GAS TURBINE COMBUSTOR
PROBLEM TO BE SOLVED: To provide a gas turbine combustor showing a superior structural strength and a reliability even if a clearance at a fuel nozzle is narrow.SOLUTION: In order to accomplish the prescribed problem, a gas turbine combustor of this invention comprises a combustion chamber to which...
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Main Authors | , , |
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Format | Patent |
Language | English Japanese |
Published |
19.01.2017
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Subjects | |
Online Access | Get full text |
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Summary: | PROBLEM TO BE SOLVED: To provide a gas turbine combustor showing a superior structural strength and a reliability even if a clearance at a fuel nozzle is narrow.SOLUTION: In order to accomplish the prescribed problem, a gas turbine combustor of this invention comprises a combustion chamber to which fuel and air are supplied; an air hole plate positioned at an upstream side of the combustion chamber and formed with a plurality of air holes arranged in concentric rows; a plurality of fuel nozzles arranged at an upstream side of each of air holes in the air hole plate so as to supply fuel; a fuel nozzle plate for supporting the fuel nozzles and distributing fuel flowing from the upstream side to the fuel nozzles; and a fuel nozzle unit having a plurality of fuel nozzles integrally supported at one common base, the fuel nozzle unit is connected to the fuel nozzle plate.SELECTED DRAWING: Figure 3
【課題】燃料ノズルの間隔が狭隘であっても、優れた構造強度と信頼性を有するガスタービン燃焼器を得ること。【解決手段】本発明のガスタービン燃焼器は、上記課題を解決を達成するために、燃料と空気が供給される燃焼室と、該燃焼室の上流側に位置し、複数の空気孔が同心円の列状に形成されている空気孔プレートと、該空気孔プレートのそれぞれの空気孔の上流側に配置され、燃料を供給する複数の燃料ノズルと、該燃料ノズルを支持し、かつ、上流側から流入する燃料を前記燃料ノズルに配分する燃料ノズルプレートと、複数の前記燃料ノズルが1つの共通ベースに一体に支持された燃料ノズルユニットとを備え、前記燃料ノズルユニットは、前記燃料ノズルプレートに接合されていることを特徴とする。【選択図】図3 |
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Bibliography: | Application Number: JP20150132432 |