Abstract: A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.

Abstract: A turbine blade outer air seal assembly includes a hot side exposed to a combustion hot gas flow, and a back side that is exposed to a supply of cooling air. The outer air seal segment includes a trailing edge cavity and a leading edge cavity separated by a divider. The cavities are feed cooling air through a plurality of inlet openings disposed transverse to the gas flow. The cooling air enters the cavities and flows toward a plurality of outlets at the leading edge and a plurality of outlets along the trailing edge. A plurality of pedestals within each of the cavities disrupts cooling air flow to increase heat absorption capacity and to increase the surface area capable of transferring heat from the hot side.

Abstract: A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.

Abstract: Air cooling passages for a gas turbine engine component, and in particular, a blade outer air seal, are provided with a filtering technique to filter impurities before they can reach a metering location. The air filtering techniques include the provision of a plurality of openings which each have a small cross-sectional area when compared to the cross-sectional area of the metering location. These small openings will filter out impurities before they reach the metering location. The metering location has a cross-sectional area that is greater than the cross-sectional area of any one of the openings, however, the total cross-sectional area of the plurality of openings exceeds the cross-sectional area of the metering location such that adequate air is supplied even if several of the openings are clogged.

Abstract: A turbine blade outer air seal assembly includes a hot side exposed to a combustion hot gas flow, and a back side that is exposed to a supply of cooling air. The outer air seal segment includes a trailing edge cavity and a leading edge cavity separated by a divider. The cavities are feed cooling air through a plurality of inlet openings disposed transverse to the gas flow. The cooling air enters the cavities and flows toward a plurality of outlets at the leading edge and a plurality of outlets along the trailing edge. A plurality of pedestals within each of the cavities disrupts cooling air flow to increase heat absorption capacity and to increase the surface area capable of transferring heat from the hot side.

Abstract: A material having improved hardness characteristics and bearing, lower friction coefficient and increased service life in clusters of sliding friction contains powder of copper, iron, phosphorus, graphite, dust of disulphide of molybdenum and steel substrate made out of low carbohydrate steel. The material has a bimetal structure with granules inserted in a matrix. The material of the invention is especially useful in the machine-building industry, particularly for the production of blocks for units of sliding friction in machines, mechanisms and equipment.