Patents by Inventor Alan J. Goetschius
Alan J. Goetschius 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: 10711642Abstract: A lubrication system for a gas turbine engine is provided. The lubrication system includes a supply source of a fluid lubricant, a main supply pump, and a boost pump system. The main supply pump has an MSP fluid flow inlet port and an MSP fluid flow exit port. The main supply pump is configured to receive a source fluid lubricant flow at a first pressure, and configured to produce a supply fluid flow at a second pressure. The second pressure is greater than the first pressure. The boost pump system has a boost pump having a BP fluid flow inlet port, and a BP fluid flow exit port. The boost pump system is configured so that the boost pump selectively receives at least a portion of the supply fluid flow from the main supply pump at the BP fluid flow inlet port, and the boost pump is configured to produce a boost supply fluid flow at a third pressure at the BP fluid flow exit port, wherein the third pressure is greater than the second pressure.Type: GrantFiled: March 31, 2017Date of Patent: July 14, 2020Assignee: Raytheon Technologies CorporationInventors: Francis Parnin, Alan J. Goetschius, Thomas B. Avis
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Patent number: 10094420Abstract: A squeeze film damper includes a static member and a whirling member positioned adjacent to the static member. A gap is formed between the static member and the whirling member. A pressurized oil reservoir is formed in the gap between the static member and the whirling member. A first low pressure oil reservoir is formed in a first cavity in the whirling member, wherein the first low pressure oil reservoir is positioned on a first end of the pressurized oil reservoir. A second low pressure oil reservoir is formed in a second cavity in the whirling member, wherein the second low pressure oil reservoir is positioned on a second end of the pressurized oil reservoir. A first primary seal is positioned between the first end of the pressurized oil reservoir and the first low pressure oil reservoir, and a second primary seal is positioned between the second end of the pressurized oil reservoir and the second low pressure oil reservoir.Type: GrantFiled: March 27, 2017Date of Patent: October 9, 2018Assignee: United Technologies CorporationInventors: David B. Hudson, Gregory M. Savela, Robert J. Morris, Christopher J. Zuck, Daniel L. Gysling, Alan J. Goetschius
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Publication number: 20180283211Abstract: A lubrication system for a gas turbine engine is provided. The lubrication system includes a supply source of a fluid lubricant, a main supply pump, and a boost pump system. The main supply pump has an MSP fluid flow inlet port and an MSP fluid flow exit port. The main supply pump is configured to receive a source fluid lubricant flow at a first pressure, and configured to produce a supply fluid flow at a second pressure. The second pressure is greater than the first pressure. The boost pump system has a boost pump having a BP fluid flow inlet port, and a BP fluid flow exit port. The boost pump system is configured so that the boost pump selectively receives at least a portion of the supply fluid flow from the main supply pump at the BP fluid flow inlet port, and the boost pump is configured to produce a boost supply fluid flow at a third pressure at the BP fluid flow exit port, wherein the third pressure is greater than the second pressure.Type: ApplicationFiled: March 31, 2017Publication date: October 4, 2018Inventors: Francis Parnin, Alan J. Goetschius, Thomas B. Avis
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Publication number: 20180274588Abstract: A squeeze film damper includes a static member and a whirling member positioned adjacent to the static member. A gap is formed between the static member and the whirling member. A pressurized oil reservoir is formed in the gap between the static member and the whirling member. A first low pressure oil reservoir is formed in a first cavity in the whirling member, wherein the first low pressure oil reservoir is positioned on a first end of the pressurized oil reservoir. A second low pressure oil reservoir is formed in a second cavity in the whirling member, wherein the second low pressure oil reservoir is positioned on a second end of the pressurized oil reservoir. A first primary seal is positioned between the first end of the pressurized oil reservoir and the first low pressure oil reservoir, and a second primary seal is positioned between the second end of the pressurized oil reservoir and the second low pressure oil reservoir.Type: ApplicationFiled: March 27, 2017Publication date: September 27, 2018Inventors: David B. Hudson, Gregory M. Savela, Robert J. Morris, Christopher J. Zuck, Daniel L. Gysling, Alan J. Goetschius
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Patent number: 9995177Abstract: A pump system for a gas turbine engine has at least one pump. At least one valve has an outlet and at least one inlet is fluidly connected to the at least one pump. A geared architecture is positioned within a bearing compartment. The geared architecture is configured to receive lubricating fluid from the outlet of the at least one valve, a self-cleaning filter is positioned downstream of the at least one valve and upstream of the geared architecture. A gas turbine engine and a method are also disclosed.Type: GrantFiled: February 19, 2014Date of Patent: June 12, 2018Assignee: United Technologies CorporationInventors: William G. Sheridan, Alan J. Goetschius
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Publication number: 20160032772Abstract: A pump system for a gas turbine engine has at least one pump. At least one valve has an outlet and at least one inlet is fluidly connected to the at least one pump. A geared architecture is positioned within a bearing compartment. The geared architecture is configured to receive lubricating fluid from the outlet of the at least one valve, a self-cleaning filter is positioned downstream of the at least one valve and upstream of the geared architecture. A gas turbine engine and a method are also disclosed.Type: ApplicationFiled: February 19, 2014Publication date: February 4, 2016Inventors: William G. Sheridan, Alan J. Goetschius
