Patent ID: 9303528
Filing Date: 2016-04-05
CPC Classification: F01D,F05D,Y02T

Claim Text:
1. A mid-turbine frame for a gas turbine engine, the mid-turbine frame comprising: a radially outer case bounding an outer cold section outward of the outer case; a radially inner case bounding an inner cold section inward of the inner case, the radially outer and inner cases defining an annular hot section therebetween; a plurality of load spokes extending radially through the hot section and securing the outer case with the inner case; a vane pack defining a sealed hot gas path axially traversing an annular portion of the hot section; and a thermal radiation shield secured within a generally annular hot section cavity defined outside the sealed hot gas path, the thermal radiation shield including a first mounting base disposed at a first axial end of a shield ring section having at least one ring portion, the first mounting base secured to an aft component mounting surface, such that the shield ring section axially extends from the first mounting base towards a second opposing axial end of the shield ring section within the generally annular hot section cavity, the shield ring section substantially blocking a line of sight between an inner vane pack boundary wall and the inner case; wherein the thermal radiation shield further comprises a second mounting base disposed at a second opposing axial end of the shield ring section; and wherein the second mounting base includes a second flange in contact with the inner case.