Patent ID: 6302642
Filing Date: 2001-10-16
Classification: F01D

Abstract:
A heat shield for a gas turbine, which heat shield encloses in an annular manner the moving blades, rotating in the hot-gas duct of the gas turbine, of a stage of the gas turbine and comprising: a plurality of heat-shield segments which are arranged one behind the other in the circumferential direction, are curved in the shape of a segment of a circle and are cooled from outside, and the longitudinal sides of which are designed as correspondingly curved rails running in the circumferential direction and having in each case a pair of arms which project in the axial direction, run in parallel and are at a distance from one another, the heat-shield segments, while forming a cavity to which cooling air can be admitted, are fastened to the inside of an annular carrier, which concentrically surrounds the heat shield in such a way that in each case a radial gap is formed between the longitudinal sides of the heat-shield segments and the adjacent elements which define the hot-gas duct on the outside, wherein cooling holes are provided in both longitudinal sides of the heat-shield segments, through which cooling holes cooling air flows from the cavity into the intermediate spaces formed between the arm pairs and flows from there into the gaps.