Patents by Inventor Harold Ray Hansel
Harold Ray Hansel 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: 7625174Abstract: A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one catch to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through said gap, such that a portion of the at least one spline seal is received within a recess defined within the turbine nozzle slot to facilitate retaining the at least one spline seal within the turbine nozzle slot.Type: GrantFiled: December 16, 2005Date of Patent: December 1, 2009Assignee: General Electric CompanyInventors: Vincent Marion Drerup, Harold Ray Hansel, Ching-Pang Lee
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Patent number: 7575415Abstract: A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one retainer tab to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through the gap, such that the at least one retainer tab facilitates retaining the retainer tab within the turbine nozzle slot.Type: GrantFiled: November 10, 2005Date of Patent: August 18, 2009Assignee: General Electric CompanyInventors: Vincent Marion Drerup, Harold Ray Hansel, James Anthony Ketzer, Ching-Pang Lee
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Patent number: 6920762Abstract: An assembly for mounting an igniter in a gas turbine engine combustor between an outer casing and an outer liner, wherein a longitudinal centerline axis extends through the gas turbine engine. The igniter mounting assembly includes a first spring member encircling a portion of said igniter and being positioned between a surface adjacent the outer casing and an outer surface of the outer liner, a first ring member connected to a first end of the first spring member adjacent the outer surface of the outer liner, and a second ring member connected to a second end of the first spring member adjacent the surface adjacent the outer casing. Accordingly, the igniter is able to maintain substantial alignment with respect to an opening in the outer liner while moving radially and/or axially with respect to the outer liner as the outer casing experiences thermal growth greater than the outer liner.Type: GrantFiled: January 14, 2003Date of Patent: July 26, 2005Assignee: General Electric CompanyInventors: Thomas Allen Wells, David Edward Bulman, Mark Eugene Noe, Harold Ray Hansel, Christopher Charles Glynn
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Patent number: 6904757Abstract: A mounting assembly for a forward end of a liner in a combustor of a gas turbine engine including a dome and a cowl, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings formed in the forward end of the liner, an aft portion of the cowl, and a portion of the dome, with each pin member including a head portion at one end thereof. A nut is adjustably connected to an end of each pin member opposite the head portion. A bushing is located on each pin member at a position intermediate the head portion and the nut, wherein the openings in the liner forward end are sized to fit around the bushings.Type: GrantFiled: December 20, 2002Date of Patent: June 14, 2005Assignee: General Electric CompanyInventors: Krista Anne Mitchell, David Edward Bulman, Mark Eugene Noe, Harold Ray Hansel, Thomas Allen Wells, Christopher Charles Glynn, John David Bibler, Toby George Darkins, Jr., Joseph John Charneski, Craig Patrick Burns
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Patent number: 6895761Abstract: A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.Type: GrantFiled: December 20, 2002Date of Patent: May 24, 2005Assignee: General Electric CompanyInventors: Krista Anne Mitchell, David Edward Bulman, Mark Eugene Noe, Harold Ray Hansel, Thomas Allen Wells, Christopher Charles Glynn, John David Bibler, Toby George Darkins, Jr., Joseph John Charneski, Craig Patrick Burns
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Patent number: 6895757Abstract: An assembly for providing a seal at an aft end of a combustor liner for a gas turbine engine including a longitudinal centerline axis extending therethrough. The sealing assembly includes a substantially annular first sealing member positioned between an aft portion of a support member and the liner aft end so as to seat on a designated surface portion of the liner aft end and a substantially annular second sealing member positioned between the support member aft portion and a turbine nozzle located downstream of the liner aft end so as to seat on a designated surface portion of the support member aft portion. Accordingly, the first sealing member is maintained in its seated position as the support member aft portion moves radially with respect to the liner aft end and the second sealing member is maintained in its seated position as the support member aft portion moves axially with respect to the turbine nozzle.Type: GrantFiled: February 10, 2003Date of Patent: May 24, 2005Assignee: General Electric CompanyInventors: Krista Anne Mitchell, David Edward Bulman, Mark Eugene Noe, Harold Ray Hansel, Christopher Charles Glynn, John David Bibler
