United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Kevin L Rugg

Gabriel L Suciu

Jose E Ruberte Sanchez

Timothy J McAlice

Brian D Merry

Michael G McCaffrey

Daniel Bernard Kupratis

Mark F Zelesky

Thomas N Slavens

Tania Bhatia Kashyap

Ioannis Alvanos

John D Riehl

Douglas Michael Berczik

Shelton O Duelm

Arthur W Utay

Winston Gregory Smiddy

Michael G Abbott

Greg C Ojard

Luke B Borkowski

A method of analyzing computed tomography data includes creating a mesh of a sampling surface that extends through a component to obtain a meshed surface; creating a plurality of additional surfaces that are different from each other and from the meshed surface, and that each correspond to one or more of a translation and a rotation of the meshed surface; querying an interpolant function, which is fitted to CT data of the component, at a plurality of points of the meshed surface to project the CT data onto the meshed surface; querying the interpolant function at a plurality of points of the additional surfaces to project the CT data onto the additional surfaces; and determining, for each of the plurality of points of the meshed surface, whether the point is a void based on the querying for the meshed surface and the querying for the additional surfaces.

Method and apparatus for analyzing computed tomography data

A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.

Attachment of ceramic matrix composite panel to liner

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The engagement portion defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines an elongated opening to the internal cavity. A method of sealing is also disclosed.

Seal assembly for gas turbine engine

A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.

Split compressor turbine engine

An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.

Twin centrifugal single spool engine

An airfoil includes a core with a first Young's Modulus; and an outer section at least partially surrounding the core with a second Young's Modulus, wherein the first Young's Modulus is higher than the second Young's Modulus.

Composite airfoil

A blade for a gas turbine engine includes composite layers that include a uni-directional layer and a fabric compliant wedge layer that are arranged adjacent to the uni-directional layer. The fabric compliant wedge layer has a reduced compressive Young's modulus compared to the uni-directional layer.

Composite blade root lay-up

One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first attachment member including an opening, a second attachment member including a loop at least partially extending through the opening, and a pin between the first attachment member and the loop.

Attachment assembly for protective panel

A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes a first multiple of CMC plies which define a suction side, a first airfoil portion of the first multiple of CMC plies at least partially parallel to an airfoil axis. A second multiple of CMC plies define a pressure side, a second airfoil portion of the second multiple of CMC plies at least partially parallel to the airfoil axis and bonded to the first airfoil portion.

Growing community of inventors

Fairfield, CT, United States of America

Kevin L Rugg