Patents by Inventor Gilbert Farmer
Gilbert Farmer 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: 6655147Abstract: An annular one-piece liner for a combustor of a gas turbine engine, including a first end adjacent to an upstream end of the combustor, a second end adjacent to a downstream end of the combustor, and a plurality of corrugations between the first and second ends, each corrugation having an amplitude and a wavelength between an adjacent corrugation, wherein the amplitude of the corrugations and/or the wavelength between adjacent corrugations is variable from the first end to the second end.Type: GrantFiled: April 10, 2002Date of Patent: December 2, 2003Assignee: General Electric CompanyInventors: Gilbert Farmer, Shaun M. Devane, John L. Vandike
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Patent number: 6651437Abstract: A combustor liner is provided having first and second annular bands which define an overlapping circumferential joint area, wherein a weld is disposed in the joint area encompassing substantially all of the axial length of the joint area. A method for producing such a combustor liner is also provided.Type: GrantFiled: December 21, 2001Date of Patent: November 25, 2003Assignee: General Electric CompanyInventors: Gilbert Farmer, James A. Groeschen, Ronald D. Redden, Shaun M. DeVane
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Publication number: 20030192320Abstract: An annular one-piece liner for a combustor of a gas turbine engine, including a first end adjacent to an upstream end of the combustor, a second end adjacent to a downstream end of the combustor, and a plurality of corrugations between the first and second ends, each corrugation having an amplitude and a wavelength between an adjacent corrugation, wherein the amplitude of the corrugations and/or the wavelength between adjacent corrugations is variable from the first end to the second end.Type: ApplicationFiled: April 10, 2002Publication date: October 16, 2003Inventors: Gilbert Farmer, Shaun M. Devane, John L. Vandike
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Patent number: 6629415Abstract: A method for fabricating a three-dimensional turbine engine combustor liner model includes coupling at least a first member to a second member to form an assembly that has an inner surface. The assembly inner surface simulates an inner surface of the aircraft engine combustor liner. The first member is at least one of a pre-formed conical member and a pre-formed cylindrical member, and the second portion is at least one of a pre-formed conical member and a pre-formed cylindrical member. The method also includes coupling the assembly to a baseplate, and coupling a plurality of templates to the assembly.Type: GrantFiled: October 27, 2001Date of Patent: October 7, 2003Assignee: General Electric Co.Inventors: Edward Lee Howard, Gilbert Farmer, James Hollice Poynter, Ronald Lee Sheranko, Gregory Thomas Lucas
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Patent number: 6620457Abstract: A method of applying a thermal barrier coating system to a metal piece having cooling holes angled in a first direction and cooling holes angled in a second direction. The method includes spraying a bond coat on a first surface of the piece at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the bond coat from entirely filling any of the holes. A thermal barrier coating is sprayed on the bond coat at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the thermal barrier coating from entirely filling any of the holes. The method also includes spraying a high pressure fluid jet from a nozzle assembly through each hole generally parallel to the respective cooling hole.Type: GrantFiled: July 13, 2001Date of Patent: September 16, 2003Assignee: General Electric CompanyInventors: Gilbert Farmer, Thomas John Tomlinson, Raymond William Heidorn, Jeffrey Arnold Fehrenbach, William Lee Imhoff, Myron Edward Rutherford
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Publication number: 20030167772Abstract: A multi-hole cooled combustor liner is provided which reduces hot streaks and associated material distress in the liner. Areas of increased cooling hole density are disposed upstream of the primary dilution holes and in circumferential alignment with fuel cup centers. Additional cooling holes are provided in between primary dilution holes are arranged in alternating pairs of circumferentially angled holes so as to provide a converging cooling air flow in the downstream direction.Type: ApplicationFiled: December 17, 2002Publication date: September 11, 2003Applicant: General Electric CompanyInventors: Gilbert Farmer, Daniel Dale Brown, Myron Edward Rutherford
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Publication number: 20030165621Abstract: A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is particularly effective in removing a TBC material deposited in a cooling hole of a component as a result of depositing a coating of the TBC material on a surface of the component, in which the deposit is removed from the cooling hole without damaging the cooling hole or the TBC coating surrounding the cooling hole on the coated surface of the component. A preferred feature is that the cooling hole, including the entrance to the hole at a surface of the component opposite the coated surface and the coating surrounding the exit of the hole at the coated surface, exhibits improved surface characteristics that increase the discharge coefficient of the cooling hole, as evidenced by an increase in the effective area of the cooling hole.Type: ApplicationFiled: March 1, 2002Publication date: September 4, 2003Inventors: Gilbert Farmer, Jeffrey Arnold Fehrenbach
