Combustor for gas turbine engine

Abstract

A combustor for a gas turbine engine of a lean premixed combustion type, includes: a fuel jetting device configured to jet a premixed fuel into a combustion chamber so that the premixed fuel burns in a premixed combustion zone which is formed in the combustion chamber; and an additive fuel supply unit disposed downstream of the premixed combustion zone so as to additionally supply fuel into the combustion chamber. The additive fuel supply unit includes first and second additive fuel supply devices disposed in a two-stage arrangement such that the second additive fuel supply device is positioned downstream of the first additive fuel supply device.

Description

CROSS REFERENCE TO RELATED APPLICATIONS [0001] This application is based upon the prior Japanese Patent Application No. 2005-308380 filed on Oct. 24, 2005, the entire contents of which are incorporated herein by reference. BACKGROUND OF THE INVENTION [0002] 1. Field of the Invention [0003] The present invention relates to a combustor for a gas turbine engine. More specifically, the present invention relates to a combustor for a gas turbine engine, capable of making the combustor of the gas turbine engine achieve desired stable, low-pollution combustion under partial load. [0004] 2. Description of the Related Art [0005] Private power generation equipment has progressively come into wide use recently, and gas turbine engines are used widely as power units for private power generation equipment. Different time zones have different power demands, respectively, on private power generation equipment. Therefore, private power generation equipment does not operate always in a maximum-load o...

AI Technical Summary

Benefits of technology

[0011] The present invention has been made in view of those problems in the related art and it is therefore an object of the present invention to provide a combustor for a gas turbine engine, capable of achieving stable combustion and of reducing the rate of emission of harmful substances, such as NOx and CO, in a wide range of load without enlarging the gas turbine engine, without complicating the constitution of the gas turbine engine and without reducing the thermal efficiency of the gas turbine engine.

[0016] The combustor according to the present invention for a gas turbine engine achieves desired stable, low-pollution combustion under load varying in a wide load range and discharges an exhaust gas including reduced amount of harmful substances, such as NOx and CO.

Problems solved by technology

Therefore, private power generation equipment does not operate always in a maximum-load operating mode and are often required to operate in a partial-load operating mode.

Although the second method can reduce the rate of NOx emission in a wide range of load on the gas turbine engine even in lean premixed combustion having a narrow stable combustion range, work necessary for extraction reduces the thermal efficiency of the gas turbine engine.

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