GAS TURBINE ENGINE IMPELLER SYSTEM FOR AN INTERMEDIATE PRESSURE (IP) COMPRESSOR

摘要

A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembly includes a diffuser that is attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase. A sealing assembly is attached to the diffuser and is attachable to a transition duct that is positioned to receive air from the diffuser. The sealing assembly is configured to prevent air from passing through the sealing assembly while allowing relative motion to occur between the transition duct and the diffuser.

主权项

1. A gas turbine engine comprising:
a compressor assembly rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller; a shroud covering a bladed portion of the centrifugal impeller; a diffuser attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase; and a sealing assembly attached to the diffuser, wherein the sealing assembly is attachable to a transition duct that is positioned to receive air from the diffuser, and wherein the sealing assembly is configured to prevent air from passing through the sealing assembly while allowing relative motion to occur between the transition duct and the diffuser.