A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one rotor and at least one blade extending radially outwardly from the rotor to a radially outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip of the blade. The blade outer air seal has forward and aft hooks. The forward and aft hooks support the blade outer air seal. The blade outer air seal is formed with a central web. The forward and aft hooks extending from the central web at a T-joint. There is a pair of mating inner laminate at the T-joint each having an axially extending portion and a vertically extending portion. The pair of mating inner laminates have an interwoven connection. A method is also disclosed.

A component for a gas turbine engine including a core and an outer enclosure. The core includes an exterior surface extending along a length between a first end and a second end and at least partially defines a cooling cavity on the exterior surface extending from the first end along at least a portion of the length. The cooling cavity is fluidly coupled to an air supply at the first end. The outer enclosure includes an outer surface. The outer enclosure is positioned outside the core and extends from the first end of the core along at least a portion of the length of the core and at least partially defines the cooling cavity.

A holding device including a ceramic member formed of a sintered ceramic material containing aluminum nitride as a main component, a heating resistor element formed of a metal and disposed in the ceramic member, an electrically conductive electricity supply connection member in contact with the heating resistor element, and an electrically conductive electricity supply terminal electrically connected to the electricity supply connection member. The holding device holds an object on the surface of the ceramic member. In the holding device, at least a portion of the surface of the electricity supply connection member, excluding its contact surface for contact with the heating resistor element and its connection surface for connection with the electricity supply terminal, is covered with a coat layer formed of a nitride containing at least one of Al, Ti, Zr, V, Ta, and Nb. Also disclosed is a method of manufacturing the holding device.

An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a plurality of cooling passages that extend from the cooling cavity through the airfoil.

A holding device including a ceramic member formed of a sintered ceramic material containing aluminum nitride as a main component, a heating resistor element formed of a metal and disposed in the ceramic member, and an electrically conductive electricity supply member in contact with the heating resistor element. The holding device holds an object on the surface of the ceramic member. In the holding device, at least a portion of the surface of the heating resistor element, excluding its contact surface for contact with the electricity supply member, is covered with a coat layer formed of a nitride containing at least one of Al, Ti, Zr, V, Ta, and Nb. Also disclosed is a method of manufacturing the holding device.

The present invention relates to a sealing lid for a package containing an optical element. For the sealing lid, a translucent material such as glass that can transmit light such as visible light is used. The present invention includes a lid main body made of the translucent material. The lid main body includes a joining region having a frame shape corresponding to an outer circumferential shape of the lid main body. A plurality of pieces of brazing material made of a eutectic alloy are fused on the joining region of the lid main body. An arrangement state of the brazing material includes aligning spherical pieces of brazing material continuously to form a frame shape along the joining region.

The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.

A super hard polycrystalline construction has a first region having a body of thermally stable polycrystalline super hard material with an exposed surface forming a working surface, and a peripheral side edge, a second region forming a substrate to the first region and a third region interposed between the first and second regions. The third region extends across a surface of the second region along an interface and has a composite material having a first phase comprising a plurality of non-intergrown diamond grains, the majority of the diamond grains having a coating comprising nano-sized BN particles. There is also disclosed a method of making such a construction.

The present invention relates to a method for the automated production of a workpiece having at least one diaphragm, including a workpiece for an electrochemical sensor, including providing a workpiece that has a wall with at least one continuous opening through the wall, wherein a diaphragm body is affixed in the at least one opening, such that the diaphragm body completely fills a cross-section of the opening, and processing the diaphragm body by means of a laser.

A method of preparing a ceramic matrix composite (CMC) component that includes a protective ceramic layer comprises adhering at least one flexible ceramic tape to a ceramic fiber preform, where the at least one flexible ceramic tape comprises ceramic particles dispersed in an organic binder phase. After the adhering, the at least one flexible ceramic tape is heated to a temperature sufficient to volatilize the organic binder phase, thereby forming a porous ceramic layer on at least a portion of the ceramic fiber preform. After the heating and volatilizing, the ceramic fiber preform and the porous ceramic layer are infiltrated with a molten material, thereby forming a CMC component including, on at least a portion thereof, a protective ceramic layer.