United Technologies Corporation

Raytheon Technologies Corporation

Alliant Techsystems Inc.

Orbital Atk, Inc.

Pw Power Systems, Inc.

Henry K Webster

Daniel P Guinan

Christopher D Gettinger

James B Philpott

Michael G McCaffrey

Jonathan Jeffery Eastwood

Jonathan Ariel Scott

John J Korzendorfer

Graham Ryan Philbrick

Fabian D Betancourt

Joseph F Englehart

Charles C Wu

Richard Seleski

Andrew P Boursy

Kevin W White

Fernando K Grant

Randall J Brown

Christopher William Moore

ChaiDee Woods Brown

Alan D Lees

Mark A Sillence

Thomas B Fortin

Sergio Rinella

Alexander Sankovich

Revi K Nigam

Costante Salvador

Dennis J Nemecek

An annular finger seal includes a base portion defining a base edge of the annular finger seal and having a center pass-through aperture. The base edge may be substantially continuous. The annular finger seal may also include a finger portion defining a finger edge of the annular finger seal and including a plurality of fingers. The finger edge may be segmented by gaps disposed between adjacent fingers of the plurality of fingers. A gas turbine engine includes a combustor section, a turbine section, and an annular finger seal. The annular finger seal includes a plurality of fingers and the annular finger seal is disposed at an adjoining interface between the combustor section and the turbine section. The annular finger seal may be mounted to the turbine section and may engage a radially inward facing surface, relative to the engine central longitudinal axis, of the combustor section.

Combustor finger seal

A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.

Gas turbine engine active clearance control system using inlet particle separator

A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support, the heat shield assembly forms an outer diameter directed toward an inner vane platform of the power turbine vane array.

Power turbine heat shield architecture

Methods and apparatus of an improved cooling structure having cooling passages are provided. A method includes forming pilot holes with an electrical discharge machine (EDM) drill near a heated flow surface. The pilot holes are then shaped with a wire EDM into cooling passages having a desired shape.

Method of manufacturing heat exchanger cooling passages in aero propulsion structure

The present invention relates to a scram jet engine for use with a hypersonic vehicle. The scram jet engine has an upper boundary wall, a lower boundary wall, and a plurality of side walls defining an inner air flowpath. The walls are formed by a plurality of tubular heat exchanger panels. Each of the heat exchanger panels comprises a plurality of structural panels, each having a plurality of cooling passages, joined together. In the scram jet engine of the present invention, fuel may be used as a coolant and supplied to the cooling passage.

Scram jet engine design

Growing community of inventors

Jupiter, FL, United States of America

Henry K Webster