United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Kristopher K Anderson

Daniel P Preuss

Nicholas J Madonna

Dominic J Mongillo, Jr

Justin M Aniello

Sarah Riley

Jeffrey R Levine

Jeffrey Michael Jacques

Shawn M McMahon

Christopher Whitfield

Richard M Salzillo

Mark A Boeke

Brett Alan Bartling

Christopher Perron

Jason B Moran

Melissa Shallcross

Stephanie Tanner

Jeffrey J De Gray

Christina A Ryan

Jr Dominic J Mongillo

Jr Richard M Salzillo

Jeffrey J Degray

Vane assemblies for gas turbine engines are described. The vane assemblies include a platform having an interior platform surface, a forward rail, and an aft rail, wherein the interior platform surface, the forward rail, and the aft rail define a plenum, an airfoil extending radially inward from the platform on a side opposite the forward and aft rails, the airfoil having a leading edge cavity and a baffle installed within the leading edge cavity, and platform feed structure arranged on the platform in the plenum and defining a fluid path through the forward rail and into the baffle of the leading edge cavity.

Vane forward rail for gas turbine engine assembly

A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.

Vane core assemblies and methods

Vane assemblies are described. The vane assemblies include a platform, an airfoil extending from the platform, a forward rail extending from the platform and arranged along a forward side of the platform, and an aft rail extending from the platform and arranged along an aft side of the platform. At least one support beam is provided extending in a forward-aft direction between the forward rail and the aft rail and separated from the platform by a first distance. The at least one support beam has a thickness in a radial direction of 40% or less of a total radial extent from the platform to an outer diameter edge of at least one of the forward rail and the aft rail and the at least one support beam has a thickness in a circumferential direction of 30% or less of a total circumferential extent of vane assembly.

Rail support beams

A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.

Turbine vane cluster including enhanced vane cooling

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

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

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Manchester, CT, United States of America

Kristopher K Anderson