Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Cidra Corporation

Weatherford/lamb, Inc.

Hamilton Sundstrand Corporation

Goodrich Corporation

Utc Power Corporation

C1dra Corporation

University of Rhode Island

United Technologies Research Center

Paul F Croteau

Andrzej Ernest Kuczek

Wenping Zhao

Ellen Y Sun

Daniel L Gysling

John P Wesson

Thomas J Martin

Justin R Hawkes

Daniel V Viens

Tahany Ibrahim El-Wardany

John E Holowczak

Robert J Maron

Matthew Andrew Hough

Russell B Hanson

John S Tu

Thomas Wolfgang Engel

Matthew B Kennedy

Stephen C Harmon

Joshua C Rathgeb

Douglas H Loose

Gajawalli V Srinivasan

Matthew E Lynch

Paul Attridge

Thomas J Garosshen

James M Diener

Jun Shi

Michael A Davis

James R Dunphy

Changsheng Guo

Jean Yamanis

John A Sharon

Tania Bhatia Kashyap

John D Riehl

Otto J Gregory

Paul K Sanchez

Kevin E Green

Zhigang Wang

Robin H Fernandez

Connie E Bird

Andrew A Consiglio

Kevin Rivera

Dustin Frame

Louis Chiapetta, Jr

A composite pressure vessel assembly includes a first and second vessels aligned side-by-side. Each vessel has a liner defining respective chambers. First and second mid-layers of the assembly cover the respective liners with portions of the respective mid-layers being in contact with one-another. An outer layer of the vessel assembly is in contact with and substantially envelops both mid-layers except for the mid-layer portions.

Composite pressure vessel assembly and method of manufacturing

A method of machining includes mounting a component in a drilling machine. The component has a target region where the hole is to be drilled. The component and a jet head are situated relative to each other in a drilling arrangement in which the target region is at a first position that is vertically equal to or vertically above a second position at which the jet head is located. A liquid stream is jetted from the jet head and contains either abrasive particles or a laser beam. The stream impinges the target region, and the abrasive particles or the laser beam cause removal of material from the component to form the hole. The liquid stream rebounds off of the component as back-splash. The drilling arrangement causes gravitational draining of the back-splash from the target region to reduce interference between the back-splash and the liquid stream.

Method and system for drilling ceramic

An instrumented vane body is provided that includes a suction side and pressure side outer walls, an interior cavity, at least one supply conduit, a plurality of sensors, and a plurality of sensor ports. The suction and pressure side outer walls extend chordwise between leading and trailing edges and between inner and outer radial ends. The supply conduit is in fluid communication with the interior cavity, and is in communication with the interior cavity through at least one of the inner or outer radial ends. The sensor ports are disposed in the leading edge and each is configured to receive a sensor, and are spaced apart from one another. Each sensor port is in fluid communication with at least one vent aperture, and each is configured to permit core gas to enter that sensor part and exit the vane body through the at least one vent aperture.

Gas turbine vane body with instrumentation

A gas turbine engine article includes a silicon-containing ceramic wall that has an external combustion gaspath side and an internal side that borders a cooling air cavity. The external combustion gaspath side has an associated combustion gas flow direction there along. An array of cooling holes extends through the silicon-containing ceramic wall and connects the internal side with the external combustion gaspath side. The cooling holes are oriented to discharge cooling air to the external gaspath side in a direction counter to the combustion gas flow direction.

Gas turbine engine article with cooling holes for mitigating recession

A composite pressure vessel assembly includes a plurality of lobes, each of the lobes having at least one interior wall and at least one curved wall, the plurality of lobes being positioned in a side by side arrangement and extending in a longitudinal direction from a first end to a second end. Also included is a plurality of end caps disposed at the ends of the lobes, wherein the plurality of lobes and end caps are formed of at least one fiber-reinforced polymer. A method of manufacturing a composite pressure vessel assembly is provided. The method includes forming a plurality of lobes consisting of at least one fiber-reinforced polymer. The method also includes forming a main body with the plurality of lobes, the lobes disposed in a side by side arrangement.

An airfoil includes an airfoil section that has an airfoil wall that surrounds a cavity. The airfoil wall includes an exterior monolithic ceramic shell and an interior CMC liner that has CMC plies. An outermost ply of the CMC plies forms tabs that are raised from an underlying ply so as to define a slot. The exterior monolithic ceramic shell includes an underlapping shell piece and an overlapping shell piece. The underlapping shell piece has a portion disposed in the slot and bonded with the tabs. The overlapping shell piece extends over the tabs and is bonded to the tabs. There are channels bounded by adjacent ones of the tabs, the underlapping shell piece, and the overlapping shell piece. Channel orifices through the CMC liner connect the cavity and the channels.

Airfoil with CMC liner and multi-piece monolithic ceramic shell

An airfoil includes an airfoil body that has a trailing edge region. The trailing edge region includes first and second monolithic ceramic exterior walls, a flow discharge passage between the first and second monolithic ceramic exterior walls, a ceramic matrix composite (CMC) liner at least a portion of which is disposed in the flow discharge passage between the first and second monolithic ceramic exterior walls, and an array of pedestals disposed in the flow discharge passage. Each of the flow guides bridges the CMC liner and at least one of the first and second monolithic ceramic exterior walls.

Ceramic airfoil trailing end configuration

A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

Diffuser case support structure

An airfoil includes an airfoil section that has an airfoil wall that surrounds a cavity. The airfoil wall includes a first wall section comprised of a monolithic ceramic shell, a second wall section comprised of a CMC liner that is bonded along an interface to an interior side of the monolithic ceramic shell, and a ceramic barrier coating that is bonded to an exterior side of the monolithic ceramic shell. The airfoil wall includes at least one of: inter-section cooling channels that extend along the interface and are bounded by the monolithic ceramic shell and the CMC liner, or intra-section cooling channels that extend within the CMC liner.

Airfoil having internally cooled wall with liner and shell

A pressure vessel assembly includes a vessel including a wall defining a chamber and a circumferentially continuous lip projecting into the chamber from the wall. The lip defines a through-bore in fluid communication with the chamber. A nozzle assembly including a tube and a flange projecting radially outward from the tube. The tube includes a first portion projecting from the flange and through the through-bore and an opposite second portion projecting outward from the flange. The flange is in contact with the wall and the first portion includes an outer surface having a contour configured to produce sealing friction between the lip and the outer surface.

Composite pressure vessel assembly with an integrated nozzle assembly

A pressure vessel assembly includes a vessel having a wall defining a chamber and a circumferentially continuous lip projecting into the chamber from the wall. The lip defines a through-bore that is in fluid communication with the chamber. A nozzle assembly of the pressure vessel assembly includes a tube projecting at least in-part into the through-bore, and an o-ring disposed between, and in sealing contact with, the tube and the lip.

A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

Diffuser case assembly

A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.

A composite pressure vessel assembly includes a first vessel having a first inner layer and a second vessel having a second inner layer. An outer layer of the assembly is in contact with and substantially envelopes the first and second inner layers. A junction of the assembly has outer boundaries defined by segments of the first inner layer, the second inner layer and the outer layer. A cross-layered component of the assembly is disposed in the junction, the first and second inner layers and the outer layer for adding strength to the junction and restricting delamination.

Growing community of inventors

Columbia, CT, United States of America

Paul F Croteau