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Patent number: 8015829Abstract: A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a number of panels. Each panel has interior and exterior surfaces and a perimeter having leading and trailing edges and first and second lateral edges. A number of cooling passageways have inlets on the panel exterior surface and outlets on the panel interior surface. The shell has a plurality of holes for directing air to a space between the shell and heat shield and adapted for preferentially directing said air toward leading edge portions of first stage vanes of a turbine section.Type: GrantFiled: February 26, 2008Date of Patent: September 13, 2011Assignee: United Technologies CorporationInventors: Joseph D. Coughlan, III, Monica Pacheco-Tougas, James B. Hoke, Alan J. Goetschius
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Publication number: 20090293488Abstract: A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a number of panels. Each panel has interior and exterior surfaces and a perimeter having leading and trailing edges and first and second lateral edges. A number of cooling passageways have inlets on the panel exterior surface and outlets on the panel interior surface. The shell has a plurality of holes for directing air to a space between the shell and heat shield and adapted for preferentially directing said air toward leading edge portions of first stage vanes of a turbine section.Type: ApplicationFiled: February 26, 2008Publication date: December 3, 2009Applicant: United Technologies CorporationInventors: Joseph D. Coughlan, III, Monica Pacheco-Tougas, James B. Hoke, Alan J. Goetschius
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Patent number: 7363763Abstract: A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a number of panels. Each panel has interior and exterior surfaces and a perimeter having leading and trailing edges and first and second lateral edges. A number of cooling passageways have inlets on the panel exterior surface and outlets on the panel interior surface. A rail protrudes from the exterior surface and is recessed from the leading edge along a majority of the leading edge.Type: GrantFiled: October 23, 2003Date of Patent: April 29, 2008Assignee: United Technologies CorporationInventors: Joseph D. Coughlan, III, Monica Pacheco-Tougas, James B. Hoke, Alan J. Goetschius
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Patent number: 7093439Abstract: The present invention relates to heat shield panels or liners to be used in combustors for gas turbine engines. The heat shield panels each comprise a hot side and a cold side and at least one isolated cooling chamber on the cold side. Each cooling chamber has a plurality of cooling film holes for allowing a coolant, such as air, to flow from the cold side to the hot side. A combustor having an arrangement of heat shield panels or liners is also described.Type: GrantFiled: May 16, 2002Date of Patent: August 22, 2006Assignee: United Technologies CorporationInventors: Monica Pacheco-Tougas, Joseph D. Coughlan, III, James B. Hoke, Alan J. Goetschius
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Publication number: 20030213250Abstract: The present invention relates to heat shield panels or liners to be used in combustors for gas turbine engines. The heat shield panels each comprise a hot side and a cold side and at least one isolated cooling chamber on the cold side. Each cooling chamber has a plurality of cooling film holes for allowing a coolant, such as air, to flow from the cold side to the hot side. A combustor having an arrangement of heat shield panels or liners is also described.Type: ApplicationFiled: May 16, 2002Publication date: November 20, 2003Inventors: Monica Pacheco-Tougas, Joseph D. Coughlan, James B. Hoke, Alan J. Goetschius
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Patent number: 6134780Abstract: A swirler 50 for a gas turbine engine combustor 10 has an outer wall 54, groupings 52 of vanes 42 attached to the outer wall, a centerbody 60 mechanically decoupled from the outer wall via the groupings of vanes so that the swirler can accommodate differential rates of thermal growth between the outer wall and the inner centerbody and vanes. Alternatively, the centerbody may be attached to one of the groupings of vanes to keep the centerbody from vibrating.Type: GrantFiled: September 9, 1999Date of Patent: October 24, 2000Assignee: United Technologies CorporationInventors: Joseph D. Coughlan, Alan J. Goetschius
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Patent number: 6098407Abstract: A premixing, tangential entry fuel injector (10) for a gas turbine engine features a secondary fuel-air injection insert (40) positively secured to a centerbody shell (38) by a braze joint (98). A secondary fuel supply tube (42), positively secured to both a centerbody base (36) and to the insert (40), is curved in at least two dimensions. In an exemplary embodiment, the tube is coiled into a spiral shape covering a single 360.degree. cycle. During engine operation, the centerbody expands axially in response to elevated temperatures in the engine's interior, causing the insert (40) to be displaced away from the base (36). The curvature of the tube allows the tube to flex slightly to accommodate the displacement. Ideally the curvature of the tube is such that the tube's natural frequency is well above the maximum vibratory frequency that the tube will experience during engine operation.Type: GrantFiled: June 8, 1998Date of Patent: August 8, 2000Assignee: United Technologies CorporationInventors: John J. Korzendorfer, Jeffrey D. Melman, Alan J. Goetschius
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Patent number: 5996352Abstract: A swirler 50 for a gas turbine engine combustor 10 has an outer wall 54, groupings 52 of vanes 42 attached to the outer wall, a centerbody 60 mechanically decoupled from the outer wall via the groupings of vanes so that the swirler can accommodate differential rates of thermal growth between the outer wall and the inner centerbody and vanes. Alternatively, the centerbody may be attached to one of the groupings of vanes to keep the centerbody from vibrating.Type: GrantFiled: December 22, 1997Date of Patent: December 7, 1999Assignee: United Technologies CorporationInventors: Joseph D. Coughlan, Alan J. Goetschius