Title:
SWING GEAR AND FUEL INJECTOR
Document Type and Number:
Japanese Patent JPH01182530
Kind Code:
A
Abstract:
PURPOSE: To realize enlargement of an operation area of a gas turbine by arrange a fuel injector body at the center of annular flow directing means, disposing a primary and a secondary air swirlers between the injector body and the annular flow directing means through an annular member. CONSTITUTION: A gas turbine for aircraft has a combustor receiving the supply of compressed air and the combustor comprises a plurality of fuel injectors 36 arranged in a peripheral direction around an annular dome defining an annular combustion chamber. In this case, each of the fuel injectors 36 is provided with a swirler including a barrel 46 which is open at both ends to serve as an annular flow directing means. A fuel injector body 48 is arranged along a central axis of the barrel 46 via an annular member 50. A primary air swirler means 58 and a secondary air swirler means 60 are disposed in an inner annulus 54 and an outer annulus 52 of the annular member 50. Then, primary fuel is supplied from a fuel pipe 40 to a fuel-atomizing nozzle 62 and secondary fuel is supplied from a fuel, pipe 42 through conduit means 64 to the outer annulus 52.
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Inventors:
JIYON UIRIAMU BINSON
SUTEFUAN JIYON HOOUERU
ERIASU HARII RAMUPESU
SUTEFUAN JIYON HOOUERU
ERIASU HARII RAMUPESU
Application Number:
JP22892388A
Publication Date:
July 20, 1989
Filing Date:
September 14, 1988
Export Citation:
Assignee:
GEN ELECTRIC
International Classes:
F23C7/00; F02C7/232; F23D17/00; F23R3/14; F23R3/34; (IPC1-7): F02C7/232
Attorney, Agent or Firm:
Tokunji Ikunuma