Abstract: An impingement plate for a turbine vane with an integrated cooling flow metering device is disclosed. The impingement plate—which covers the outer end of the vane and allows some cooling air to pass through to the vane's top surface—is re-designed to incorporate an orifice plate for metering the amount of cooling air flow which enters a cooling passage in the vane. The multi-hole orifice pattern in the metering device is designed to optimize the downstream airflow pattern, thus improving heat transfer from the vane to the cooling air. The reduced cooling air flow through the vane results in increased turbine engine efficiency, and the re-designed impingement plate can be used with the existing vane design.

Abstract: An impingement plate for a turbine vane with an integrated cooling flow metering device is disclosed. The impingement plate—which covers the outer end of the vane and allows some cooling air to pass through to the vane's top surface—is re-designed to incorporate an orifice plate for metering the amount of cooling air flow which enters a cooling passage in the vane. The multi-hole orifice pattern in the metering device is designed to optimize the downstream airflow pattern, thus improving heat transfer from the vane to the cooling air. The reduced cooling air flow through the vane results in increased turbine engine efficiency, and the re-designed impingement plate can be used with the existing vane design.

Abstract: A flow control insert for a turbine vane is disclosed. The flow control insert is designed to be placed in a trailing edge cooling passage of the turbine vane to simultaneously reduce cooling air flow and increase heat transfer from the vane to the cooling air, thereby improving efficiency of the turbine via reduced cooling air flow requirement while maintaining vane temperature within a specified range. Two different flow control insert designs are disclosed, where either design fits inside the cooling passage opening and allows an existing vane casting design to be used.

Abstract: An integrated thermal barrier coating and cooling flow metering plate for a turbine vane are disclosed. On an existing vane design, the thickness of the thermal barrier coating is increased in order to provide more thermal protection around the vane material itself. The increased insulation around the vane allows the volume of cooling air flow to be reduced, while still maintaining the vane temperature within specification. The reduced cooling air flow is obtained by adding a flow metering plate at the inlet of a vane trailing edge cooling circuit, thereby increasing turbine efficiency via reduced cooling air flow requirements, while allowing an existing vane casting design to be used.

Abstract: A shroud assembly for a turbine portion of a gas turbine engine, the shroud assembly comprising an annular ceramic shroud ring, a plurality of arcuate shroud support segments, and a plurality of inwardly biased resilient members. The annular ceramic shroud ring is circumferentially disposed about radially extending blades of a turbine rotor and partially defines an annular hot gas passage of the turbine portion. The plurality of arcuate shroud support segments are radially disposed outwardly of the ceramic shroud ring and are contiguous therewith. The plurality of inwardly biased resilient members are each engaged between one of the shroud support segments and an outer annular turbine support case composed of a material having a different thermal expansion coefficient than the ceramic shroud ring. The resilient members maintain contact between the shroud support segments and the ceramic shroud ring.

Abstract: A shroud assembly for a turbine portion of a gas turbine engine, the shroud assembly comprising an annular ceramic shroud ring, a plurality of arcuate shroud support segments, and a plurality of inwardly biased resilient members. The annular ceramic shroud ring is circumferentially disposed about radially extending blades of a turbine rotor and partially defines an annular hot gas passage of the turbine portion. The plurality of arcuate shroud support segments are radially disposed outwardly of the ceramic shroud ring and are contiguous therewith. The plurality of inwardly biased resilient members are each engaged between one of the shroud support segments and an outer annular turbine support case composed of a material having a different thermal expansion coefficient than the ceramic shroud ring. The resilient members maintain contact between the shroud support segments and the ceramic shroud ring.

Abstract: A method and device (1) for applying threads (9) on a support (11) in order o obtain a ply (13) while imparting a sinuous form to the threads. There is used a rotary drum (2) having rows (4A) of fixed teeth (5A) and rows (4B) with movable teeth (5B) which are displaced parallel to the axis of rotation of the drum. Plies obtained with this method or device and articles incorporating such plies, such articles being, for instance, tires.

Abstract: A device (1) making it possible to apply at least one thread (2) to a supt (3) and characterized by the following features:it has a front clamp (4) and a rear clamp (5) along a direction of advance (F.sub.1);it has means (6, 7) for opening and closing said clamps (4, 5);it has means (8) permitting the displacement of the rear clamp (5) in the direction of advance (F.sub.1) or in a direction (F.sub.2) opposite to the direction of advance (F.sub.1); andit has means (9) for displacing the thread (2) in transverse directions.a reinforcing ply for a pneumatic tire having reinforcing threads applied on a support in a sinuous pattern having vertices.

Abstract: A device (1) making it possible to apply at least one thread (2) to a supt (3) and characterized by the following features:it has a front clamp (4) and a rear clamp (5) along a direction of advance (F.sub.1);it has means (6, 7) for opening and closing said clamps (4, 5);it has means (8) permitting the displacement of the rear clamp (5) in the direction of advance (F.sub.1) or in a direction (F.sub.2) opposite to the direction of advance (F.sub.1); andit has means (9) for displacing the thread (2) in transverse directions.The invention also concerns the process used in the device (1) as well as the assemblies obtained with this device (1) and this process, these assemblies being, for instance, reinforcing plies used in pneumatic tires.

Abstract: A ceramic stator vane assembly for a gas turbine engine comprises a plurality of ceramic stator vane segments arranged in an annular array with each vane segment having integral concentric tip and root platform members. The tip and root platform members define continuous inner and outer surfaces for receiving inner and outer ceramic rings. Radial and axial housing members are provided for mounting the stator vane assembly within the engine, and thermal insulation means are provided between the ceramic vane assembly and the housing members.