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A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for re

A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes 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 includes 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 terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening.

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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;

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. 2. The gas turbine engine of claim 1, wherein the base wall, the inboard wall, and the end wall are integrally formed with one another. 3. The gas turbine engine of claim 1, wherein the contoured shroud is mounted within the internal cavity with a bolt, the opening having a size sufficient to allow installation access to the bolt. 4. The gas turbine engine of claim 1, wherein the opening is a hole at a distance from the free edge. 5. The gas turbine engine of claim 1, wherein the opening is a scallop formed at the free edge. 6. The gas turbine engine of claim 5, wherein the scallop is configured to relieve thermal stress in the contoured shroud. 7. The gas turbine engine of claim 1, wherein contoured shroud further includes a deflector at the opening. 8. The gas turbine engine of claim 7, wherein the internal engine cavity is provided with a cooling air flow. 9. The gas turbine engine of claim 8, wherein the deflector directs the cooling air flow into the hot gas recirculation pocket through the opening. 10. The gas turbine engine of claim 7, wherein the deflector is positioned on an upstream edge of the opening and projects into the hot gas recirculation pocket. 11. The gas turbine engine of claim 7, wherein the deflector deflects the combustion gases out of the hot gas recirculation pocket. 12. The gas turbine engine of claim 11, wherein the deflector is positioned on an upstream edge of the opening and projects into the internal engine cavity. 13. The gas turbine engine of claim 1, wherein the combustion gas has areas of high pressure and low pressure, and wherein the opening corresponds to one of the areas of low pressure. 14. A gas turbine, 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 circumferentially extending row of stator vanes mounted on the housing within the hot gas flow path at a position generally at the upstream side of the annular space in the duct wall relative to the direction of combustion gas flow through the hot gas flow path;a turbine rotor including a rotor disk rotatably supported within the internal engine cavity with a periphery of the rotor disk disposed generally within the annular space formed in the duct wall, and a plurality of rotor blades on the disk periphery and disposed generally within the hot gas flow path; anda contoured shroud mounted within the internal engine cavity in close running clearance with the rotor disk at the disk periphery, the shroud defining a radially outwardly open and circumferentially extending 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 additionally defining an attachment access opening. 15. The gas turbine of claim 14, wherein the contoured shroud includes 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 disk, and an end wall extending from the inboard wall in a radially outward direction and in close running clearance with the rotor disk, the end wall terminating in a circumferentially extending free edge disposed in close proximity to the annular space in the duct wall, the end wall defining the attachment access opening. 16. The gas turbine of claim 15, wherein the base wall, the inboard wall, and the end wall are integrally formed with one another. 17. The gas turbine of claim 15, wherein the attachment access opening is a hole at a distance from the free edge. 18. The gas turbine of claim 15, wherein the attachment access opening is a scallop formed at the free edge. 19. The gas turbine of claim 14, wherein contoured shroud further includes a deflector at the annular space. 20. 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, the contoured shroud further including a deflector at the opening that directs cooling air flow from the internal engine cavity into the hot gas recirculation pocket through the opening.