-18 1989-12-13 Rolls Royce Plc Combustors for gas turbine engines.
GB2219653B (en) * 1987-12-18 1991-12-11 Rolls Royce Plc Improvements in or relating to combustors for gas turbine engines
EP1426558A2 (en) * 2002-11-22 2004-06-09 General Electric Company Gas turbine transition piece with dimpled surface and cooling method for such a transition piece
EP1426558A3 (en) * 2002-11-22 2005-02-09 General Electric Company Gas turbine transition piece with dimpled surface and cooling method for such a transition piece

Also Published As

Publication number Publication date
FR2251706B1 (en) 1976-05-07
FR2251706A1 (en) 1975-06-13

Similar Documents

Publication Publication Date Title
GB1459591A (en) Combustion equipment
GB1414412A (en) Chamber assembly for use in a continuous combustion process
GB1422982A (en) Gas turbine engine
GB1458054A (en) Gas turbine engines including exhaust reheat combustion equipment
GB1424197A (en) Combustion chambers for gas turbine engines
GB1427146A (en) Combustion apparatus for gas turbine engines
GB1247144A (en) Combustion chambers, especially for use in gas turbine engines
FR2372965A1 (en) PERFECTED DIFFUSER FOR GAS TURBINE ENGINE
GB1438379A (en) Cooling arrangement for duct walls
GB1437397A (en) Gas turbine engine fuel distribution systems
GB1179166A (en) An Annular Combustion Chamber for a Gas Turbine Engine.
GB1344359A (en) Combustion equipment for gas turbine engines
GB1128431A (en) Internal combustion engine turbocharger
GB1040390A (en) Gas turbine engine
GB1429677A (en) Gas turbine engine combustion equipment
GB1425438A (en) Combustion apparatus air supply of gas turbine engines
GB970189A (en) Combustion equipment for a gas turbine engine
GB983945A (en) Improvements in gas turbine engine exhaust system
GB1410137A (en) Gas turbine engines
GB798865A (en) Improvements in and relating to combustion systems for axial-flow gas turbine engines and ram jet engines
GB1442350A (en) Gas turbine engine combustion equipment
GB1354333A (en) Regenerative gas turbine engines
GB1121361A (en) Improvements in fluid mixing apparatus
GB1533177A (en) Gas turbine engine
GB1397296A (en) Combustion apparatus especially for gas turbine engines

Legal Events

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