Siemens Energy, Inc.

United States of America As Represented by the Secretary of the Air Force

Jerome H Katy

David James Wiebe

Adam Wallace

Alexander Ralph Beeck

Malberto Gonzalez

Cheryl A Schopf

Richard Seleski

Benjamin G Hettinger

Harry Patat

Perry P Sifford

A turbine assembly having an outer casing (), an inner structural ring (), and an annular gas path () defined between outer and inner flow path walls () for conducting a gas flow through the turbine assembly. A plurality of structural struts () are spaced apart in a circumferential direction, each strut () including a strut body () extending in a radial direction for supporting the inner structural ring () to the outer casing (). A first strut end () at a radially outer end of the strut body () is detachably attached to the outer casing () with a first fastener structure () engaging the outer casing (), and a second strut end () at a radially inner end of the strut body () is detachably attached to the inner structural ring () with a second fastener structure () engaging the inner structural ring ().

Turbine assembly with detachable struts

A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.

Purge and cooling air for an exhaust section of a gas turbine assembly

A support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall.

Gas turbine engine with angled and radial supports

An improved blade outer air cooling system for aircraft jet engines is disclosed. An integrated substrate backplate, cooling impingement plate and manifold replaces a conventional substrate backplate supporting a seal surface. A cooling impingement plate is mounted on the back of the backplate and a manifold is mounted over the impingement plate. The combined seal surface and new substrate outer air seal assembly attaches to the engine case structure through flange hooks formed as part of the manifold. A support supports the manifold inside the case structure and includes an opening for cooling air to enter an inlet into the manifold. A metal seal ring is compressed between the manifold and the support. The backplate includes holes for exhausting or purging cooling air after impinging on the backplate. The backplate, impingement plate and manifold may be welded, brazed or otherwise united together.

Blade outer air seal cooling system

Growing community of inventors

Palm Beach Gardens, FL, United States of America

Jerome H Katy