Raytheon Technologies Corporation

Rtx Corporation

Bryan H Farrar

Howard J Liles

Jon E Sobanski

Andrew Joseph Lazur

Bryan P Dube

Michael G McCaffrey

Tyler G Vincent

Andrew J Lazur

Lei Jin

Cheng Gao

Zachary Paul Konopaske

Ryan M Brodeur

Zachary P Konopaske

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

An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

Two-piece baffle

A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.

Contour weaving to form airfoil

A method of forming a ceramic matrix composite component with cooling channels includes embedding a plurality of wires into a preform structure, densifying the preform structure with embedded wires, and removing the plurality of wires to create a plurality of corresponding channels within the densified structure.

Method of forming cooling channels in a ceramic matrix composite component

A vane arc segment includes a continuous airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The airfoil section has a pressure side and a suction side. The first platform defines axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along at least a portion the axially-sloped suction side circumferential mate face.

CMC vane mate face flange

A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section extending there between. There is a spar having a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion with a clevis mount that that protrudes from the second fairing platform. A support platform adjacent the second fairing platform has first and second through-holes. The end portion of the spar leg extends through the first through-hole and a pin extends though the clevis mount to lock the support platform to the spar leg. A stabilizer rod extends through the second through-hole of the support platform and limits rotation of the support platform about the pin.

Vane with pin mount and anti-rotation stabilizer rod

An airfoil assembly includes an airfoil. The airfoil has first and second platforms and an airfoil between the first and second platforms. A support ring is configured to retain the first platform. The support ring has a lip which extends radially inward from the support ring. The lip is configured to engage an axial face of the first platform. The lip has a primary retention feature and a secondary retention feature. The primary and secondary retention features are configured to retain the first face of the first platform with respect to the annular ring. A support structure for an airfoil and a method of retaining an airfoil assembly are also disclosed.

Vane retention feature

A vane arc segment includes an airfoil piece that has a first platform, a second platform, and an airfoil section between the first platform and the second platform. At least the first platform is formed of a fiber-reinforced composite (FRC) and defines a radial flange. A cap is fitted on the radial flange.

Vane arc segment platform flange with cap

A gas turbine engine includes a plurality of airfoil vanes situated in a circumferential row about an engine central axis. Each of the plurality of airfoil vanes include a first platform, and a second platform, and an airfoil section therebetween. A face of the first platform includes a trailing edge recess and a leading edge recess. The trailing edge recess and leading edge recesses of adjacent ones of the first platforms together define a slot. A sealing element situated in each slot. The sealing element has a geometry that tracks the geometry of the slot such that the seal is trapped in the slot by a form-fit relationship in circumferential and axial dimensions by a form-fit relationship between the sealing element and the slot. A method of sealing a plurality of airfoil vanes is also disclosed.

Platform seal

A stator vane may comprise an airfoil extending between a first platform and a second platform, the airfoil including a core extending relatively orthogonal to the first platform and the second platform, at least one of the first platform or second platform comprising a frustic load transmission feature, wherein the frustic load transmission feature comprises at least a first angular surface disposed proximate a platform edge, wherein the first angular surface is defined by a non-orthogonal angle &#x3b8; with respect to an outer platform surface.

Frustic load transmission feature for composite structures

A stator vane may comprise an airfoil extending between a first platform and a second platform, a first shear tube may extend through the airfoil and relatively orthogonal to the first platform and the second platform, wherein the first shear tube extends through the first platform and the second platform. In various embodiments, a second shear tube may extend through the airfoil into the first platform and the second platform parallel the first shear tube.

Growing community of inventors

West Hartford, CT, United States of America

Bryan H Farrar