United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Untied Technologies Corporation

Raytheon Technology Corporation

Steven D Porter

San Quach

John T Ols

Jon E Sobanski

Kevin Zacchera

Jonathan Lemoine

Anthony P Cherolis

Paul K Sanchez

Seth A Max

Dennis M Moura

Joshua Daniel Winn

Christopher Whitfield

Shawn M McMahon

Nicholas Waters Oren

Richard N Allen

Sean D Bradshaw

Noah Wadsworth

Jorge I Farah

Julian Partyka

John W Mubeezi

Steven J Bullied

Carl R Verner

Gregory E Reinhardt

Donald William Peters

Christopher Treat

James P Bangerter

Joseph James Sedor

Jonathan P Burt

David T Feindel

Thomas A Mariano

Raymond S Hummel

Caroline Karanian

Sandra S Pinero

Jonathan J Jakiel

James B Park

Amy M Gordon

Conway Chuong

James Tilsley Auxier

Jonathan Jeffery Eastwood

Zhongtao Dai

Matthew Budnick

Shelton O Duelm

Kyle C Lana

Alberto A Mateo

John H Mosley

Jeffrey Jay Lienau

Fumitaka Ichihashi

Alex J Schneider

Renee J Jurek

Corneil S Paauwe

Jeremy Styborski

Karl A Mentz

Eva Wong

David Bitzko

Tracy A Propheter-hinckley

Cara M Redding

Lauryn M Curtis

Seth Max

Carolina Karanian

Noah Wadswoth

Joshua David Winn

In one aspect, a panel for lining a combustor shell of a combustor of a gas turbine engine includes a front surface configured to face a combustion chamber and a back surface configured to face the combustor shell, a plurality of cooling holes extending from the back surface to the front surface, a rail extending from the back surface and defining a perimeter of the panel, and a plurality of studs disposed adjacent to and connected to the rail. The rail is configured to contact the combustor shell. The plurality of studs are configured to be received in a plurality of holes of the combustor shell. The plurality of studs is asymmetrically arranged around the perimeter of the panel.

Combustor panel with rail integrated perimeter studs

A brush seal system includes a component including a first mating surface. The brush seal system further includes a brush seal including a brush seal backing plate, a retaining ring, and a plurality of bristles retained between the brush seal backing plate and the retaining ring. The brush seal backing plate includes a second mating surface mounted to the first mating surface. The brush seal system further includes at least one cooling channel extending from an exterior side of the component to an interior side of the component so as to bypass the brush seal.

Combustor to vane sealing assembly and method of forming same

An aerodynamic component of a gas turbine engine is provided and is fittable to a shell having a shell shape. The aerodynamic component includes a body having a component shape initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell. Deviation of the component shape from the shell shape aids in an establishment of a final desired shape of the aerodynamic component following the assembly operation.

Aerodynamic component for a gas turbine engine

A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.

Multi-direction hole for rail effusion

A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface and a plurality of holes, each hole including a central axis having vector components defined by a common vector.

Pull-plane effusion combustor panel

A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.

Turbine vane with platform pad

A heat shield panel for a combustor of a gas turbine engine including a panel body having a first surface and a second surface. The second surface being configured to be oriented toward a combustor liner of the combustor. The heat shield further includes a plurality of first pin fins projecting from the second surface of the panel body. Each of the plurality of first pin fins has a rounded top opposite the second surface. The heat shield further includes a plurality of second pin fins projecting from the second surface of the panel body. Each of the plurality of second pin fins has a flat top opposite the second surface. The plurality of second pin fins are intermittently spaced amongst the plurality of first pin fins. The plurality of second pin fins are organized in a uniform distribution across the second surface of the heat shield panel.

Backside features with intermitted pin fins

A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area. The combustor includes: a shell having a kink; and a kinked heat shield panel in facing spaced relationship with the shell, the kinked heat shield panel including a kink located proximate the kink in the shell, wherein the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface.

Combustor heat shield panel

A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.

Conformal seal and vane bow wave cooling

A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, and a rail disposed about a periphery of the cold side, the rail including a first rail member having a first length extending along the panel, a first height extending from the cold side, and a first thickness that varies along the first length.

Tapered panel rail

Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling

A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.

Gas turbine engine turbine vane ring arrangement

A gas-turbine engine is provided. The gas-turbine engine comprises a high pressure turbine with an aft blade platform. A static structure may be disposed aft of the high pressure turbine and proximate a cavity defined by the aft blade platform. A vane of the static structure may have a vane platform with a shaped tip extending into the cavity.

Hardware geometry for increasing part overlap and maintaining clearance

Growing community of inventors

Wethersfield, CT, United States of America

Steven D Porter