Abstract: An assembly of a rotating component and a rotationally stationary component includes a first bearing portion located at the rotating component and rotatable therewith, and a second bearing portion located at the rotationally stationary component. The second bearing portion is supported at the rotationally stationary component and rotatably with the rotating component when in contact with the first bearing portion. The first bearing portion and the second bearing portion define a single point contact therebetween.

Abstract: An assembly of a rotating component and a rotationally stationary component includes a first bearing portion located at the rotating component and rotatable therewith, and a second bearing portion located at the rotationally stationary component. The second bearing portion is supported at the rotationally stationary component and rotatably with the rotating component when in contact with the first bearing portion. The first bearing portion and the second bearing portion define a single point contact therebetween.

Abstract: Aspects of the disclosure are directed to an active clearance control system for an engine of an aircraft, comprising: a collector that is configured to receive a cooling fluid, at least two manifolds coupled to the collector, where a first of the manifolds is configured to receive at least a first portion of the cooling fluid from the collector and a second of the manifolds is configured to receive at least a second portion of the cooling fluid from the collector, and an insert coupled to the collector and the manifolds, where the insert is configured to seal an interface between the collector and the at least two manifolds over an operating range of the engine.

Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.

Abstract: Aspects of the disclosure are directed to an active clearance control system for an engine of an aircraft, comprising: a collector that is configured to receive a cooling fluid, at least two manifolds coupled to the collector, where a first of the manifolds is configured to receive at least a first portion of the cooling fluid from the collector and a second of the manifolds is configured to receive at least a second portion of the cooling fluid from the collector, and an insert coupled to the collector and the manifolds, where the insert is configured to seal an interface between the collector and the at least two manifolds over an operating range of the engine.

Abstract: A rotor disk assembly comprises a circular body configured to rotate about an axis, a contoured slot formed partially through the circular body in an axial direction, and a protrusion extending radially from the circular body adjacent the contoured slot. A turbine or compressor assembly is also provided. The turbine or compressor assembly may include a first disk configured to rotate about an axis, a first contoured slot formed partially through the first disk, a first protrusion adjacent to the first contoured slot and extending radially outward from the first disk, and a first blade disposed in the first contoured slot and configured to engage the first protrusion.

Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.

Abstract: A sealing system for sealing a gap between a first body and a second body includes a first seal having a first portion adapted to be attached to the first body and a second portion extending into the gap. The sealing system also includes a second seal. The second seal has a first portion adapted to be attached to the second body and a second portion extending across the gap. The second portion of the first seal and the second portion of the second seal are adjacent and overlapping with each other to seal the gap.

Abstract: A turbine blade includes a platform, an airfoil located on one side of the platform, and a base located on an opposite side of the platform. The base includes an attachment portion that is receivable in a blade retention slot of a turbine disk and a shelf located outside the turbine disk. The shelf includes a mistake proof feature that projects from an outer surface of the shelf.

Abstract: A sealing system for sealing a gap between a first body and a second body includes a first seal having a first portion adapted to be attached to the first body and a second portion extending into the gap. The sealing system also includes a second seal. The second seal has a first portion adapted to be attached to the second body and a second portion extending across the gap. The second portion of the first seal and the second portion of the second seal are adjacent and overlapping with each other to seal the gap.

Abstract: A turbine blade includes a platform, an airfoil located on one side of the platform, and a base located on an opposite side of the platform. The base includes an attachment portion that is receivable in a blade retention slot of a turbine disk and a shelf located outside the turbine disk. The shelf includes a mistake proof feature that projects from an outer surface of the shelf.

Abstract: A pump/flow guide is positioned in a gas turbine engine and attached to a transition duct to face a turbine disk. The pump/flow guide provides a smooth path for guiding purge flow to resist the ingestion of hot gas. One leg of the pump/flow guide extends radially outwardly and contacts the radially inner section of the transition duct that forms a “fish mouth.” Spaced tabs on the pump/flow guide receive bolts to secure the pump/flow guide to the transition duct. The pump/flow guide thus provides a relatively smooth flow passage for purge gas flow.

Abstract: A gas turbine engine includes a turbine rotor and a compressor, which provides discharge air. A nozzle, typically referred to a tangential on-board injector (TOBI), is arranged near the rotor to deliver the discharge air near the turbine rotor for cooling it. The TOBI receives pollution air leaking past seals within the gas turbine engine. The TOBI swirls the discharge air and the pollution air before it reaches the turbine rotor. The TOBI provides multiple passages separated by vanes. At least some of the passages include discharge inlets and outlets for carrying the discharge air from the compressor to the turbine rotor. Typically, several of the passages are unused and blocked. However, the example arrangement provides a pollution inlet and outlet in at least one of the normally unused, blocked passages.

Abstract: A system for optimizing cooling air supply pressure includes a high pressure fluid source which receives bleed air from the exit of a high pressure compressor and a nozzle and ejector assembly for supplying fluid to a point of use at a pressure sufficient to maintain a required cooling airflow and backflow margin at the point of use, and for reducing leakage of the cooling fluid between the high pressure source and the point of use.

Abstract: A system for optimizing cooling air supply pressure includes a high pressure fluid source which receives bleed air from the exit of a high pressure compressor and a nozzle and ejector assembly for supplying fluid to a point of use at a pressure sufficient to maintain a required cooling airflow and backflow margin at the point of use, and for reducing leakage of the cooling fluid between the high pressure source and the point of use.