GAS TURBINE RING SEGMENT COOLING APPARATUS

摘要

A gas turbine shroud ring segment assembly (36) with an outer structural block (32A) having cooling channels (72) between inlets (60) on a front face and outlets (74, 76) on a front hanger rail (48). The outlets may be positioned on a radially inner surface (77) of the front rail for impingement and forced convection cooling of backsides of radially inner front lips (44) of adjacent shroud ring segments (30A, 30B) mounted on front and rear rails (48, 50) of the block. The outlets may enter a pocket (86) on the inner surface configured to allow coolant flow in all positions of the ring segments (32A, 32B). The cooling channel may form a main channel (72A) and tributary channels (72B, 72C). These channels may be drilled upward from the rail to the inlet. The tributaries may have offset intersections (72E, 72D) with the main channel.

主权项

1. An outer structural block for a shroud ring assembly of a gas turbine engine, comprising:
a shroud ring segment mounting device, and a cooling channel comprising a first outlet on a radially inner surface of a fore element of the shroud ring segment mounting device.