United Technologies Corporation

Raytheon Technologies Corporation

Goss International Americas, Inc.

Rtx Corporation

Ken Francis Blaney

Thomas E Clark

Paul M Lutjen

Richard K Hayford

Neil L Tatman

Anthony B Swift

Todd M LaPierre

Kevin J Ryan

Christopher M Jarochym

Jose R Paulino

Dmitriy A Romanov

Thurman Carlo Dabbs

Terence P Tyler

Dominic J Mongillo, Jr

Stephen Karl Kramer

Shawn J Gregg

Michael S Stevens

Russell E Keene

Brian R Pelletier

Bruce E Chick

Michael Thomas Woroniak

Matthew A Devore

Thomas J Praisner

Daniel S Rogers

Michael Robert Lemelin

Mark Bernard Dumais

Daniel J Whitney

James N Knapp

Peter J Milligan

Matthew James Bennison

Jr Terence P Tyler

Michael Lemelin

Jr Dominic J Mongillo

A mandrel for a molding process includes a first portion and a second portion that form a mandrel having a channel between the first and second portions. At least one locking pin is configured to urge the first and second portions away from each other to establish a gap in response to inserting the locking pin into the channel along a respective end of the mandrel. A molding apparatus and method of forming a matrix composite component are also disclosed.

Constant cross section mandrel for CMC components

An airfoiled component comprises: a root section, an airfoil section, a damper pocket enclosed within a portion of the airfoil section, and a damper. The airfoil section includes a suction sidewall and a pressure sidewall each extending chordwise between a leading edge and a trailing edge, and extending spanwise between the root section and an airfoil tip. The damper includes a fixed end unified with a damper mounting surface, and a free end extending into the damper pocket from the damper mounting surface.

Internally damped airfoiled component

A method of assembling a blade outer air seal assembly includes engaging a first blade outer air seal with a first attachment surface on a first attachment body. The first blade outer air seal includes a first attachment body passage for accepting the first attachment body. A second blade outer air seal is engaged with a second attachment surface on the first attachment body. The second blade outer air seal includes a second attachment body passage for accepting the first attachment body. Rotation is prevented of the first attachment body relative to the first blade outer air seal with a first post engaging the first blade outer air seal. Rotation is prevented of the first attachment body relative to the second blade outer air seal with a second post engaging the second blade outer air seal.

Gas turbine engine component

A self-pumping fuel injector includes a pump and a motor for, in-part, delivering fuel to a combustor at higher fuel pressures during start-up and ramping-up conditions. Each pump may include a stationary flow interuptor that intermittently and variably supplies fuel to a rotating spindle that, in-turn, expels the fuel into a nozzle of the injector for improve fuel spray distributions.

Self-pumping fuel injector for a gas turbine engine and method of operation

A seal assembly includes at least one blade outer air seal (BOAS) including a base portion that extends between a leading edge and a trailing edge. A forward wall and an aft wall extend radially outward from the base portion to a radially outer portion. The radially outer portion is spaced from the base portion and at least partially defines a passage with the forward wall, aft wall, and base portion. At least one attachment body is located at least partially within the passage. The at least one attachment body includes a leading edge connected to a trialing edge by a radially inner surface and a radially outer surface. The radially outer surface includes at least one blade outer air seal attachment surface for engaging the at least one BOAS. At least one post extends from the radially outer surface and has a blade outer air seal guide surface.

A mandrel for a molding process that includes a first portion that has a first portion outer surface, a first portion inner surface, a first portion first end, and a first portion second end. A thickness of the first portion first end is greater than the first portion second end. A second portion has a second portion outer surface, a second portion inner surface, a second portion first end, and a second portion second end. A thickness of the second portion first end is smaller than the second portion second end. The first portion inner surface engages the second portion inner surface to form a mandrel that has a constant cross-section.

A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of segments that extend circumferentially about an axis and mounted in the support structure. At least two of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. A recess is arranged in at least one of the first wall and the second wall. An intersegment seal is arranged between the at least two segments. The intersegment seal has a circumferentially extending portion and a radially extending tab. The radially extending tab extends into the recess to define at least two cavities within the recess.

BOAS thermal baffle

A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a support structure via a carrier. At least one of the segments have a first hook circumferentially spaced from a second hook. A base portion extends from the first hook to the second hook. The carrier has a cavity on a radially inner surface between the carrier and the base portion.

CMC BOAS arrangement

A blade outer air seal assembly includes a support structure arranged about an axis. At least one blade outer air seal segment is mounted in the support structure. A flow guide is arranged between the support structure and the at least one blade outer air seal segment defining a passage between the flow guide and the blade outer air seal segment. The passage extends in a generally axial direction.

CMC BOAS cooling air flow guide

A blade outer air seal includes a base portion. A first wall and a second wall extend from the base portion. The first wall is circumferentially spaced from the second wall. The first and second walls extend at an angle less than 90&#xb0; from the base portion. The first and second walls extend towards one another.

A gas turbine engine component includes a main body. A cooling passage is within the main body. The cooling passage is defined by a first wall opposite a second wall. The cooling passage has an inlet on the second wall. A protrusion is formed on the first wall arranged across from the inlet.

Boas flow directing arrangement

A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a support structure via a carrier. At least one of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. The first and second walls extend at an angle less than 90&#xb0; from the base portion. The carrier has a flat portion that extends from the first wall to the second wall.

A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a support structure. At least two of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. A first hook extends from the first wall and a second hook extends from the second wall. A wedge seal is arranged between the at least two adjacent seal segments. A clip is configured to bias the wedge seal radially inward.

An attachment body for a blade outer air seal includes a leading edge connected to a trialing edge by a radially inner wall and a radially outer wall. At least one forward hook extends from the radially outer wall. At least one aft hook extends from the radially outer wall. At least one post extends from the radially outer surface and has a blade outer air seal (BOAS) guide surface.

Attachment body for blade outer air seal

A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a chamber within the attachment block, and communicates to circumferential edges of the attachment block to direct cooling air along the central web of the blade outer air seal. A blade outer air seal assembly is also disclosed.

Growing community of inventors

Middleton, NH, United States of America

Ken Francis Blaney