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Publication number: 20030159445Abstract: A cowl for use with a combustor of a gas turbine engine, the cowl includes a main body with an annular corrugation. A combustor of a gas turbine engine, the combustor includes: a hollow body defining a combustion chamber, the hollow body having a liner; an outer cowl having an annular corrugation, the cowl connecting to the liner; and an inner cowl connecting to the liner. A method of configuring a cowl for a gas turbine engine combustor, the method includes forming an annular corrugation in a main body of the cowl.Type: ApplicationFiled: February 27, 2002Publication date: August 28, 2003Inventors: Gilbert Farmer, Ronald D. Redden, Balena B. Shorter, James A. Groeschen, Mehmet M. Dede, Daniel L. Durstock
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Publication number: 20030152713Abstract: A method of stripping coating from a portion of a coated surface of a component. The method includes fastening a mask sheet to the component over a region adjacent the portion of the coated surface. The mask sheet has a contour generally corresponding to a contour of the surface of the component. A high pressure fluid jet is sprayed from a spray head toward the portion of the coated surface after the mask sheet is fastened to the component to strip the coating from the portion of the surface. After the coating is stripped from the portion of the surface, the mask sheet is removed from the component.Type: ApplicationFiled: February 19, 2003Publication date: August 14, 2003Applicant: General Eletric CompanyInventors: Gilbert Farmer, Jeffrey Arnold Fehrenbach, William Lee Imhoff, David Allen Kastrup
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Patent number: 6592287Abstract: An assembly of parts is prepared by providing a female part having a recess and a male part having an inserted surface received within the recess. A relief pattern such as knurling is formed on the inserted surface. The inserted surface of the male part is inserted into the recess of the female part with a contacting-channeled fit between the inserted surface and the recess surface, so that the knurl serves to align the inserted surface within the recess. The inserted surface of the male part is brazed or otherwise joined to the recess of the female part.Type: GrantFiled: September 21, 1999Date of Patent: July 15, 2003Assignee: General Electric CompanyInventors: Michael P. Hagle, Gilbert Farmer
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Publication number: 20030115886Abstract: A combustor liner is provided having first and second annular bands which define an overlapping circumferential joint area, wherein a weld is disposed in the joint area encompassing substantially all of the axial length of the joint area. A method for producing such a combustor liner is also provided.Type: ApplicationFiled: December 21, 2001Publication date: June 26, 2003Applicant: General Electric CompanyInventors: Gilbert Farmer, James A. Groeschen, Ronald D. Redden, Shaun M. DeVane
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Patent number: 6568079Abstract: A replacement method facilitates replacing of a portion of a combustor liner within a gas turbine engine combustor in a cost-effective and reliable manner. The combustor includes a combustion zone that is defined by an inner and an outer liner. The inner and outer liners each include a series of panels and a plurality of nuggets formed by adjacent panels. The method includes the steps of cutting between an outer surface and an inner surface of at least one liner panel, removing at least one panel that is adjacent the area of the liner that was cut, and installing a replacement panel into the combustor for each panel that was removed from the combustor.Type: GrantFiled: June 11, 2001Date of Patent: May 27, 2003Assignee: General Electric CompanyInventors: Gilbert Farmer, David Bruce Patterson, Steven Allen Stiverson, James Michael Caldwell, Edward John Emilianowicz, Jeffrey Michael Martini
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Patent number: 6561872Abstract: A method of stripping coating from a portion of a coated surface of a component. The method includes fastening a mask sheet to the component over a region adjacent the portion of the coated surface. The mask sheet has a contour generally corresponding to a contour of the surface of the component. A high pressure fluid jet is sprayed from a spray head toward the portion of the coated surface after the mask sheet is fastened to the component to strip the coating from the portion of the surface. After the coating is stripped from the portion of the surface, the mask sheet is removed from the component.Type: GrantFiled: June 11, 2001Date of Patent: May 13, 2003Assignee: General Electric CompanyInventors: Gilbert Farmer, Jeffrey Arnold Fehrenbach, William Lee Imhoff, David Allen Kastrup
