Rtx Corporation

United Technologies Corporation

Raytheon Technologies Corporation

Daniel S Rogers

Joseph Micucci

Mikayla M Rogers

Danielle Mahoney

Morely S Sherman

Robert A White, Iii

Steven J Feigleson

Stephen W Milks

Timothy J Harding

Paul M Lutjen

Carson A Roy Thill

Marshall F Thayer

James E Weisheit

Thomas E Clark

David A Litton

Ken Francis Blaney

Jose R Paulino

Gregory E Reinhardt

Christopher T Anglin

Christopher M Valva

Yuk-Kwan Brian Yuen

Jeremy Drake

Brian C McLaughlin

Anthony B Swift

Terence P Tyler

Taryn Narrow

Ahmed Abdillahi Abdi

Peter J Rosenfeld

Aaron Tomich

Collin P Fitzgerald

Leonard Kolshak

Matthew Nickerson

Giovanni Lawrence

Jr Terence P Tyler

A gas turbine engine includes a turbine section that has a ceramic matrix composite body that defines a core gaspath side that a row of blades, a forward end, an aft end, and circumferential sides. The forward end abuts at least one vane of a first row of vanes, and the aft end including a seal channel. A compliant seal is disposed in the seal channel and seals against at least one vane of a second row of vanes.

Blade outer air seal with compliant seal

A section of a gas turbine engine includes a ceramic component and a metallic component situated adjacent the ceramic component. The ceramic component and the metallic component are situated outside of a core flow path of the gas turbine engine. The section of a gas turbine engine also includes an interface between the ceramic component and a metallic component and a mullite-based coating disposed at the interface. The coating provides thermal protection to the ceramic component and the metallic component, and provides thermochemical protection against interaction between the ceramic component and the metallic component. A gas turbine engine and a method of protecting components in a gas turbine engine are also disclosed.

Machinable coating with thermal protection

A blade outer air seal has seal mount hooks on both a leading edge of the central web and a trailing edge of the central web. The seal mount hooks have a generally radially outward extending section extending to a generally axially extending section. The seal mount hooks have a support face which is to be supported on a support mount hook. The support face is generally formed about a single radius of curvature over at least 50% of a circumferential length defined from a radially inner end of the support face to a radially outer end of the support face. A radius of curvature of the inner support surface is greater than or equal to 0.150 inch and less than or equal to 0.300 inch. A blade outer air seal and a gas turbine engine are also disclosed.

Blade outer air seal with large radius of curvature mount hooks

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 turbine section that has a seal system disposed in interfaces between adjacent blade outer air seals. The seal system includes a first seal and at least one second seal that partially overlaps the first seal, the at least one second seal is configured to bias the first seal into a sealing position.

CMC BOAS with overlapping seals

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 gas turbine engine includes a turbine section that has a retainer ring, a first vane that bears against the retainer ring to prevent movement of the first vane in a first axial direction, a second vane axially spaced from the first vane, and a blade axially between the first vane and the second vane. A blade outer air seal is situated radially outwardly of the blade. The blade outer air seal includes a ceramic matrix composite body that defines a core gaspath side that faces the blade, a forward end, an aft end, and circumferential sides. There is a spring seal at the aft end of the blade outer air seal that seals against the second vane. The spring seal provides a preload that biases the blade outer air seal against the first vane and thereby biases the first vane against the retainer ring.

Blade outer air seal with retainer ring

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 gas turbine engine turbine blade includes a turbine blade body including an inner platform. An airfoil extends radially outwardly of the inner platform. The airfoil has a leading edge and a trailing edge, and a suction wall and a pressure wall. The turbine blade body has mount structure including at least one circumferentially outwardly extending mount portion on a suction wall side and a pressure wall side each having a radially outer face. The turbine blade body is formed of one of a polymer, metal or ceramic matrix composite. There is a protective coating on the radially outer faces of the at least one enlarged mount portions. A gas turbine engine is also disclosed.

Machinable coating for CMC and metal interface in a turbine section

A blade outer air seal arc segment includes a ceramic matrix composite body that defines a core gaspath side, a non-core gaspath side opposite the core gaspath side, a forward end, an aft end, and circumferential sides. The ceramic matrix composite body has first and second flanges on the non-core gaspath side. The ceramic matrix composite body is comprised of fiber plies disposed in a ceramic matrix. The fiber plies include flange fiber plies that have a +/−15-75 degree ply layup arrangement.

Blade outer air seal with angle-oriented ply layup for CMC compound radii

There is a blade outer air seal positioned to be radially outward of blades in the rotating blade row relative to the rotational axis. There is at least one brush seal having bristles extending from a mount location radially inward to contact a sealing surface on the blade outer air seal. An angle is defined between the bristles and relative to the sealing surface having a radially inward extending component, and with an axial component in a direction toward a leading edge attachment feature and a trailing edge attachment feature, and the angle is less than 90° on a side of the brush seal opposite the leading edge and trailing edge mount hooks. A gas turbine engine component is also disclosed.

Angled brush seal and gas turbine engine component combination

A fan assembly of a gas turbine engine includes a fan rotor including a fan rotor hub, and a plurality of fan blades extending radially outwardly from the fan rotor hub, and a fan case including an inner case portion and an outer case portion surrounding the plurality of fan blades. A plurality of struts extend between the inner case portion and the outer case portion. A bearing assembly is configured to support the fan rotor at the inner case portion. The bearing assembly includes a bearing inner race secured to the fan rotor, a bearing outer race secured to the inner case portion, and a plurality of bearing elements located radially between the bearing inner race and the bearing outer race.

Housing less front bearing compartment for gas turbine engine

A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.

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Lyman, ME, United States of America

Daniel S Rogers