Patent ID: 6425240
Filing Date: 2002-07-30
Classification: F23R

Abstract:
A gas turbine combustor, comprising:a) a combustion chamber having first and second, hollow, chamber portions at least partly overlapping each other and being mounted for telescoping movement relative to each other along an axis between end-limiting positions; b) an air supply manifold having primary and secondary air inlets spaced apart along the axis and being together operative for supplying air to the combustion chamber, the primary inlet having a variable cross-sectional area through which a primary part of the air flows into the combustion chamber, the secondary inlet being located at an overlapping region of the chamber portions and having a variable cross-sectional area through which a secondary part of the air flows into the combustion chamber; c) a fuel injector for injecting fuel to the primary part of the air flowing into the combustion chamber; d) a burner for combustion the fuel and the air within the combustion chamber; and e) an actuator means for moving the chamber portions relative to each other in opposite directions along the axis between the end-limiting positions, and for varying the cross-sectional areas of the primary and secondary inlets in inverse proportion to each other during movement of the chamber portions.