Patent ID: 8206080
Filing Date: 2012-06-26
Classification: F01D,Y02T

Abstract:
1. A gas turbine engine, comprising: a housing including a duct wall and defining a generally annular and axially elongated hot gas flow path for passage of combustion gas, the duct wall separating the hot gas flow path from an internal engine cavity, the duct wall having at least one annular space; a rotor rotatably mounted on an engine shaft for transferring energy from the combustion gas in the hot gas flow path to the engine shaft, the rotor extending from the internal engine cavity, through the annular space of the duct wall, and into the hot flow path; a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path, the contoured shroud comprising a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction, the end wall terminating in a circumferentially extending free edge disposed in proximity to the annular space, the end wall defining an opening.