Patent ID: 9079245
Filing Date: 2015-07-14
Classification: B22F,C22C,F01D,F05D

Abstract:
1. A turbine shroud assembly of a gas turbine engine, comprising a plurality of shroud segments disposed circumferentially one adjacent to another, wherein circumferentially adjacent shroud segments have confronting sides defining an inter-segment gap therebetween, and wherein a flow restrictor integrally projects from a first one of said confronting sides of a first shroud segment through the inter-segment gap and into overlapping relationship with a cooperating joint surface provided at a second one of said confronting sides of an adjacent second shroud segment, said flow restrictor and said joint surface defining a clearance therebetween configured to accommodate thermal expansion during hot operating conditions, said clearance and said inter-segment gap being configured to cooperatively define a tortuous leakage path in a generally radial direction between said first and second shroud segments at said hot operating conditions, wherein each of the shroud segments has a shroud body including forward and aft hooks extending from a radially outer surface of a platform having an opposite radially inner hot gas path side surface, and wherein the flow restrictor has a generally axially extending portion integrally projecting from the platform and a generally radially extending portion integrally projecting from at least one of the forward and aft hooks, wherein each of the shroud segments has a metal injection molded (MIM) shroud body, and wherein said flow restrictor forms part of said MIM shroud body.