Raytheon Technologies Corporation

United Technologies Corporation

David J Sander

Jonathan Lemoine

Shelton O Duelm

John J Korzendorfer

Harvey C Lee

Witt C Guinn

Dalton C Petrillo

Kelly A Vanston

A heat shield provided with a gas turbine engine includes a heat shield body extending between a first heat shield end and a second heat shield end. The heat shield body has an exterior surface disposed proximate an inner surface of a first case and an interior surface disposed opposite the exterior surface. The interior surface defines a rib that extends towards a combustor vane support lock.

Gas turbine engine having a heat shield

A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape and a groove formed circumferentially along an inner surface of the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The groove in the heat shield may be configured to retain the tab of the support lock.

Heat shield with axial retention lock

A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape. The heat shield may define an aperture extending through the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The aperture in the heat shield may be configured to retain the tab of the support lock.

A method of assembling an attachment structure of a gas turbine engine includes providing a frame that has a first annular case, an inner annular case spaced radially inwardly from the first annular case, and a plurality of vanes extending between the inner case and the first annular case, providing a second annular case that extends around the frame, the first annular case and the second annular case include a plurality of interlocks, each of the plurality of interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second annular case, and inserting the first member in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.

Gas turbine engine attachment structure and method therefor

A heat shield assembly for an engine case of a gas turbine engine may include a heat shield having an annular shape. A first groove may be formed circumferentially along an inner surface of the heat shield. A support lock may have a second groove extending radially inward from a distal surface of the support lock. A retention ring may be configured to fit within the first groove of the heat shield and the second groove of the support lock.

Heat shield with axial retention

An attachment structure for a gas turbine engine includes a frame that has a first annular case. A second annular case extends around the frame. The first annular case and the second annular case include a plurality of interlocks. Each of the interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second case. The first member is received in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.

An exemplary laser instrumentation bracket includes a support structure providing a recess configured to receive a collar of a laser housing. The laser housing has a main body extending axially through an aperture of the support structure when the recess receives the collar.

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South Windsor, CT, United States of America

David J Sander