Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Ratheyon Technologies Corporation

Carson A Roy Thill

Danielle Mahoney

Andrew D Keene

Justin K Bleil

Jaime A Arbona

Paul M Lutjen

Timothy M Davis

Mark Broomer

Craig R McGarrah

Mark John Rogers

Russell E Keene

Daniel S Rogers

Anthony B Swift

Joseph Micucci

Mikayla M Rogers

Dominic J Mongillo, Jr

Daniel L Gysling

Thomas E Clark

JinQuan Xu

Jose R Paulino

Bruce L Morin

Anthony P Cherolis

Thurman Carlo Dabbs

Ramons Andris Reba

Robin H Fernandez

Stephen A Morford

Kevin W White

Robert L Hazzard

Ramons A Reba

Conway Choung

Jeffrey A Perry

Kevin D Tracy

Timothy A Dunbar

Jinquan Xu

Craig Mcgarrah

A turbine section for a gas turbine engine includes a turbine having at least one blade rotatable around an axis. The at least one blade has a tip. The turbine section for a gas turbine engine also includes at least one blade outer air seal arranged radially outward from the tip. The blade outer air seal has a center web and first and second mounting arms extending from the center web. Each of the first and second mounting arms include at least one aperture configured to receive a pin to attach the blade outer air seal to an engine static structure. A gas turbine engine and a method of attaching a blade outer air seal to a static structure of a gas turbine engine are also disclosed.

Attachment for blade outer air seal

A gas turbine engine includes a compressor section, a combustor section and a turbine section for rotation on an axis. The turbine section includes at least one row of rotating turbine blades each having a radially outer tip. A blade outer air seal is positioned radially outwardly of the radially outer tip. The blade outer air seal has a central web positioned radially outwardly of the radially outer tip. The blade outer air seal has an upstream mount arm and a downstream mount arm receiving mount structure from a static structure. The static structure has sealing members engaging an upstream outer surface of the upstream mount arm at an upstream seal material and a downstream outer surface of the downstream mount arm at a downstream seal material. A method is also disclosed.

Blade outer air seal with machinable coating at sealing surfaces

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment including a sealing portion, and a first rail and a second rail opposed to the first rail. The sealing portion extends in a circumferential direction between opposed mate faces and extends in an axial direction between a leading edge and a trailing edge. Each of the first and second rails extend outwardly in a radial direction from the sealing portion to respective first and second edge faces, and the sealing portion has a sealing face dimensioned to bound a gas path and includes a backside face opposed to the sealing face. The first and second rails include respective first and seconds pairs of hooks dimensioned to mount the seal arc segment to an engine static structure in an installed position. The seal arc segment is radially opposed to the sealing face between the first and second edge faces establishing a first region. The seal arc segment is radially opposed to the sealing face between the leading and trailing edges establishing a second region. A method of sealing for a gas turbine engine is also disclosed.

Seal assembly with reduced pressure load arrangement

A component for a gas turbine engine includes a component body formed of ceramic matrix composite lamina and has at least one hook. The at least one hook has an attachment region radially inward of the at least one hook. The attachment region is radially thinner from a hook end of the at least one hook to a remote end, and then becomes radially thicker. A slot is formed through a radial thickness of the at least one hook from the hook end in a remote direction, such that there are two sections of the attachment region. A gas turbine engine is also disclosed.

Attachment region for CMC components

An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a gas turbine engine component that has a first interface portion, and a support that has a mounting portion and a second interface portion, the mounting portion attachable to an engine static structure, a first retention feature that releasably secures the first interface portion to the support in a first installed position of the gas turbine engine component, and a second retention feature dimensioned to secure the first interface portion to the second interface portion in a second installed position of the gas turbine engine component. The first installed position differs from the second installed position, and one of first and second retention features is dimensioned to carry the gas turbine engine component in response to release of another one of the first and second retention features. A method of sealing for a gas turbine engine is also disclosed.

Seal assembly with secondary retention feature

A flow path component assembly includes a flow path component having a plurality of segments that extend circumferentially about an axis and mounted in a support structure. At least one of the plurality of segments have a first wall and a second wall that extend radially outward from a base portion. The first wall is axially spaced from the second wall. A coating is on a portion of the first wall and a portion of the second wall. The coating is in contact with a feature on the support structure.

Blade outer air seal arrangement and method of sealing

A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.

Gas turbine engine component for acoustic attenuation

A component assembly includes a first component that has a first hole. The first hole has a non-circular cross section. A first portion of the first hole has a first radius of curvature and a second component. A pin extends from the second component and through the first hole. The pin has a non-circular cross section. A second portion of the pin has a second radius of curvature. The first radius of curvature and the second radius of curvature are substantially the same.

Compact pin attachment for CMC components

An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment that has a sealing portion and a pair of opposed rails extending outwardly from the sealing portion. The sealing portion includes a sealing face dimensioned to bound a core flow path and has a backside face opposed to the sealing face. The backside face includes a first localized region, a second localized region between the pair of rails, and a third localized region. A support includes a mounting portion and a first interface portion. At least one retention pin is dimensioned to engage the first interface portion of the support and at least one of the pair of rails such that the seal arc segment is carried by the at least one retention pin. A support plate is arranged relative to the support such that the at least one retention pin is trapped between the support plate and the support. A cooling cavity is established between the support, the support plate, and the second localized region. A method of sealing is also disclosed.

Seal assembly with distributed cooling arrangement

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment including a sealing portion, and a first rail and a second rail opposed to the first rail. The sealing portion extends in a circumferential direction between opposed mate faces and extends in an axial direction between a leading edge and a trailing edge. Each of the first and second rails extend outwardly in a radial direction from the sealing portion to respective first and second edge faces, and the sealing portion has a sealing face dimensioned to bound a gas path and includes a backside face opposed to the sealing face. Each of the first and second rails includes at least one interface bore dimensioned to receive a retention pin such that the seal arc segment is carried by the retention pin in an installed position. The seal arc segment is radially opposed to the sealing face between the first and second edge faces establishing a first region. The seal arc segment is radially opposed to the sealing face between the leading and trailing edges establishing a second region. A method of sealing for a gas turbine engine is also disclosed.

A flow path component assembly includes a support structure. A flow path component has a plurality of segments that are arranged circumferentially about an axis and are mounted in the support structure by a carrier. At least one of the segments have a first wall axially spaced from a second wall. The first wall has first and second hooks spaced apart from one another in a circumferential direction. The second wall has third and fourth hooks spaced apart from one another in the circumferential direction. The first, second, third, and fourth hooks are in engagement with the carrier.

Boas arrangement with double dovetail attachments

A flow path component includes a base portion that extends between a first circumferential side and a second circumferential side. A first wall and a second wall extend radially outward from the base portion. The first wall is axially spaced from the second wall to form a passage between the first and second walls. A slot is formed in the first circumferential side. A notch in the base portion extends in a radial direction from the passage to the slot.

Feather seal slot arrangement for a CMC BOAS assembly

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 mounted in a carrier. At least two of the plurality of segments have a first wall that extends radially outward from a base portion. The base portion has a radially inner side and a radially outer side. A heat shield abuts the radially outer side of the at least two segments. The heat shield is formed from a ceramic material.

CMC heat shield

A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.

Growing community of inventors

South Berwick, ME, United States of America

Carson A Roy Thill