Title:
METHOD FOR REDUCING COMBUSTOR PRESSURE CHANGE OF GAS TURBINE ENGINE
Document Type and Number:
Japanese Patent JPH10196954
Kind Code:
A
Abstract:
To reduce an acoustic effect for guiding excess combustor pressure change in a gas turbine engine.
Fuel-air mixture is burnt in a combustor at a downstream of an outlet surface 124 of a fuel nozzle 10. Recirculating regions 200, 300 generated by the nozzle 10 in all operating states of the engine are disposed at an interval to the surface 124, and the combustion product is isolated from the fuel and air of a mixing region 28 of the nozzle 10.
More Like This:
Inventors:
SNYDER TIMOTHY S (US)
SOWA WILLIAM A (US)
SOWA WILLIAM A (US)
Application Number:
JP36523397A
Publication Date:
July 31, 1998
Filing Date:
December 19, 1997
Export Citation:
Assignee:
UNITED TECHNOLOGIES CORP (US)
International Classes:
F02C9/28; F02M61/16; F23C7/00; F23C7/02; F23C9/00; F23D11/36; F23D17/00; F02C7/232; F23R3/12; F23R3/28; F23R3/30; F23R3/34; (IPC1-7): F23R3/28; F02C7/232; F02C9/28; F23C7/02; F23R3/12; F23R3/30; F23R3/34
Attorney, Agent or Firm:
Asakura Shozo
Previous Patent: FUEL NOZZLE ASSEMBLY
Next Patent: METHOD FOR BURNING FUEL IN BURNER OF GAS TURBINE ENGINE
Next Patent: METHOD FOR BURNING FUEL IN BURNER OF GAS TURBINE ENGINE