Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Jeremy Styborski

William P Stillman

Corey D Anderson

Alexander Broulidakis

Michael A Disori

Alex J Schneider

Adam J Diener

Dominic J Mongillo, Jr

Thomas N Slavens

San Quach

Matthew A Devore

Steven D Porter

James Tilsley Auxier

Zhongtao Dai

Dave J Hyland

Lea Kennard Castle

Corneil S Paauwe

Rodney H Warner

David J Hyland

Caroline Karanian

Eva Wong

James Tisley Auxier

Lauryn M Curtis

A featured embodiment of a cast plate heat exchanger assembly includes a cast plate including a plate portion defining a plurality of internal passages. A plurality of fin portions extend from the plate portion. First augmentation structures are disposed on surfaces of the fin portions for conditioning cooling airflow to enhance transfer of thermal energy. A method is also disclosed.

Heat augmentation features in a cast heat exchanger

A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; and a second component having a first surface, a second surface opposite the first surface of the second component, and an impingement slot extending from the second surface of the second component to the first surface of the second component, the second surface of the first component and the first surface of the second component defining a cooling channel therebetween in fluid communication with the impingement slot, wherein the impingement slot is in fluid communication with the second surface of the first component, wherein the impingement slot includes a slot tab configured to direct airflow into the cooling channel at least partially in a lateral direction parallel to the second surface of the first component such that a cross flow is generated in the cooling channel.

And manufacturing process for directed impingement punched plates

A component for a gas turbine engine may comprise a cooling channel. A first trip strip may extend from a wall of the cooling channel. A leg of the first trip strip and a first plane orthogonal to a direction of airflow through the cooling channel may form a first angle. A second trip strip may be downstream from the first trip strip and extending from the wall of the cooling channel. A leg of the second trip strip and a second plane orthogonal to the direction of airflow through the cooling channel may form a second angle different from the first angle.

Variably skewed trip strips in internally cooled components

A combustor of a gas turbine engine including a first forward liner panel. The forward liner panel including a liner panel forward edge, a liner panel aft edge opposite of the liner panel forward edge, and a first liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first liner panel side edge is non-perpendicular to the liner panel forward edge and oriented at an angle about perpendicular to a swirl flow in the combustor.

Combustor panel configuration with skewed side walls

A heat exchanger assembly includes a plate including a plate portion having a leading edge, a trailing edge, an inlet side and an outlet side. The leading edge of the plate portion includes a terminal tip and a varying radius that decreases in a direction toward the terminal tip. An inlet manifold is on the inlet side. An outlet manifold is on the outlet side. A cast plate for a plate fin heat exchanger is also disclosed.

Shaped leading edge of cast plate fin heat exchanger

An airfoil includes a first wall and a second wall that at least partially define a channel, and a trip strip coupled to the first wall, where at least a part of the trip strip forms a corrugated pattern. A gas turbine engine includes a compressor section, a combustor section, and a turbine section, where the turbine section includes an airfoil, where the airfoil includes a first wall and a second wall that at least partially define a channel, and a trip strip coupled to the first wall, where at least a part of the trip strip forms a corrugated pattern.

Trip strips for augmented boundary layer mixing

A gas turbine engine includes a first vane of a turbine section, a second vane of the turbine section, an impingement plate that includes a first impingement hole and a second impingement hole, and a pipe that supplies a fluid. The first vane includes a first platform. The second vane includes a second platform and a baffle. A first portion of the fluid traverses the first impingement hole and impinges on a first surface of the first platform. A second portion of the fluid traverses the second impingement hole and impinges on a second surface of the second platform. A third portion of the fluid bypasses the impingement plate and enters the baffle.

Cooling arrangement for engine components

Partitioned baffles and components for installation within gas turbine engines are provided. The partitioned baffles include a baffle body defining a first cavity, the baffle body having a first inlet and at least one first impingement hole arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole and a partitioned channel installed within the baffle body and defining a second cavity, wherein the partitioned channel has a second inlet and at least one second impingement hole, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole. The baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source.

Multiple source impingement baffles for gas turbine engine components

A method for evaluating a turbine component includes inducing a thermal response of the component at an initial time, capturing a two-dimensional infrared image of the thermal response of the component with a thermal imaging device, wherein the two-dimensional infrared image comprises a plurality of infrared image pixels, generating a two-dimension to three-dimension mapping template to correlate two-dimensional infrared image data with three-dimensional locations on the component, mapping at least a subset of the plurality of infrared image pixels of the two-dimensional infrared image to three-dimensional coordinates using the mapping template, and generating a three-dimensional infrared image and infrared data of the component from the mapped infrared image pixels to three-dimensional coordinates, wherein the three-dimensional infrared image and infrared data is used to qualify the component for use.

Growing community of inventors

East Hartford, CT, United States of America

Jeremy Styborski