Rtx Corporation

Morely S Sherman

Daniel S Rogers

Joseph Micucci

Mikayla M Rogers

Paul M Lutjen

Timothy J Harding

Marshall F Thayer

James E Weisheit

John R Paulus

Dmitriy A Romanov

Danielle Mahoney

Billie Rosalie Maldonado

James R Plante

Nolan Frederic Quinn

Mary E M Hiller

Thurman C Dabbs

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 component for a gas turbine engine, including: at least one internal cavity extending through the component, the internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity; a plurality of cooling features extending from a surface of the at least one internal cavity, the plurality of cooling features are formed in accordance with at least one of the following groups: i) a plurality of airfoil shaped features that extend upwardly from the surface of the at least one internal cavity and a plurality of wedge shaped features each having a triangular base that has an upstream portion and a downstream portion, the upstream portion extending further from the surface than the downstream portion; ii) a plurality features having a curved or 'J' shaped base that extends upwardly from the surface, a plurality features having a double curved or symmetrically “J” shaped base that extends upwardly from the surface, and a plurality features having a base that extends upwardly from the surface with a curved portion that defines an opening therethrough; iii) a first plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the first plurality of pins and a second plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the second plurality of pins the plurality of grooves formed in the peripheral surface of each of the second plurality of pins are configured such that “V” shapes or inverted “V” shapes are formed in the peripheral surface of each of the second plurality of pins; and iv) a plurality of chevron shaped trip strips that are located in a channel, the plurality of chevron shaped trip strips are spaced from each other such that a “U” shaped passage is formed therebetween and each chevron shaped trip strip has a top portion that curls inwardly towards the channel and a plurality of pairs of features that each extend from a surface of another channel towards each other where a gap is located between distal ends of the plurality of pairs of features.

Cooling features for a component of a gas turbine engine

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 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

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

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Portsmouth, NH, United States of America

Morely S Sherman