Henry K Webster

US Patent:

6715293, Apr 6, 2004

Filed:

Mar 28, 2002

Appl. No.:

10/112635

Inventors:

Mark A. Sillence - Juno Isles FL
Daniel P. Guinan - Hobe Sound FL
Dennis J. Nemecek - Port St. Lucie FL
Costante Salvador - Palm Beach Gardens FL
Henry K. Webster - Jupiter FL
Thomas B. Fortin - Sunrise FL
Sergio Rinella - West Palm Beach FL
Revi K. Nigam - Palm City FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F02K 714

US Classification:

60768, 60267, 60767, 166169

Abstract:

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.

US Patent:

20100108289, May 6, 2010

Filed:

Jul 30, 2009

Appl. No.:

12/512515

Inventors:

Daniel P. Guinan - Hobe Sound FL, US
James B. Philpott - Lake Worth FL, US
Henry K. Webster - Jupiter FL, US
Christopher Gettinger - Palm Beach Gardens FL, US

International Classification:

F24H 9/02
B23H 5/04
B21D 53/02

US Classification:

165 53, 219 6917, 2989003

Abstract:

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.

US Patent:

20190078514, Mar 14, 2019

Filed:

Sep 11, 2017

Appl. No.:

15/700328

Inventors:

- Farmington CT, US
Joseph F. Englehart - Gastonia NC, US
Graham Ryan Philbrick - Durham CT, US
Henry K. Webster - Jupiter FL, US
Richard Seleski - Palm Beach Gardens FL, US
Michael G. McCaffrey - Windsor CT, US

International Classification:

F02C 7/05
F01D 11/24
F02C 7/18
B64D 33/02

Abstract:

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.

US Patent:

20180030844, Feb 1, 2018

Filed:

Aug 1, 2016

Appl. No.:

15/225179

Inventors:

- Farmington CT, US
Henry K. Webster - Jupiter FL, US
Jonathan Ariel Scott - Southington CT, US
Randall J. Brown - East Windsor CT, US
Alan D. Lees - Manchester CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Farmington CT

International Classification:

F01D 11/00
F02C 7/28
F01D 9/02
F02C 3/14

Abstract:

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.

US Patent:

20160102568, Apr 14, 2016

Filed:

Oct 13, 2014

Appl. No.:

14/512523

Inventors:

- Glastonbury CT, US
Fabian D. Betancourt - Meriden CT, US
John J. Korzendorfer - Glastonbury CT, US
Andrew P. Boursy - Marlborough CT, US
Alexander Sankovich - Hebron CT, US
Henry K. Webster - Jupiter FL, US
Christopher W. Moore - Ellington CT, US
Charles C. Wu - Glastonbury CT, US

International Classification:

F01D 9/06
F01D 25/12
F01D 9/04

Abstract:

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.

US Patent:

20150174710, Jun 25, 2015

Filed:

Mar 26, 2014

Appl. No.:

14/225926

Inventors:

- Minneapolis MN, US
James B. Philpott - Lake Worth FL, US
Henry K. Webster - Jupiter FL, US
Christopher Gettinger - Palm Beach Gardens FL, US

Assignee:

Alliant Techsystems Inc. - Minneapolis MN

International Classification:

B23P 15/26
F24H 9/02

Abstract:

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.