United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Gregg, Shawn J.

Riley, Sarah

Boeke, Mark A.

Salzillo, Richard M.

Degray, Jeffrey J.

Mark A Boeke

Jeffrey J DeGray

Richard M Salzillo

Sarah Riley

Shawn J Gregg

Kevin Rajchel

Nicholas M LoRicco

Jeffrey R Levine

Tracy A Propheter-Hinckley

Dominic J Mongillo, Jr

Russell J Bergman

Edwin Otero

Andrew S Aggarwala

Daniel A Snyder

Kyle C Lana

Michael N Task

Mosheshe Camara-Khary Blake

Kristopher K Anderson

Vincent E Simms

Allison Mainelli

Guillermo J Fernandez

Jeffrey J De Gray

Richard Salzillo, Jr

Jr Richard M Salzillo

Jeffrey J Degray

Richard M Salzillo Jr

An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of a platform of the upstream airfoil assembly, an upstream segment of a platform of the downstream airfoil assembly and a nub that projects radially outward from the upstream segment. The downstream portion and the upstream segment are spaced from one-another defining a cooling cavity therebetween for the flow of cooling air. The portion and segment overlap axially such that the nub is axially aligned to the downstream portion for improved cooling effectiveness and a reduction of core airflow into the cooling cavity.

Low loss airfoil platform rim seal assembly

A stator vane rail is provided. The stator vane rail may comprise a forward rail, an aft rail located axially opposite the forward rail, a first axial surface extending between the forward rail and the aft rail, a first feather seal slot disposed in the first axial surface, wherein a terminus of the first feather seal slot is radially spaced from a radial surface of the aft rail, a second axial surface extending between the forward rail and the aft rail, and a second feather seal slot disposed in the second axial surface, wherein the second feather seal slot extends from the radial surface of the aft rail.

Vane intersegment gap sealing arrangement

A cooled component for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis of the gas turbine engine. The internal ribs are disposed within an internal cavity defining cooling air passages within the cooled component. A plurality of cooling holes are arranged in rows with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes is disposed on a side opposite the internal rib relative to a corresponding internal opening. A gas turbine engine and a method of fabricating a turbine airfoil are also disclosed.

Cooled turbine vane with alternately orientated film cooling hole rows

A flow path component includes a platform having at least one radially aligned face. A chordal seal extends axially from the radially aligned face. The chordal seal includes a first curved face configured to prevent edge line contact under deflection conditions while the flow path component is installed in an engine.

Flowpath component for a gas turbine engine including a chordal seal

An article includes a body that has a coating thereon. The coating has a first portion disposed on a first section of the body and a second portion disposed on a second, different section of the body. The first portion has a first microstructure and the second portion has a second, different microstructure.

Multiple coating configuration

A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

Turbine vane cooling arrangement

A section of a gas turbine engine according to an exemplary aspect of this disclosure includes, among other things, a vane assembly including a featherseal slot. The section further includes a featherseal at least partially received in the featherseal slot. The featherseal includes a radial portion having at least one tapered side.

Featherseal having tapered radial portion

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.

Gas turbine engine component with discharge slot having oval geometry

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.

Gas turbine engine component having variable width feather seal slot

An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface. A recess is in an interior surface of the airfoil wall adjacent the fillet. A baffle tube is located in the airfoil cavity spaced from the recess.

Gas turbine engine airfoil

An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.

Cooling feed orifices

An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.

Chordal seal

An airfoil of a turbine engine may have internal passages to permit the travel of cooling air through the airfoil. Multiple airfoils may be formed together in a stator vane assembly, and cooling air may be directed through the stator vane assembly. The stator vane assembly may be mounted to an engine structure to carry structural loads experienced by the stator vane assembly. Buttresses may be formed in the stator vane assembly, such as beneath each airfoil of the stator vane assembly, and extending into a passage permitting the travel of cooling air through the airfoil. The buttresses may enhance the strength and stability of the stator vane assembly by facilitating the transmission of structural loads to an engine structure. A channel may be defined through one or more buttress to enable the passage of cooling air into the airfoils, and yet allow the buttresses to carry structural loads.

Support buttress

An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.

Airfoil with variable trip strip height

A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.

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Plainville, CT, United States of America

Mark A Boeke