Siemens Energy, Inc.

Coi Ceramics, Inc.

Other

Siemens Westinghouse Power Corporation

Siemens Power Generation, Inc.

Composites Horizons, LLC

Composite Horizons, LLC

Thomas Barrett Jackson

Gary Brian Merrill

Jay Alan Morrison

Jeffrey Thomas Hynes

Wilfred Hon

Benjamin Jeffrey Hynes

Christian X Campbell

Yevgeniy P Shteyman

Anthony L Schiavo

Harry A Albrecht

John R Glabe

Andrew Szweda

Andrew B MacFarland

Paul C Kuhl

Todd Willis

Stanley L Houchins

A combination of a component and a composite, the composite having a) a PMC layer, and b) a tile layer comprising a plurality of Ox/Ox CMC tiles, each tile having: i) a central portion, ii) an outer portion and iii) one or more overlap joints formed by the overlapping of the outer portions of adjoining tiles so that hot gases entering a smooth top surface of the tile layer between abutting outer and central periphery segments must travel laterally between the overlapping outer portions of adjoining tiles to reach a top surface of the PMC layer. A method of heat shielding a component with a heat shielding composite comprising a) providing the composite and b) applying the composite to a surface of the component.

Polymer matrix-ceramic matrix hybrid composites for high thermal applications

A composite has a) a PMC layer, and b) a tile layer comprising a plurality of Ox/Ox CMC tiles each has: i) a central portion, ii) an outer portion disposed surrounding the central portion, the bottom surface of the outer portion is disposed flush with the bottom surface of the central portion, the tile layer forms a smooth continuous top surface and a smooth continuous bottom surface, and the tiles are disposed with respect to one another such that each tile is inverted with respect to an adjoining tile, and iii) one or more overlap joints formed by the overlapping of the outer portions of adjoining tiles, so that hot gases entering the smooth top surface of the tile layer between abutting outer and central periphery segments must travel laterally between the overlapping outer portions of adjoining tiles to reach the top surface of the PMC layer.

A method of forming a ceramic matrix composite structure. The method comprises forming at least one prepregged composite material comprising a ceramic fiber preform and a pre-ceramic matrix slurry. The at least one prepregged composite material is placed over at least one surface of a tool using an advanced fiber placement apparatus to form an at least partially uncured composite material structure. The at least partially uncured composite material structure is exposed at least to elevated temperatures to convert the at least partially uncured composite material structure into a ceramic matrix composite structure. A system for forming a ceramic matrix composite structure, an advanced fiber placement apparatus, and a ceramic matrix composite structure are also described.

Methods of forming ceramic matrix composite structures

A method of processing solid core ceramic matrix composite articles. The method improves the physical characteristics of the article by forming the airfoil using a co-processing method wherein a refractory ceramic is cast against a preformed ceramic matrix composite (CMC) shell. In one aspect, the shell is continuous to help prevent delaminations. In another aspect, the shell is open. In one embodiment, the article includes a split line. The split line helps the article to be less susceptible to damage caused from internal strain.

Processing method for solid core ceramic matrix composite airfoil

Radomes include an outer wall having a first average thickness and an inner wall having a second average thickness that is different from the first average thickness. At least a major portion of the inner wall is separated from at least a major portion of the outer wall by a space therebetween. The outer wall may comprise a layer of ceramic matrix composite (CMC) material. Aircraft and spacecraft include such radomes. Methods of forming radomes include forming an outer wall having a first average thickness, forming an inner wall having a different second average thickness, and coupling together the inner wall and the outer wall in such a manner as to provide a space between at least a major portion of the outer wall and at least a major portion of the inner wall.

Radomes, aircraft and spacecraft including such radomes, and methods of forming radomes

A gas turbine ring segment () for use in gas turbine engines made from a ceramic matrix composite (CMC) material is disclosed. The ring segment includes a stacked multiplicity of CMC thin-sheet lamellae () each comprising a peripheral surface collectively defining a cross-section profile of the ring segment. The lamellae collectively define a channel () formed in the center thereof for receiving a bow-tie member (). The bow-tie member is disposed in the channel for holding together the stacked lamellae in a through thickness direction, and the in-plane strength of the bow-tie member is perpendicular to the in-plane strength of the lamellae. A stem portion () of the assembly may be further secured with a wrap () of CMC ribbon.

Stacked lamellae ceramic gas turbine ring segment component

A method of bonding an insulation layer () to a CMC layer () by applying a compliant joining layer () between them in a series of steps (-) effective to bond the layers () with reduced differential shrinkage stresses during firing and reduced residual stresses. The CMC layer () and the compliant layer () may each be fired to an intermediate stage prior to applying the next layer (andrespectively), such that the compliant layer () has a remaining amount of curing shrinkage between that of the CMC layer () and the insulating layer () during a final firing stage. The insulation layer () may be a friable graded insulation (F) cast as a composite of hollow ceramic spheres (S) in a ceramic matrix (M). The compliant layer () may form a checkerboard of cracks () oriented generally perpendicular to the layer surface that function to relax stress. The cracks define columns () of material that form a bond at opposed ends to the CMC layer and to the insulation respectively.

Process for applying a thermal barrier coating to a ceramic matrix composite

An airfoil () having a continuous layer of ceramic matrix composite (CMC) material () extending from a suction side () to a pressure side () around a trailing edge portion (). The CMC material includes an inner wrap () extending around an inner trailing edge portion () and an outer wrap () extending around an outer trailing edge portion (). A filler material () is disposed between the inner and outer wraps to substantially eliminate voids in the trailing edge portion. The filler material may be pre-processed to an intermediate stage and used as a mandrel for forming the outer trailing edge portion, and then co-processed with the inner and outer wraps to a final form. The filler material may be pre-processed to include a desired mechanical feature such as a cooling passage () or a protrusion (). The filler material may include an upper layer () and a lower layer () separated by an intermediate layer () that extends to between the inner wrap and the outer wrap along the suction and/or pressure sides.

Ceramic matrix composite airfoil trailing edge arrangement

A composite structure () having a bond enhancement member () extending across a bond joint () between a ceramic matrix composite (CMC) material () and a ceramic insulation material (), and a method of fabricating such a structure. The bond enhancement member may extend completely through the CMC material to be partially embedded in a core material () bonded to the CMC material on an opposed side from the insulation material. A mold () formed of a fugitive material having particles () of a bond enhancement material may be used to form the CMC material. A two-piece mold () may be used to drive a bond enhancement member partially into the CMC material. A compressible material () containing the bond enhancement member may be compressed between a hard tool () and the CMC material to drive a bond enhancement member partially into the CMC material. A surface () of a ceramic insulation material () having a bond enhancement member () extending therefrom may be used as a mold for laying up a CMC material.

Bond enhancement for thermally insulated ceramic matrix composite materials

A sink assembly of a type including an enclosing cabinet (14) for supporting a sink bowl (16) from a floor (24) includes a liquid-impervious cabinet liner (22) supported by the cabinet (14) within an enclosed space (32) below the sink bowl (16) and its drain pipe (20) for catching water dripping from leaks and condensations. The sink liner (22) communicates with a second drain pipe (52) which exhausts water from the sink liner (22). The sink liner (22) is constructed so that its drain pan (42) is raised above a cabinet floor (40), with the drain pan (42) having tapered surfaces for accelerating flow toward the second drain pipe (52).

Growing community of inventors

Portland, OR, United States of America

Thomas Barrett Jackson