United Technologies Corporation

Siemens Aktiengesellschaft

Siemens Energy, Inc.

Florida Turbine Technologies, Inc.

Siemens Westinghouse Power Corporation

Jesse Eng

Cheryl A Schopf

Clinton A Mayer

John Carl Glessner

Arthur J Harris, Jr

Roland Liebe

Stefan Dahlke

Daniel Hofmann

Mark S Maier

David D North

Ronald L Sigworth

Hank Reid

Kenneth Michael Tamaddoni-Jahromi

David Dealba North

Art Harris

A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage.

Heat shield manifold system for a midframe case of a gas turbine engine

An inventive hot gas seal for sealing an opening, e.g. a gap or hole, in a heat shield element or between heat shield elements of a heat shield or a liner comprises at least one resilient portion for providing a force which is designed such that the hot gas seal can be held in said opening by said force and/or that the sealing efficiency of the hot gas seal is increased by said force. Thus, further means for holding the seal in place and/or for increasing the sealing efficiency are not necessary. The invention is particularly useful if the design of said resilient portion is such that the force provides a holding action and increases the sealing efficiency, at the same time.

Hot gas seal

A split ring wedge bearing friction damper for an aero engine that allows the engine to operate without an oil tank, a pump, and a lubricant cooler, the friction damper having a damper ring and a wedge ring that both have wedge surfaces in contact so that an axial load can be applied to the bearing outer race to provide damping to the bearing, and so that the damper ring can also have a radial displacement to produce a radial load on the damper ring against the stator bearing support surface in which the axial load provides the friction damping and the radial load eliminates lost motion for maximum damping.

Split ring wedge bearing damper

A combustor () for a gas turbine engine is provided with a premix pilot fuel stage () in order to reduce the emission of oxides of nitrogen from the engine. An in-service engine may be modified to add the premix pilot fuel stage by delivering premix pilot fuel to a ring manifold () for tip-feeding a premix pilot fuel outlet member such as a swirler vane () or fuel peg (). In this manner, complex and expensive components such as the top hat (), support housing () and diffusion pilot burner assembly () may be used without modification. Thermal stresses caused by the differential cooling of the ring manifold by the premix pilot fuel () are reduced by a heat shield () installed within the manifold.

Premixed pilot burner for a combustion turbine engine

The last stages of a compressor section of a gas turbine engine that utilizes a drum rotor and segmented stator supported to an axially split outer case suspends the segmented stator case to a full hoop outer case so that the segmented stator displaces axially and thermally grows circumferentially while being constrained radially. A method of assembly and disassembly of the full hoop outer case is provided.

Compressor case construction

A seal is provided for preventing passage of working medium gases between the roots of the rotor blades of a gas turbine engine and the rotor thereof. The seal comprises a compressed laminar exfoliated graphite piece placed in the cavity between the root of the rotor blade and the receiving slot in the rotor disk, which piece expands upon heating to seal said cavity.

Expandable blade root sealant

The performance of a TOBI for a gas turbine engine is improved by providing bypass apertures in the housing of said TOBI for directing a stream of air into the seal sealing the TOBI compartment and bypassing the nozzles of the TOBI to reduce the size of the plume of the TOBI cooling air.

Growing community of inventors

Jupiter, FL, United States of America

Jesse Eng