Raytheon Technologies Corporation

Rtx Corporation

Jaime A Arbona

Carson A Roy Thill

Justin K Bleil

Danielle Mahoney

Andrew D Keene

Robin H Fernandez

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 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 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.

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West Palm Beach, FL, United States of America

Jaime A Arbona