Raytheon Technologies Corporation

Rtx Corporation

Danielle Mahoney

Carson A Roy Thill

Andrew D Keene

Jaime A Arbona

Justin K Bleil

Thomas E Clark

Daniel S Rogers

Joseph Micucci

Mikayla M Rogers

William M Barker

William Wangard, Iii

Daniel J Whitney

Robin H Fernandez

Morely S Sherman

William Wangard Iii

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

Blade outer air seal with machinable coating

A gas turbine engine includes a row of blade outer air seal (BOAS) arc segments arranged around an engine axis. Each of the BOAS arc segments includes a ceramic matrix composite (CMC) body that has forward and aft flanges that project from the non-core gaspath side. An annular seal plate is located forward of the forward flange and includes a radially-extending wall, an axially-extending wall that projects forwardly from the radially-extending wall, and a nose that projects aftly from the radially-extending wall. The nose seals against the forward flange. A flexible seal is located in a recess defined by the radially-extending wall and the axially-extending wall. The flexible seal seals against a forward face of the radially-extending wall and is radially spaced apart from a radially outer face of the axially-extending wall.

Blade outer air seal with seal plate and flexible seal

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

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 blade outer air seal includes a carrier that has a dovetail and a ceramic seal segment supported on the dovetail. The ceramic seal segment has first and second axial ends, first and second circumferential sides, an inner side, an outer side, and first and second inward-facing dovetail hooks that project from the outer side and define a dovetail key. The ceramic seal segment is axially receivable onto the dovetail of the carrier via the dovetail key.

Blade outer air seal with inward-facing dovetail hooks and backside cooling

A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of seal segments that extend circumferentially about an axis and mounted in the support structure via a carrier. The carrier has a plurality of carrier segments that extend circumferentially about the axis. At least one of the seal segments have a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first wall axially spaced from a second wall. The first and second walls extend from the base portion to a first outer portion to form a first passage. The first wall has at least one slot engaged with a first carrier hook on one of the plurality of carrier segments. At least one of the carrier segments have a carrier window engaged with a support structure hook on the support structure.

Double box boas and carrier system

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 support structure. A blade outer air seal has a plurality of segments that extend circumferentially about an axis and mounted in the support structure via a carrier. At least one of the plurality of segments has a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first hook extends from the base portion near the first axial side and faces towards the second axial side. A second hook extends from the base portion near the second axial side and faces towards the first axial side. A slot is in the second hook configured to receive a pin.

Growing community of inventors

Dover, NH, United States of America

Danielle Mahoney