Abstract: A faceplate of a showerhead has a bottom side that faces a plasma generation region and a top side that faces a plenum into which a process gas is supplied during operation of a substrate processing system. The faceplate includes apertures formed through the bottom side and openings formed through the top side. Each of the apertures is formed to extend through a portion of an overall thickness of the faceplate to intersect with at least one of the openings to form a corresponding flow path for process gas through the faceplate. Each of the apertures has a cross-section that has a hollow cathode discharge suppression dimension in at least one direction. Each of the openings has a cross-section that has a smallest cross-sectional dimension that is greater than the hollow cathode discharge suppression dimension.

Abstract: A method of connecting hollow elongate members 12 which may be window frame members. The method comprising locating a plastics material insert 16 extending outwardly for a short distance from each hollow member 12, heating the inserts, and bringing the hollow members together such that the heated inserts 16 fuse together to connect the hollow members 12.

Abstract: A seal segment for a gas turbine engine has a radially outer wall with a first length, a radially inner wall with a second length, and a rib member which extends radially between the outer wall and the inner wall and along the first and second lengths.

Abstract: One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: An apparatus including a first component having an exterior surface formed of a ceramic material and including a primary surface region and a plurality of secondary surface regions protruding from the primary surface region, and a second component positioned in contact with at least one of the secondary surface regions and spaced from the primary surface region to define a determinant load path between the first and second components. A method of forming the apparatus is also provided.

Abstract: A seal segment for a gas turbine engine has a radially outer wall with a first length, a radially inner wall with a second length, and a rib member which extends radially between the outer wall and the inner wall and along the first and second lengths.

Abstract: An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and a CMC foam layer bonded to the first CMC sheet. The CMC foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the CMC foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.

Abstract: An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and an open-cell foam layer bonded to the first CMC sheet. The open-cell foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the open-cell foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.

Abstract: An apparatus including a first component having an exterior surface formed of a ceramic material and including a primary surface region and a plurality of secondary surface regions protruding from the primary surface region, and a second component positioned in contact with at least one of the secondary surface regions and spaced from the primary surface region to define a determinant load path between the first and second components. A method of forming the apparatus is also provided.

Abstract: One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A method and system are disclosed where a user network processor gathers video, audio, metadata and tags from a network server site and from contributing network sites, the material having been provided thereto by contribution devices from one or more sources. The user network processor stores contributed material and then manipulates and edits video strings and audio strings provided in the contributed material using a process that reads metadata and tags to automatically collate material from each source and then uses an editing display screen where collated material from each source is displayed in horizontal timelines along a time axis and a cursor co-operates with timeline selection buttons to select one item at a time to be included into an edited version. The selections are displayed by a selection line joining nodes on the display screen.

Abstract: An article of manufacture includes a first ceramic matrix composite (CMC) sheet having a number of flow passages therethrough, and an open-cell foam layer bonded to the first CMC sheet. The open-cell foam layer is an open-cell foam. The article of manufacture includes a second CMC sheet bonded to the open-cell foam layer, the second CMC sheet having a thermal and environmental barrier coating and having a number of flow passages therethrough.

Abstract: A workpiece is processed which includes a multiplicity of recesses formed in the exposed surface. The invention includes depositing a first barrier layer 13 of for example, titanium nitride, a second layer 11 of aluminium alloy and a third relatively thin layer 12 of titanium nitride and then exposing the sandwich of layers to elevated heat and pressure so that the second layer is deformed to fill the recesses 10.