United Technologies Corporation

Raytheon Technologies Corporation

Blake J Luczak

James Thompson Beals

Matthew A Devore

Eric L Couch

Dominic J Mongillo, Jr

Paul M Lutjen

Eric A Hudson

Joseph Parkos, Jr

Gary L Grogg

Christopher R Joe

James N Knapp

Glenn A Cotnoir

John D Wiedemer

Thomas M Morin

Michael F Benamati

Joseph J Parkos Jr

A blade for a gas turbine engine includes composite layers including neck plies and tooth plies that are flared relative to the neck plies. The neck plies and tooth plies respectively provide a neck and a root. The root includes a tooth. A Wedge is provided by wedge plies adhered over the root and the tooth.

Blade wedge attachment lay-up

A rotor includes a rotor hub, a plurality of blades mounted in a circumferentially-spaced arrangement on the rotor hub and a plurality of platform segments circumferentially arranged, respectively, between neighboring ones of the blades. The platform segments include core gas-path defining surfaces and are mounted with a freedom to circumferentially move relative to the neighboring ones of the blades.

Non-integral blade and platform segment for rotor

A rotor includes a disk that has slots circumferentially arranged around its periphery. Blades include respective roots that are mounted in respective ones of the slots. The roots are smaller than the slots such that there are circumferential gaps between the roots and circumferential sides of the slots. Wedges are respectively located within the circumferential gaps. The wedges are free floating with regard to the blades and the disk.

Blade wedge attachment

A blade root shim comprises a base, a suction side shim wall, a pressure side shim wall, and a contact relief region. The base extends longitudinally between a leading shim end and a trailing shim end. The suction side shim wall extends along the base and corresponds to a suction side blade root bearing surface. The pressure side shim wall, spaced circumferentially apart from the suction shim wall, corresponds to a pressure side blade bearing surface. The contact relief region is formed into an upper wall portion of either the suction side shim wall or the pressure side shim wall.

CMC blade attachment shim relief

A seal assembly for a gas turbine engine includes a seal body and a biasing support member. The seal body includes a generally annular shape that defines an outer diameter surface. The biasing support member is circumferentially disposed about the outer diameter surface of the ceramic matrix composite seal body and includes an array of spring fingers that circumferentially overlap about the biasing support member. The array of spring fingers contacts the seal body and centers the seal body relative to the centerline axis of the gas turbine engine.

Seal assembly for gas turbine engine

Removing of a casting core from a metal casting leaves at least one opening in a surface of the metal. The opening is filled with a sacrificial material. The metal and sacrificial material are machined at the opening. After the machining, a remainder of the sacrificial material is removed.

Method of machining parts having holes

An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. The metallic casting core includes a plurality of body sections. The first region is along at least some of the body sections. The metallic casting core includes a plurality of springs spanning gaps between adjacent body sections and unitarily formed therewith.

Investment casting cores and methods

An airfoil for a gas turbine engine component such as a turbine blade or a vane includes at least one microcircuit cooling channel having a plurality of sub-channels extending along a radial direction of the airfoil. The plurality of channels are axially spaced, and are fed by radially spaced inlets.

Turbine component with axially spaced radially flowing microcircuit cooling channels

A method for manufacturing an investment casting core uses a metallic blank having a thickness between parallel first and second faces less than a width and length transverse thereto. The blank is locally thinned from at least one of the first and second faces. The blank is through-cut across the thickness.

Contoured metallic casting core

A method involves forming a core assembly. The forming includes molding a first ceramic core over a first refractory metal core to form a core subassembly. The subassembly is assembled to a second ceramic core.

In a method for manufacturing a combination investment casting core, a plurality of cores are each formed by cutting a metallic sheet to define a first portion and a number of separate second portions linked by the first portion. The second portions are bent out of local alignment with the first portion. The first portions of the cores are assembled and secured to each other.

Investment casting core assembly

A turbine outer air seal includes, in a radially inner major surface thereof, at least one circumferential groove accommodating a plurality of holes which supply air for film cooling the radially inner surface of the air seal.

Turbine outer air seal

A cooled cast part has an exterior surface. A cooling passageway system extends from at least one inlet port to a plurality of outlet ports. The passageway system includes a first passageway to at least a first of the outlets and surrounding at least one post. The system includes a second passageway to at least a second of the outlets passing through the at least one post.

Growing community of inventors

Manchester, CT, United States of America

Blake J Luczak