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Patent number: 6557350Abstract: A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.Type: GrantFiled: May 17, 2001Date of Patent: May 6, 2003Assignee: General Electric CompanyInventors: Gilbert Farmer, Ella Christine Kutter, Steven Clayton Vise, John Robert Staker, Marwan Al-Roub, Tariq Kay Harris
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Publication number: 20030079530Abstract: A method for fabricating a three-dimensional turbine engine combustor liner model includes coupling at least a first member to a second member to form an assembly that has an inner surface. The assembly inner surface simulates an inner surface of the aircraft engine combustor liner. The first member is at least one of a pre-formed conical member and a pre-formed cylindrical member, and the second portion is at least one of a pre-formed conical member and a pre-formed cylindrical member. The method also includes coupling the assembly to a baseplate, and coupling a plurality of templates to the assembly.Type: ApplicationFiled: October 27, 2001Publication date: May 1, 2003Inventors: Edward Lee Howard, Gilbert Farmer, James Hollice Poynter, Ronald Lee Sheranko, Gregory Thomas Lucas
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Patent number: 6553767Abstract: An annular gas turbine engine combustor liner has a single piece annular shell circumscribed about a first axis of revolution. The shell has a hot side and a cold side, an annular dilution hole section, and a plurality of asymmetrical cylindrical dilution holes extending through the section. Pockets are circumferentially interdigitated between the dilution holes and extend into the shell from the cold side such that the pockets form dilution hole bosses between the pockets through which the dilution holes extend. Each of the dilution holes is circumscribed about a second axis of revolution which is not parallel to the first axis of revolution. The liner may further include forward and aft annular cooling nuggets located forward and aft of the dilution hole section and having annular film cooling slots which are open in the axially aftwardly direction.Type: GrantFiled: June 11, 2001Date of Patent: April 29, 2003Assignee: General Electric CompanyInventors: Gilbert Farmer, Daniel D. Brown, Myron E. Rutherford, Steven C. Vise, Jeffrey M. Martini
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Publication number: 20030027093Abstract: A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.Type: ApplicationFiled: July 31, 2001Publication date: February 6, 2003Inventors: Ella Christine Kutter, Marwan Al-Roub, Thomas Anthony Leen, Daniel Dale Brown, Craig Douglas Young, Gilbert Farmer, Mohammad Ehteshami
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Patent number: 6513331Abstract: A multi-hole cooled combustor liner is provided which reduces hot streaks and associated material distress in the liner. Areas of increased cooling hole density are disposed upstream of the primary dilution holes and in circumferential alignment with fuel cup centers. Additional cooling holes are provided in between primary dilution holes are arranged in alternating pairs of circumferentially angled holes so as to provide a converging cooling air flow in the downstream direction.Type: GrantFiled: August 21, 2001Date of Patent: February 4, 2003Assignee: General Electric CompanyInventors: Daniel Dale Brown, Gilbert Farmer, Myron Edward Rutherford
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Publication number: 20030010035Abstract: A method of applying a thermal barrier coating system to a metal piece having cooling holes angled in a first direction and cooling holes angled in a second direction. The method includes spraying a bond coat on a first surface of the piece at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the bond coat from entirely filling any of the holes. A thermal barrier coating is sprayed on the bond coat at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the thermal barrier coating from entirely filling any of the holes. The method also includes spraying a high pressure fluid jet from a nozzle assembly through each hole generally parallel to the respective cooling hole.Type: ApplicationFiled: July 13, 2001Publication date: January 16, 2003Inventors: Gilbert Farmer, Thomas John Tomlinson, Raymond William Heidorn, Jeffrey Arnold Fehrenbach, William Lee Imhoff, Myron Edward Rutherford
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Publication number: 20020184762Abstract: A replacement method facilitates replacing of a portion of a combustor liner within a gas turbine engine combustor in a cost-effective and reliable manner. The combustor includes a combustion zone that is defined by an inner and an outer liner. The inner and outer liners each include a series of panels and a plurality of nuggets formed by adjacent panels. The method includes the steps of cutting between an outer surface and an inner surface of at least one liner panel, removing at least one panel that is adjacent the area of the liner that was cut, and installing a replacement panel into the combustor for each panel that was removed from the combustor.Type: ApplicationFiled: June 11, 2001Publication date: December 12, 2002Inventors: Gilbert Farmer, David Bruce Patterson, Steven Allen Stiverson, James Michael Caldwell, Edward John Emilianowicz, Jeffrey Michael Martini