Gas turbine combustor

Abstract

A gas turbine combustor includes a pilot burner, provided at a top portion of a combustion liner having a combustion chamber defined therein, and a main burner of a premixing type disposed adjacent an outer periphery thereof. The pilot burner is provided with an inflow passage, provided in an upstream end portion to allow the compressed air from a radially outer area into a radially inner area, a plurality of fuel supply holes for injecting the fuel into the inflow passage in a direction perpendicular to the flow of the compressed air, a premixing passage for guiding the air-fuel mixture from the inflow passage in an axially downstream direction while the compressed air and the fuel are mixed together, and a plurality of premixed air-fuel mixture injection holes for injecting the premixed air-fuel mixture from the premixing passage into the combustion chamber.

Description

CROSS REFERENCE TO THE RELATED APPLICATION[0001]This application is a continuation application, under 35 U.S.C. §111(a), of international application No. PCT / JP2012 / 070061, filed Aug. 7, 2012, which claims priority to Japanese patent application No. 2011-192549, filed Sep. 5, 2011, the disclosure of which are incorporated by reference in their entirety into this application.BACKGROUND OF THE INVENTION[0002]1. Field of the Invention[0003]The present invention relates to a gas turbine combustor capable of suppressing the emissions of nitrogen oxides (hereinafter referred to as NOx).[0004]2. Description of Related Art[0005]The gas turbine apparatuses are subjected to severe environmental standards regarding the composition of exhaust gases emitted from a turbine during the operation thereof. In particular, reduction of the emissions of NOx contained in the exhaust gases is sought for. As a method of reducing the NOx emission in the gas turbine apparatus, a technique of injecting water ...

AI Technical Summary

Benefits of technology

The present invention aims to provide a gas turbine combustor with a pilot burner that can effectively premix compressed air and fuel to achieve low NOx emissions. The invention includes an annular inflow passage with guide pieces to guide the compressed air towards the center of the passage, where it collides with a larger volume of air inside the passage, enhancing turbulence and facilitating mixing with the fuel. Overall, this design helps achieve efficient and effective premixing of air and fuel to achieve low NOx emissions.

Problems solved by technology

It has, however, been found that in the case of the combustor of a type utilizing the premixing type pilot burner such as disclosed in the above mentioned patent document 1, premixed air-fuel mixture of a kind that is uniformly mixed with even concentration distribution cannot be obtained because the premixing length, in which fuel and a compressed air are mixed, is extremely short.

Accordingly, no leaned premix combustion is ideally performed and, therefore, no satisfactory reduction of the NOx emission is expected.

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