Raytheon Technologies Corporation

Rtx Corporation

Tyler G Vincent

Howard J Liles

San Quach

Jon E Sobanski

Bryan P Dube

Robert A White, Iii

Daniel Carlson

Raymond C Surace

Richard Wesley Jackson, Iii

Bryan H Farrar

Alex J Schneider

Mary Colby

Cheng Gao

Chang Gao

Joshua William Owen Richards

A layout for asymmetric trip strips including a flow passage having a lower wall and an upper wall opposite the lower wall, each of the lower wall and the upper wall including an inner surface, the flow passage having a passage inlet and a length L and a diameter d; multiple skewed trip strips extending from at least one inner surface of the lower wall or the upper wall; and at least one periodic reflection of the skewed trip strips along the flow passage downstream of the passage inlet at a frequency with a length-to-diameter ratio of L/d≤20.

Layout for asymmetric cast trips in long passages

A component for a gas turbine engine includes a matrix composite component having a radially outer end and a radially inner end. The ceramic matrix component having an internal chamber defined by an inner surface. A spar is received within the internal cavity, and spaced from an inner surface of the matrix component defining a chamber with the inner surface. Flow guides are formed on one of an outer surface of the spar and the inner surface of the matrix component. The flow guides direct airflow towards a portion of the inner surface. An air inlet chamber is formed at one radial end of the spar and an air outlet chamber formed at an opposed radial end of the spar. The air inlet chamber is defined such that air will flow into the internal chamber, outwardly of the spar, and inwardly of the inner surface of the matrix component. A gas turbine engine is also disclosed.

Flow guides for internal cooling of a CMC airfoil

A flow path component assembly includes a flow path component that has a plurality of segments that extend circumferentially about an axis. At least one of the segments have a first radial side and a second radial side and extend from a first circumferential side to a second circumferential side. A mateface seal is arranged on the first radial side near the first circumferential side. The mateface seal has a v-shaped groove.

Chevron grooved mateface seal

A method includes forming a ceramic matrix composite component by infiltrating an array of ceramic-based fibers with a ceramic-based matrix; forming a plurality of cooling holes in the ceramic matrix composite component; applying a slurry of particles in a carrier fluid to the ceramic matrix composite component such that the slurry passes through the cooling holes and wicks into the ceramic matrix composite material; and processing the ceramic matrix composite component to remove the carrier fluid, thereby leaving a filler at a wall surface of the plurality of cooling holes. A component is also disclosed.

Ceramic matrix composite article and method of making the same

A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.

Ceramic wall seal interface cooling for an airfoil vane arc segment

A gas turbine engine component includes a supply cavity and a manifold cavity that shares a common divider wall with the supply cavity. The common divider wall includes inlet metering holes that connect the supply cavity and the manifold cavity. An exterior wall has an exterior surface and an opposed interior surface that bounds portions of the supply cavity and of the manifold cavity. Outlet cooling holes extend through the exterior wall and connect the manifold cavity with the exterior surface. The number of the inlet metering holes is equal to or less than the number of the outlet cooling holes, and at least one of the inlet holes is coaxial with at least one of the outlet holes.

Gas turbine engine component with manifold cavity and metering inlet orifices

A flow path component includes a platform that extends between a first side and a second side. A slot is in the first side. The slot divides the platform into a first portion and a second portion at the first side. There is a groove along the first side in the first portion.

Scalloped mateface seal arrangement for CMC platforms

A method of forming a ceramic matrix composite component having an internal cooling circuit includes wrapping at least a first sheet around a first mandrel, wrapping at least a second sheet around a second mandrel, creating a first plurality of holes in the first sheet corresponding to a plurality of openings in the first mandrel, creating a second plurality of holes in the second sheet corresponding to a plurality of openings in the second mandrel, aligning the first mandrel and the second mandrel such that the first plurality of holes face and are aligned with the second plurality of holes, wrapping at least a third sheet around both the first mandrel and second mandrel to form a preform, the preform comprising each of the first sheet, the second sheet, and the third sheet, and densifying the preform. The first sheet, second sheet, and third sheet are formed from a ceramic fiber material.

Preform crossovers for composite airfoils

A gas turbine engine article includes a ceramic body that defines a flange, first and second cooling passages partitioned from each other by the flange, a through-hole in the rib that connects the first and second cooling passages, a thermal insulation bushing that lines the through-hole.

Ceramic article with thermal insulation bushing

Ceramic wall seal interface cooling

A vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the flange. There is a conformal thermal insulation blanket disposed on the flange.

Vane arc segment with conformal thermal insulation blanket

An airfoil fairing includes an airfoil section that is formed of a fiber-reinforced composite wall. The airfoil section has first and second radial ends, pressure and suction sides, leading and trailing ends that join the pressure and suction sides, an internal cavity, and a rib that extends radially in the internal cavity. The rib has a radial rib end at the first radial end of the airfoil section and extends across the internal cavity from a first rib side at the pressure side to a second rib side at the suction side. The rib defines at the radial end first and second shoulders. The first and second shoulders define a radial notch there between.

Gas turbine engine airfoil fairing with rib having radial notch

A vane includes a ceramic airfoil section that has an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side. The ceramic airfoil section has an internal cavity. A support spar extends through the internal cavity for supporting the ceramic airfoil section. The support spar is spaced from the airfoil wall such that there is a gap there between. The support spar has an internal through-passage that is fluidly isolated from the gap in the ceramic airfoil section. A baffle is disposed in the gap and is spaced apart from the airfoil wall and the support spar so as to divide the gap into a plenum space between the support spar and the baffle and an impingement space between the baffle and the airfoil wall. The baffle has impingement holes directed toward the airfoil wall that connect the plenum space and the impingement space.

CMC vane with support spar and baffle

A vane arc segment includes an airfoil section, a spar, and a baffle. The spar supports the airfoil section and has a leg that extends in an internal cavity of the airfoil section. The leg is spaced from the airfoil wall such that there is a gap there between. The baffle divides the gap into a plenum space between the leg and the baffle and an impingement space between the baffle and the airfoil wall. The baffle has impingement holes directed toward the airfoil wall that connect the plenum space and the impingement space. The impingement space is of substantially uniform thickness and the plenum space is of non-uniform thickness along a portion of the span length of the airfoil section.

Vane with baffle and recessed spar

A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section. A spar has a spar platform adjacent the first fairing platform and a hollow spar leg that extends from the spar platform and through the hollow airfoil section. The hollow spar leg has an internal passage for receiving cool air there through, a clevis mount, and a pin fairing. The clevis mount is distal from the spar platform and protrudes from the second fairing platform. The clevis mount includes first and second prongs with aligned holes. A pin extends through the aligned holes. The pin fairing extends over the pin between the first and second prongs for guiding the cooling air around the pin. There is a support platform adjacent the second fairing platform. The pin locks the support platform to the spar leg.

Growing community of inventors

Portland, CT, United States of America

Tyler G Vincent