Patents by Inventor Barry Lynn Allmon
Barry Lynn Allmon 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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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: 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: 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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Patent number: 7384199Abstract: A bearing assembly for a gas turbine engine rotor includes, in an exemplary, an inner race, an outer race assembly, and a rolling element. The outer race assembly includes a body, a plurality of first springs attached to the body, and a plurality of second springs. Each first spring is radially aligned with a corresponding second spring forming a spring pair. The outer race assembly also includes a plurality of connecting members. Each connecting member extends between and connects a first end of the first spring and a first end of the second spring of said spring pair. The outer race assembly further includes a flange with each second spring attached to the flange.Type: GrantFiled: August 27, 2004Date of Patent: June 10, 2008Assignee: General Electric CompanyInventors: Barry Lynn Allmon, Richard Leon Riffle, Jerry Lynn Cabe, Duane Howard Anstead
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Patent number: 7334982Abstract: An apparatus for scavenging lubricating oil comprises an integrated slinger/runner rotatable with the turbine engine rotor discourages oil seepage out of an oil sump of a forward bearing for a gas turbine engine during all operating conditions of the gas turbine engine from idle to take-off speeds and during static non-operation. The apparatus includes a runner comprising an axially forward section and a frusto-conical aft section, and a slinger joined coaxially integrally to the aft frusto-conical aft section. The apparatus includes a means for blocking flow of oil from the frusto-conical aft section toward the axially forward section.Type: GrantFiled: May 6, 2005Date of Patent: February 26, 2008Assignee: General Electric CompanyInventors: Anant Pal Singh, Stephen Anthony Wilton, Duane Howard Anstead, Barry Lynn Allmon
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Patent number: 7260892Abstract: A method facilitates the assembly of a stator assembly for a turbine engine. The method includes providing a cantilevered shell including a first end and a second end, and coupling a second member within the turbine engine. The method also includes coupling the shell to a frame such that the shell extends circumferentially around at least a portion of the second member such that a non-uniform circumferential radial gap is defined radially between the second member and the shell using methods other than directing machining of an inner surface of the shell, and wherein the non-uniform circumferential radial clearance gap becomes substantially uniform during operation of the engine.Type: GrantFiled: December 24, 2003Date of Patent: August 28, 2007Assignee: General Electric CompanyInventors: Jan Christopher Schilling, Daniel Edward Mollmann, Barry Lynn Allmon, Anthony Durchholz
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Patent number: 6783319Abstract: A bearing assembly for a gas turbine engine rotor includes a paired race, a bearing, a mounting joint, and a plurality of mechanical fuses. The paired race includes an outer race and an inner race. The bearing is between the inner and outer races, and is configured to support the rotor on a support frame. The mounting joint includes a joint inner race and a joint outer race. At least one of the joint inner race and the joint outer race includes a spherical surface. The mounting joint is configured to reduce dynamic loads to the gas turbine engine structure and static bending to the rotor. The plurality of mechanical fuses extend through at least one of the joint inner race and the joint outer race.Type: GrantFiled: September 7, 2001Date of Patent: August 31, 2004Assignee: General Electric Co.Inventors: Thomas Matthew Doerflein, Stephen Anthony Wilton, Barry Lynn Allmon
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Publication number: 20030210979Abstract: A bearing assembly for a gas turbine engine rotor includes a paired race, a bearing, a mounting joint, and a plurality of mechanical fuses. The paired race includes an outer race and an inner race. The bearing is between the inner and outer races, and is configured to support the rotor on a support frame. The mounting joint includes a joint inner race and a joint outer race. At least one of the joint inner race and the joint outer race includes a spherical surface. The mounting joint is configured to reduce dynamic loads to the gas turbine engine structure and static bending to the rotor. The plurality of mechanical fuses extend through at least one of the joint inner race and the joint outer race.Type: ApplicationFiled: September 7, 2001Publication date: November 13, 2003Inventors: Thomas Matthew Doerflein, Stephen Anthony Wilton, Barry Lynn Allmon
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Patent number: 6540483Abstract: A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner race, and an outer race, said inner and outer races within said bearing bore. The bearing centering apparatus sub-assembly includes a plurality of first springs and a plurality of second springs. The retainer is coupled to the bearing housing and is configured to maintain an axial position of the bearing outer race with respect to the support structure.Type: GrantFiled: August 27, 2001Date of Patent: April 1, 2003Assignee: General Electric CompanyInventors: Barry Lynn Allmon, Morris Green Penn
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Publication number: 20030039538Abstract: A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner race, and an outer race, said inner and outer races within said bearing bore. The bearing centering apparatus sub-assembly includes a plurality of first springs and a plurality of second springs. The retainer is coupled to the bearing housing and is configured to maintain an axial position of the bearing outer race with respect to the support structure.Type: ApplicationFiled: August 27, 2001Publication date: February 27, 2003Inventors: Barry Lynn Allmon, Morris Green Penn
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Patent number: 6491497Abstract: A rotor assembly for a gas turbine engine includes a bearing assembly that reduces dynamic loads to a support frame and static bending to the rotor assembly during periods of rotor unbalance. The rotor assembly includes a rotor shaft coupled to a fan and supported longitudinally with a plurality of bearing assemblies on a support frame. A number two bearing assembly includes a paired race, a rolling element, and a mounting race. The mounting race includes a spherical face and is secured to the bearing assembly with a retainer that plastically fails at a pre-determined moment load.Type: GrantFiled: September 22, 2000Date of Patent: December 10, 2002Assignee: General Electric CompanyInventors: Barry Lynn Allmon, Christopher Charles Glynn, Kenneth Lee Fisher, Daniel Edward Mollmann, Bala Corattiyil, Randy Marinus Vondrell, Morris Green Penn, Michael Joseph Gambone, Jan Christopher Schilling
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Publication number: 20020127102Abstract: A rotor assembly for a gas turbine engine including a bearing centering sub-assembly that facilitates reduces an effect of radial forces transmitted to a bearing assembly is described. The bearing assembly supports a rotor shaft with a rolling element positioned radially inward from an outer race. The bearing centering sub-assembly is coupled to the outer race and includes a plurality of first springs and a plurality of second springs extending circumferentially in rows. Each first springs is coupled between a second spring and the outer race such that each first spring is radially aligned with respect to each second spring.Type: ApplicationFiled: January 26, 2001Publication date: September 12, 2002Inventors: Bala Corattiyil, Barry Lynn Allmon
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Patent number: 6443698Abstract: A rotor assembly for a gas turbine engine including a bearing centering sub-assembly that facilitates reduces an effect of radial forces transmitted to a bearing assembly is described. The bearing assembly supports a rotor shaft with a rolling element positioned radially inward from an outer race. The bearing centering sub-assembly is coupled to the outer race and includes a plurality of first springs and a plurality of second springs extending circumferentially in rows. Each first springs is coupled between a second spring and the outer race such that each first spring is radially aligned with respect to each second spring.Type: GrantFiled: January 26, 2001Date of Patent: September 3, 2002Assignee: General Electric CompanyInventors: Bala Corattiyil, Barry Lynn Allmon