Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Winston Gregory Smiddy

Thomas E Clark

Paul M Lutjen

William M Barker

Dominic J Mongillo, Jr

San Quach

Jeffrey T Morton

Daniel J Whitney

Matthew D Parekh

Andrew Joseph Lazur

Kathryn S Read

Kevin L Rugg

Jr Dominic J Mongillo

A method for forming a ceramic matrix composite (CMC) component with an internal cooling channel includes partially densifying a first fiber preform to form a portion of a final ceramic matrix volume, machining a first channel into a surface of the partially densified first fiber preform, covering the first channel with a fibrous member to form a near net shape fiber preform with an internal passage formed by the first channel and the fibrous member, and densifying the near net shape fiber preform.

Internal cooling circuits for CMC and method of manufacture

A gas turbine engine includes one of a turbine section and a compressor section having multiple stages. At least one of the stages defines an outer diameter comprised of a plurality of circumferentially arranged blade outer air seals. Each blade outer air seal is spaced from each adjacent blade outer air seal in the plurality of circumferentially arranged blade outer air seals via a mateface gap. The mateface gap is oblique to a radius of the gas turbine engine, such that air entering the mateface gap is directed to an inner diameter surface of at least one of the blade outer air seals in the plurality of blade outer air seals.

Mateface for blade outer air seals in a gas turbine engine

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has an elongated seal body having a seal face that bounds a gas path and an opposed impingement face. The seal body defines an internal cavity extending in a circumferential direction between opposed mate faces and extending in a radial direction between walls of the seal body defining the seal and impingement faces. A baffle divides the internal cavity into at least a first region and a second region. The first region has a first section extending transversely from a second section. The first section has a component in the radial direction, and the second section has a component in an axial direction such that the second region is defined between the baffle and the walls of the seal body defining the seal face. A method of sealing is also disclosed.

Seal assembly with baffle for gas turbine engine

A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a core flowpath, and a turbine fluidly connected to the combustor via the core flowpath. The turbine includes at least one stage having a plurality of rotors and a plurality of vanes. An outer diameter of the core flowpath at at least one stage is at least partially defined by a set of circumferentially arranged blade outer air seals. Each blade outer air seal includes a platform. An internal cooling cavity is defined within the platform. At least one mateface of the platform includes a cooling trench, and a first set of cooling holes connecting the internal cavity to the cooling trench.

Blade outer air seal including cooling trench

A gas turbine engine includes a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is positioned radially outwardly of the radially outer tip of the turbine blade. The blade outer air seal has a forward hook at an axially forward location and an aft hook at an axially aft location. An axial direction is defined by a rotational axis of the turbine blade. The blade outer air seal has a central web extending axially between the forward and aft hooks. The forward and aft hooks extend generally radially outward from the central web, and have slots for being received on forward and aft support hooks of a blade outer air seal support.

Blade outer air seal formed of laminate and having radial support hooks

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends circumferentially between first and second mate faces and an engagement portion along the first mate face. A support has an interface portion that extends from a mounting portion. The interface portion abuts the engagement portion to limit relative movement, and the mounting portion defines an aperture that receives a fastener to mechanically attach the mounting portion to an engine static structure. A portion of the fastener is circumferentially aligned with the first mate face. The fastener defines a first cooling passage that delivers cooling flow at a location adjacent to the first mate face.

Seal assembly for gas turbine engine

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body extending circumferentially between opposed mate faces, the seal body having a seal face that bounds a gas path and an opposed impingement face, a seal carrier extending along the impingement face, and a seal member trapped between the seal carrier and the impingement face such that the seal member is circumferentially aligned with one of the mate faces. A method of sealing is also disclosed.

Seal assembly with impingement seal plate

A method of forming a gas turbine engine component includes the steps of (a) forming an intermediate portion, (b) forming cooling circuit structure into at least an outer layer of the intermediate portion, (c) providing an outer layer over the formed cooling circuits to close off the cooling circuits, such that there are laminate on both a radially inner and a radially outer side of the cooling circuits, and (d) forming an inlet and an outlet to the cooling circuits through the outer layer. A gas turbine engine is also disclosed.

Internal cooling circuit for blade outer air seal formed of laminate

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The engagement portion defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines an elongated opening to the internal cavity. A method of sealing is also disclosed.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body having a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The seal body defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines a plurality of apertures to the internal cavity. A housing is mounted to the seal such that the impingement face is exposed to define a plenum between the housing and the impingement face. The housing defines a plurality of cooling passages, and each of the plurality of cooling passages define a passage axis that is oriented such that a projection of the passage axis intersects the seal body. A method of sealing is also disclosed.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal having an elongated seal body extending between a seal face that faces toward a gas path and a backside face opposite the seal face, and the seal face extending circumferentially between first and second mate faces. The seal body defines an internal cavity that extends circumferentially from a first opening along the first mate face to a second opening along the second mate face, and the backside face extends between the first and second openings. A shield includes a shield body that spans between the first and second openings such that the backside face is situated between the internal cavity and the shield body.

Growing community of inventors

Saco, ME, United States of America

Winston Gregory Smiddy