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Edward A Rainous

from Cincinnati, OH
Age ~66

Edward Rainous Phones & Addresses

  • 9659 Timbermill Ct, Cincinnati, OH 45231 (513) 522-6565
  • Wyoming, OH

Work

Company: Quest global Position: Consulting engineer

Resumes

Resumes

Edward Rainous Photo 1

Consulting Engineer

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Location:
Cincinnati, OH
Work:
Quest Global
Consulting Engineer

Publications

Us Patents

Methods And Apparatus For Turbine Nozzle Locks

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US Patent:
6773228, Aug 10, 2004
Filed:
Jul 3, 2002
Appl. No.:
10/188438
Inventors:
Edward Atwood Rainous - Cincinnati OH
Charles Louis Williams - Loveland OH
Michael Peter Murphy - Loveland OH
Janice Ilene Pirtle - Milford OH
James Harold Joy - Batavia OH
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 904
US Classification:
415189, 4152093, 2988922
Abstract:
A method enables a gas turbine engine nozzle to be secured within an engine casing that includes an exterior surface. The method comprises the steps of forming a first opening to extend through the engine casing, inserting a nozzle lock through the first opening from the casing exterior surface, coupling the nozzle lock to a portion of the nozzle, and securing the nozzle lock to the engine casing.

Ice Shed Reduction For Leading Edge Structures

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US Patent:
8245981, Aug 21, 2012
Filed:
Apr 30, 2008
Appl. No.:
12/112733
Inventors:
Edward Atwood Rainous - Cincinnati OH, US
Barry Lynn Allmon - Maineville OH, US
Jeffre Gerry Loewe - Cincinnati OH, US
William Clarke Brooks - Lebanon OH, US
Lee Alan Blanton - Cincinnati OH, US
Courtney James Tudor - Cincinnati OH, US
Vicky Showalter Budinger - Loveland OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
B64C 21/00
B64C 1/38
US Classification:
2442001, 244130
Abstract:
A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.

Containment Cases And Method Of Manufacture

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US Patent:
8333558, Dec 18, 2012
Filed:
Mar 5, 2008
Appl. No.:
12/042692
Inventors:
Scott Roger Finn - Niskayuna NY, US
Deepali Bhate - Rexford NY, US
Curt Brian Curtis - West Chester OH, US
Stephen Mark Whiteker - Covington KY, US
Qi Zhu - Niskayuna NY, US
Lee Alan Blanton - Cincinnati OH, US
Edward Atwood Rainous - Cincinnati OH, US
Assignee:
General Electric Company - Niskayuna NY
International Classification:
F01D 21/00
US Classification:
415200, 415 9, 4151731, 4151733
Abstract:
A containment case comprises a composite core, with an inner surface, and at least one ceramic layer integrated with the composite core. The at least one ceramic layer is bonded to the inner surface of the composite core with a resin. In another embodiment, a containment case comprises a composite core, with an inner surface, and a hybrid material comprising at least one ceramic material and at least one non-ceramic material. The hybrid material is disposed on the inner surface of the composite core. The hybrid material is bonded to the inner surface of the composite core with a resin. A method of fabricating a containment case includes the steps of disposing one or more layers of ceramic fabric on an inner surface of a composite core, infusing the composite core and the one or more layers of ceramic fabric with resin, and curing the resin.

Ice Shed Reduction For Leading Edge Structures

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US Patent:
7992823, Aug 9, 2011
Filed:
Apr 30, 2008
Appl. No.:
12/112660
Inventors:
Edward Atwood Rainous - Cincinnati OH, US
Barry Lynn Allmon - Maineville OH, US
Jeffre Gerry Loewe - Cincinnati OH, US
William Clarke Brooks - Lebanon OH, US
Lee Alan Blanton - Cincinnati OH, US
Courtney James Tudor - Cincinnati OH, US
Vicky Showalter Budinger - Loveland OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
B64D 15/00
US Classification:
244134E, 252 70, 106 13, 106 1412
Abstract:
A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation; and a metallic icephobic plating comprising nickel applied to at least a portion of the flowpath surface.

Laser Shock Peened Gas Turbine Engine Compressor Airfoil Edges

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US Patent:
20070243071, Oct 18, 2007
Filed:
Aug 17, 2005
Appl. No.:
11/205959
Inventors:
Seetha Mannava - Cincinnati OH, US
James Rhoda - Mason OH, US
Herbert Halila - Cincinnati OH, US
Larry Jacobs - Loveland OH, US
Edward Rainous - Cincinnati OH, US
International Classification:
F03B 3/12
US Classification:
41624100R
Abstract:
Gas turbine engine compressor component that has an airfoil such as a compressor blade with a metallic airfoil having a leading edge and a trailing edge and at least one laser shock peened surface extending radially along at least a portion of the leading edge and a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface.

Integrated Nacelle Assembly

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US Patent:
20110146230, Jun 23, 2011
Filed:
Jun 30, 2010
Appl. No.:
12/827801
Inventors:
Donald George LaChapelle - Cincinnati OH, US
Christopher Charles Glynn - Lawrenceburg IN, US
Donald Lee Gardner - West Chester OH, US
Stephen Craig Mitchell - West Chester OH, US
Mullahalli Venkataramaniah Srinivas - Mason OH, US
Edward Atwood Rainous - Cincinnati OH, US
David Lance Pennekamp - Hamilton OH, US
International Classification:
F02K 3/02
F04D 29/44
US Classification:
602262, 415200
Abstract:
An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.

Ice Shed Reduction For Leading Edge Structures

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US Patent:
20120312924, Dec 13, 2012
Filed:
Aug 21, 2012
Appl. No.:
13/590970
Inventors:
Edward Atwood Rainous - Cincinnati OH, US
Barry Lynn Allmon - Maineville OH, US
Jeffre Gerry Loewe - Cincinnati OH, US
William Clarke Brooks - Lebanon OH, US
Lee Alan Blanton - Cincinnati OH, US
Courtney James Tudor - Cincinnati OH, US
Vicky Showalter Budinger - Loveland OH, US
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
B64D 15/00
US Classification:
244134 E
Abstract:
A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.
Edward A Rainous from Cincinnati, OH, age ~66 Get Report