Rtx Corporation

Raytheon Technologies Corporation

Cheng Gao

Howard J Liles

James T Roach

David Wasserman

Jonas S Banhos

Thomas S Heylmun

San Quach

Jon E Sobanski

Bryan P Dube

Tyler G Vincent

Christian X Campbell

Bryan H Farrar

A ceramic matrix composite (CMC) blade outer air seal (BOAS) assembly includes a CMC BOAS including a base and a pair of rails having a substantially π-shaped cross-section. The pair of rails include a first pair of aligned holes at a first end and second pair of aligned holes at a second end. A first pair of parallel metallic pins have a first end connected to a first central support pin and a second end connected to a second central support pin, respectively, wherein the first pair of parallel metallic pins are configured to engage the first pair of aligned holes. A second pair of parallel metallic pins also have a first end connected to a first central support pin and a second end connected to a second central support pin, respectively, wherein the second pair of parallel metallic pins are configured to engage the second pair of aligned holes.

Dual pin support for blade outer air seal and method

A vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the outer platform and formed of ceramic matrix composites ('CMC'). The vane having an internal cooling chamber. A metal baffle is received within the internal cooling chamber and extends beyond the outer platform. A bathtub seal has a central portion receiving the metal baffle. The metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. The bathtub seal having an inner wall and an outer wall outward of the metal baffle. The inner wall, the outer wall and a base wall define a bathtub seal chamber. The base wall is in contact with the outer platform. The vane is connected to the outer wall. The static structure is received within the bathtub seal chamber. A connection is configured to deliver pressurized air to the bathtub seal chamber. A gas turbine engine is also disclosed.

Bathtub seal for damping CMC vane platform

A method includes forming an airfoil, where the airfoil includes an airfoil wall that has a span between first and second radial ends and defines leading and trailing edges, pressure and suction sides each join the leading and trailing edges, and an internal cavity, the internal cavity is divided into at least first and second sub-cavities that extend over the span, and the first sub-cavity defines a venturi tube. The forming includes i) fabricating a fiber preform of the airfoil around a plurality of mandrels, wherein the mandrel in the first sub-cavity is radially split, and ii) densifying the fiber preform with a ceramic matrix. The airfoil may include an internal cavity that is divided into at least first and second sub-cavities extending over the span, where the first sub-cavity defines a venturi tube.

Airfoil with venturi tube

An article includes a ceramic matrix composite (CMC) vane arc segment for disposal about an engine central axis. The CMC vane arc segment includes first and second platforms and an airfoil section that extends therebetween. The airfoil section defines a radial stacking axis that is oblique to a Z-axis that is perpendicular to the engine central axis such that the radial stacking axis forms a non-zero angle with the Z-axis.

Tilted CMC vane arc segment

An airfoil includes an airfoil wall that has a span between first and second radial ends and that defines leading and trailing edges, pressure and suction sides each joining the leading and trailing edges, and an internal cavity. The internal cavity is divided into at least first and second sub-cavities extending over the span. The first sub-cavity defines a venturi tube.

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

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.

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South Glastonbury, CT, United States of America

Cheng Gao