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Patent number: 6775985Abstract: A support assembly for a gas turbine engine combustor including an inner liner and an inner casing spaced therefrom, wherein a longitudinal centerline axis extends through the gas turbine engine. The support assembly includes an annular inner support cone located adjacent an aft end of said inner liner, an annular nozzle support connected to the inner support cone, and a plurality of support members connected at a first end to a forward end of the inner liner and connected at a second end to the inner support cone.Type: GrantFiled: January 14, 2003Date of Patent: August 17, 2004Assignee: General Electric CompanyInventors: Krista Anne Mitchell, David Edward Bulman, Mark Eugene Noe, Harold Ray Hansel, Christopher Charles Glynn
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Publication number: 20040154303Abstract: An assembly for providing a seal at an aft end of a combustor liner for a gas turbine engine including a longitudinal centerline axis extending therethrough. The sealing assembly includes a substantially annular first sealing member positioned between an aft portion of a support member and the liner aft end so as to seat on a designated surface portion of the liner aft end and a substantially annular second sealing member positioned between the support member aft portion and a turbine nozzle located downstream of the liner aft end so as to seat on a designated surface portion of the support member aft portion. Accordingly, the first sealing member is maintained in its seated position as the support member aft portion moves radially with respect to the liner aft end and the second sealing member is maintained in its seated position as the support member aft portion moves axially with respect to the turbine nozzle.Type: ApplicationFiled: February 10, 2003Publication date: August 12, 2004Inventors: Krista Anne Mitchell, David Edward Bulman, Mark Eugene Noe, Harold Ray Hansel, Christopher Charles Glynn, John David Bibler
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Publication number: 20040134198Abstract: A support assembly for a gas turbine engine combustor including an inner liner and an inner casing spaced therefrom, wherein a longitudinal centerline axis extends through the gas turbine engine. The support assembly includes an annular inner support cone located adjacent an aft end of said inner liner, an annular nozzle support connected to the inner support cone, and a plurality of support members connected at a first end to a forward end of the inner liner and connected at a second end to the inner support cone.Type: ApplicationFiled: January 14, 2003Publication date: July 15, 2004Inventors: Krista Anne Mitchell, David Edward Bulman, Mark Eugene Noe, Harold Ray Hansel, Christopher Charles Glynn
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Publication number: 20040118122Abstract: A mounting assembly for a forward end of a liner in a combustor of a gas turbine engine including a dome and a cowl, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings formed in the forward end of the liner, an aft portion of the cowl, and a portion of the dome, with each pin member including a head portion at one end thereof. A nut is adjustably connected to an end of each pin member opposite the head portion. A bushing is located on each pin member at a position intermediate the head portion and the nut, wherein the openings in the liner forward end are sized to fit around the bushings.Type: ApplicationFiled: December 20, 2002Publication date: June 24, 2004Inventors: Krista Anne Mitchell, David Edward Bulman, Mark Eugene Noe, Harold Ray Hansel, Thomas Allen Wells, Christopher Charles Glynn, John David Bibler, Toby George Darkins, Joseph John Charneski, Craig Patrick Burns
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Publication number: 20040118127Abstract: A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.Type: ApplicationFiled: December 20, 2002Publication date: June 24, 2004Inventors: Krista Anne Mitchell, David Edward Bulman, Mark Eugene Noe, Harold Ray Hansel, Thomas Allen Wells, Christopher Charles Glynn, John David Bibler, Toby George Darkins, Joseph John Charneski, Craig Patrick Burns
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Patent number: 6397603Abstract: A combustor having liners made from ceramic matrix composite materials (CMC's) that are capable of withstanding higher temperatures than metallic liners. The ceramic matrix composite liners are used in conjunction with mating components that are manufactured from superalloy materials. To permit the use of a combustor having liners made from CMC materials in conjunction with metallic materials used for the mating forward cowls, and aft seals with attached seal retainer over the broad range of temperatures of a combustor, the combustor is designed to allow for the differential thermal expansion of the differing materials at their interfaces in a manner that does not introduce stresses into the liner as a result of thermal expansion and also balances the flow of cooling air as a result of the thermal expansion.Type: GrantFiled: May 5, 2000Date of Patent: June 4, 2002Assignee: The United States of America as represented by the Secretary of the Air ForceInventors: Wayne Garcia Edmondson, James Dale Steibel, Harold Ray Hansel