Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.

Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.

Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.

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 power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support, the heat shield assembly forms an outer diameter directed toward an inner vane platform of the power turbine vane array.

Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.

Abstract: Provided are methods for the preparation of certain substituted pyrrolidine compounds, forms of (2S,4R)-1-(2-aminoacetyl)-4-benzamidopyrrolidine-2-carboxylic acid hydrochloride, and methods for preparing and using these forms.

Abstract: A power turbine section for a gas turbine engine includes an inlet duct upstream of a first power turbine vane array, the inlet duct including a lip.

Abstract: A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support, the heat shield assembly forms an outer diameter directed toward an inner vane platform of the power turbine vane array.

Abstract: A method and system of transmitting data via a computer network to a plurality of end-users. Transmission of successive data units may be prompted by human-operated and/or automated central control. Successive arrays of data units may be transmitted over a plurality of channels, in parallel. Each end-user chooses which channel or channels to receive and may change channels at will. Transmission of successive arrays may coincide with successive occurrences during the course of a live event. Data units also may be transmitted over one or more channels asynchronously with transmissions over other channels. Controller-prompted transmissions, received passively by end-users, also may be integrated with a facility for end-users to browse data sources in a self-directed sequence and pace.

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: Provided are methods for the preparation of certain substituted pyrrolidine compounds, forms of (2S,4R)-1-(2-aminoacetyl)-4-benzamidopyrrolidine-2-carboxylic acid hydrochloride, and methods for preparing and using these forms.

Abstract: According to an embodiment disclosed herein, an apparatus for cooling a rotating part having cooling channels therein, the rotating part attaching to a disk rotating about an axis, the disk having a conduit for feeding a cooling fluid to the cooling channel is described. The apparatus has a first impeller rotating with the disk and in register with the conduit and an outer periphery of the disk, the impeller directing the cooling flow to the conduit.

Abstract: Provided are methods for the preparation of certain substituted pyrrolidine compounds, forms of (2S,4R)-1-(2-aminoacetyl)-4-benzamidopyrrolidine-2-carboxylic acid hydrochloride, and methods for preparing and using these forms.

Abstract: A method and system of transmitting data via a computer network to a plurality of end-users. Transmission of successive data units may be prompted by human-operated and/or automated central control. Successive arrays of data units may be transmitted over a plurality of channels, in parallel. Each end-user chooses which channel or channels to receive and may change channels at will. Transmission of successive arrays may coincide with successive occurrences during the course of a live event. Data units also may be transmitted over one or more channels asynchronously with transmissions over other channels. Controller-prompted transmissions, received passively by end-users, also may be integrated with a facility for end-users to browse data sources in a self-directed sequence and pace.

Abstract: A system and method of transmitting data via a computer network to a plurality of end-users. Transmission of successive data units may be prompted by human-operated and/or automated central control. Successive arrays of data units may be transmitted over a plurality of channels, in parallel. Each end-user chooses which channel or channels to receive and may change channels at will. Transmission of successive arrays may coincide with successive occurrences during the course of a live event. Data units also may be transmitted over one or more channels asynchronously with transmissions over other channels. Controller-prompted transmissions, received passively by end-users, also may be integrated with a facility for end-users to browse data sources in a self-directed sequence and pace.

Abstract: According to an embodiment disclosed herein, an apparatus for cooling a rotating part having cooling channels therein, the rotating part attaching to a disk rotating about an axis, the disk having a conduit for feeding a cooling fluid to the cooling channel is described. The apparatus has a first impeller rotating with the disk and in register with the conduit and an outer periphery of the disk, the impeller directing the cooling flow to the conduit.

Abstract: Provided are methods for the preparation of certain substituted pyrrolidine compounds, forms of (2S,4R)-1-(2-aminoacetyl)-4-benzamidopyrrolidine-2-carboxylic acid hydrochloride, and methods for preparing and using these forms.

Abstract: A rotor for a gas turbine engine comprises an annular body and a plurality of holes. The annular body is configured to rotate in a circumferential direction about an axis extending through a center of the annular body. The annular body comprises an outer diameter surface and an inner diameter surface. The plurality of holes extends through the annular body. Each of the holes comprises an elongate profile in the circumferential direction, and a side wall extending between the outer diameter surface and the inner diameter surface. The side wall is slanted in the circumferential direction.

Abstract: A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a control pocket defined between a radially inner surface and a spaced radially outer surface. The control pockets and their associated knife edge seals create a difficult flow path to prevent leakage into radially inner portions of the turbine section.