Patent ID: 7909569
Filing Date: 2011-03-22
Classification: F01D,F05D,Y02T

Abstract:
1. A turbine support case for use in a gas turbine engine, the support case comprising: a first annular portion cantilevered with respect to the gas turbine engine; a second annular portion axially downstream of the first portion relative to a direction of airflow through the engine, the second portion having a downstream end at which the support case is attached to the gas turbine engine; and a third annular portion provided axially between a downstream end of the first portion and an upstream end of the second portion, the third portion connecting the first portion to the second portion such that the turbine support case is defined by sequentially the first annular portion, the third annular portion and the second annular portion along an air flow direction, with the first annular portion cantilevered through the third annular portion and the second annular portion, the third portion having an average wall thickness smaller than an average wall thickness of the first portion or the second portion to provide the support case; the support case having an internal surface facing toward a rotor of gas turbine engine, and an external surface facing away from the rotor of the gas turbine engine, with the first annular portion, the second annular portion and the third annular portion each being made of a single layer of material between the internal surface and the external surface wherein the third portion is made of a material having a larger thermal expansion coefficient than that of at least one among the first portion and the second portion.