Patents by Inventor Edward Atwood Rainous
Edward Atwood Rainous has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 8876042Abstract: 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.Type: GrantFiled: June 30, 2010Date of Patent: November 4, 2014Assignee: General Electric CompanyInventors: Donald George LaChapelle, Christopher Charles Glynn, Donald Lee Gardner, Stephen Craig Mitchell, Mullahalli Venkataramaniah Srinivas, Edward Atwood Rainous, David Lance Pennekamp
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Patent number: 8333558Abstract: 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.Type: GrantFiled: March 5, 2008Date of Patent: December 18, 2012Assignee: General Electric CompanyInventors: Scott Roger Finn, Deepali Bhate, Curt Brian Curtis, Stephen Mark Whiteker, Qi Zhu, Lee Alan Blanton, Edward Atwood Rainous
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Publication number: 20120312924Abstract: 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.Type: ApplicationFiled: August 21, 2012Publication date: December 13, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Edward Atwood Rainous, Barry Lynn Allmon, Jeffre Gerry Loewe, William Clarke Brooks, Lee Alan Blanton, Courtney James Tudor, Vicky Showalter Budinger
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Patent number: 8245981Abstract: 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.Type: GrantFiled: April 30, 2008Date of Patent: August 21, 2012Assignee: General Electric CompanyInventors: Edward Atwood Rainous, Barry Lynn Allmon, Jeffre Gerry Loewe, William Clarke Brooks, Lee Alan Blanton, Courtney James Tudor, Vicky Showalter Budinger
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Patent number: 7992823Abstract: 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.Type: GrantFiled: April 30, 2008Date of Patent: August 9, 2011Assignee: General Electric CompanyInventors: Edward Atwood Rainous, Barry Lynn Allmon, Jeffre Gerry Loewe, William Clarke Brooks, Lee Alan Blanton, Courtney James Tudor, Vicky Showalter Budinger
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Publication number: 20110146230Abstract: 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.Type: ApplicationFiled: June 30, 2010Publication date: June 23, 2011Inventors: Donald George LaChapelle, Christopher Charles Glynn, Donald Lee Gardner, Stephen Craig Mitchell, Mullahalli Venkataramaniah Srinivas, Edward Atwood Rainous, David Lance Pennekamp
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Publication number: 20090272095Abstract: 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.Type: ApplicationFiled: April 30, 2008Publication date: November 5, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Edward Atwood Rainous, Barry Lynn Allmon, Jeffre Gerry Loewe, William Clarke Brooks, Lee Alan Blanton, Courtney James Tudor, Vicky Showalter Budinger
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Publication number: 20090272850Abstract: 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.Type: ApplicationFiled: April 30, 2008Publication date: November 5, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Edward Atwood Rainous, Barry Lynn Allmon, Jeffre Gerry Loewe, William Clarke Brooks, Lee Alan Blanton, Courtney James Tudor, Vicky Showalter Budinger
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Publication number: 20090226310Abstract: 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.Type: ApplicationFiled: March 5, 2008Publication date: September 10, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Scott Roger Finn, Deepali Bhate, Curt Brian Curtis, Stephen Mark Whiteker, Qi Zhu, Lee Alan Blanton, Edward Atwood Rainous
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Patent number: 6773228Abstract: 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.Type: GrantFiled: July 3, 2002Date of Patent: August 10, 2004Assignee: General Electric CompanyInventors: Edward Atwood Rainous, Charles Louis Williams, Michael Peter Murphy, Janice Ilene Pirtle, James Harold Joy
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Publication number: 20040005217Abstract: 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.Type: ApplicationFiled: July 3, 2002Publication date: January 8, 2004Inventors: Edward Atwood Rainous, Charles Louis Williams, Michael Peter Murphy, Janice Ilene Pirtle, James Harold Joy