Gas turbine combustor

摘要

A gas turbine combustor of the present invention comprises a fuel injector for injecting a fuel toward a combustion chamber; a swirler which takes-in compressed air generated in a compressor and swirls the compressed air, in the vicinity of the fuel injector; a tubular guide member for guiding the compressed air taken-in from the swirler, to the combustion chamber; and a heat shield having a cylindrical portion located outward relative to the guide member; wherein the cylindrical portion has a purge hole; and air is introduced through the purge hole and is supplied to a space formed between the guide member and the cylindrical portion.

主权项

1. A gas turbine combustor comprising:
a support member disposed to form a boundary between an interior space of a cowling and an interior space of a combustion tube; a fuel injector for injecting a fuel toward a combustion chamber, which is the interior space of the combustion tube; a swirler which takes in compressed air generated in a compressor and swirls the compressed air in a vicinity of the fuel injector; a tubular guide member for guiding the compressed air taken in from the swirler and an air-fuel mixture of the fuel injected from the fuel injector to the combustion chamber; a heat shield having a cylindrical portion located outward relative to the guide member; and a rear end wall extending radially outward from an upstream end portion of the guide member; wherein the cylindrical portion is fastened to the support member and has a purge hole which is upstream of a location at which the support member is fastened to the cylindrical portion; a first opening of the purge hole faces the interior space of the cowling; a second opening of the purge hole faces an annular space which is communicated with the interior space of the combustion tube and formed by the guide member, the cylindrical portion, and the rear end wall; and air is introduced from the interior space of the cowling through the purge hole and is supplied to the annular space; and a portion which is located at a boundary between the guide member and the rear end wall and faces the annular space has a circular-arc cross-section; the gas turbine combustor further comprising:
a guide section for guiding the air introduced through the purge hole to a region in an obliquely outward direction toward a downstream side;wherein a radial distance between the cylindrical portion and the guide member is greater than a radial distance between the cylindrical portion and the guide section.