Patents by Inventor Robert S. Thompson, Jr.
Robert S. Thompson, Jr. 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: 9464527Abstract: Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with corresponding aft hollow interior portions of each blade. A radially-extending central rib within each blade partitions the hollow interior thereof into aft and forward hollow interior portions that are in fluid communication through an associated opening in the central rib and through a radially-extending gap between the central rib and the interior surface of the blade. A blade outlet duct provides for fluid communication between the forward hollow interior portion and a forward cavity of the bladed rotor, and a rotor outlet duct provides for discharging the fuel from a radially-inboard portion of the forward cavity.Type: GrantFiled: March 14, 2014Date of Patent: October 11, 2016Assignee: Williams International Co., LLCInventors: Robert S. Thompson, Jr., Gregg G. Williams, David W. Jarrell, Curtis E. Lynch, Mark E. Suchezky
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Patent number: 9157377Abstract: A control schedule incorporating a relationship between corrected torque and inlet pressure is selected or determined responsive to a power-level command representative of a level of power to be transmitted to a controllable load by a single-spool turboshaft engine. At least a substantial portion of the control schedule provides for a flat-rated power level by the single-spool turboshaft engine substantially independent of associated inlet air pressure and inlet air temperature, and for at least one selectable mode of operation, the control schedule provides for minimizing or nearly minimizing a measure of fuel consumption, and for at least one other selectable mode of operation, the control schedule provides for operation at a substantially fixed level of rotational speed.Type: GrantFiled: April 3, 2015Date of Patent: October 13, 2015Assignee: WILLIAMS INTERNATIONAL CO., L.L.C.Inventors: Ray D. Lickfold, Gregg G. Williams, Robert S. Thompson, Jr.
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Publication number: 20150211422Abstract: A control schedule incorporating a relationship between corrected torque and inlet pressure is selected or determined responsive to a power-level command representative of a level of power to be transmitted to a controllable load by a single-spool turboshaft engine. At least a substantial portion of the control schedule provides for a flat-rated power level by the single-spool turboshaft engine substantially independent of associated inlet air pressure and inlet air temperature, and for at least one selectable mode of operation, the control schedule provides for minimizing or nearly minimizing a measure of fuel consumption, and for at least one other selectable mode of operation, the control schedule provides for operation at a substantially fixed level of rotational speed.Type: ApplicationFiled: April 3, 2015Publication date: July 30, 2015Inventors: Ray D. LICKFOLD, Gregg WILLIAMS, Robert S. THOMPSON, JR.
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Patent number: 9008943Abstract: One of a controllable load and a fuel flow to a single-spool turboshaft engine is controlled so that a rotational speed of a single-spool turboshaft engine is substantially regulated to a level corresponding to a corrected rotational speed command, and the other of the fuel flow and the controllable load is controlled so that a torque transmitted from the single-spool turboshaft engine to the controllable load is substantially regulated to a level corresponding to a corrected torque command. Under at least one operating condition, the corrected rotational speed command is determined so as to minimize or nearly minimize a measure of fuel consumption by the single-spool turboshaft engine when operated so that the torque transmitted to the controllable load corresponds to the corrected torque command.Type: GrantFiled: August 1, 2013Date of Patent: April 14, 2015Assignee: Williams International Co., L.L.C.Inventors: Ray D. Lickfold, Gregg Williams, Robert S. Thompson, Jr.
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Patent number: 8820092Abstract: Fuel (12) is supplied to a rotatable portion (118) of a gas turbine engine (10) comprising a rotor (24) and at least one blade (26, 26.1) operatively coupled thereto, so as to provide for cooling at least one of the rotor (24) or the at least one blade (26, 26.1) by transforming the fuel (12) to a vapor or gaseous state. The fuel (12) is discharged in a vapor or gaseous state from the rotatable portion (118) directly into a combustion chamber (16) of the gas turbine engine (10).Type: GrantFiled: April 9, 2009Date of Patent: September 2, 2014Assignee: Williams International Co., L.L.C.Inventors: Robert S. Thompson, Jr., Gregg Williams, David W. Jarrell, Curtis E. Lynch, Mark E. Suchezky
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Publication number: 20140193274Abstract: Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with corresponding aft hollow interior portions of each blade. A radially-extending central rib within each blade partitions the hollow interior thereof into aft and forward hollow interior portions that are in fluid communication through an associated opening in the central rib and through a radially-extending gap between the central rib and the interior surface of the blade. A blade outlet duct provides for fluid communication between the forward hollow interior portion and a forward cavity of the bladed rotor, and a rotor outlet duct provides for discharging the fuel from a radially-inboard portion of the forward cavity.Type: ApplicationFiled: March 14, 2014Publication date: July 10, 2014Applicant: WILLIAMS INTERNATIONAL CO., L.L.C.Inventors: Robert S. THOMPSON, JR., Gregg WILLIAMS, David W. JARRELL, Curtis E. LYNCH, Mark E. SUCHEZKY
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Publication number: 20140039775Abstract: One of a controllable load and a fuel flow to a single-spool turboshaft engine is controlled so that a rotational speed of a single-spool turboshaft engine is substantially regulated to a level corresponding to a corrected rotational speed command, and the other of the fuel flow and the controllable load is controlled so that a torque transmitted from the single-spool turboshaft engine to the controllable load is substantially regulated to a level corresponding to a corrected torque command. Under at least one operating condition, the corrected rotational speed command is determined so as to minimize or nearly minimize a measure of fuel consumption by the single-spool turboshaft engine when operated so that the torque transmitted to the controllable load corresponds to the corrected torque command.Type: ApplicationFiled: August 1, 2013Publication date: February 6, 2014Applicant: WILLIAMS INTERNATIONAL CO., L.L.C.Inventors: Ray D. LICKFOLD, Gregg WILLIAMS, Robert S. THOMPSON, JR.
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Patent number: 8566000Abstract: A controller receives a power-level command representative of a level of power to be transmitted by a single-spool turboshaft engine to a controllable load. A torque command determined responsive to a measure of inlet pressure, from a control schedule responsive to the power-level command, is representative of a level of torque to be transmitted by an element to drive the controllable load. Under some operating conditions, a rotational speed command provides for at least nearly minimizing a measure of associated fuel consumption when the transmitted torque is regulated to the level corresponding to the torque command by controlling one of the controllable load and a fuel flow to the engine, and the other of the controllable load and the fuel flow to the engine is controlled so as to regulate an associated rotational speed to a level corresponding to the rotational speed command.Type: GrantFiled: February 23, 2011Date of Patent: October 22, 2013Assignee: Williams International Co., L.L.C.Inventors: Ray D. Lickfold, Gregg Williams, Robert S. Thompson, Jr.
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Patent number: 8545106Abstract: Lubrication fluid is discharged through an axial gap between a outer bearing race and a bearing housing from a cavity bounded in part by a forward surface of the outer bearing race that is axially slideable within the bearing housing so as to provide for changing the axial gap. The pressure in the cavity is automatically controlled responsive to an axial force on outer bearing race by an axial position of the outer bearing race that determines a size of the axial gap, so as to provide for increasing the pressure responsive to increasing axial force over at least a portion of an operating range. The lubrication fluid in the axial gap provides for isolating axial vibrations of the outer bearing race relative to the bearing housing.Type: GrantFiled: July 8, 2010Date of Patent: October 1, 2013Assignee: Williams International Co., L.L.C.Inventors: Craig R. Miller, Robert S. Thompson, Jr.
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Patent number: 8459038Abstract: A load applied to a low pressure spool of a two-spool turboshaft engine is controlled responsive to inlet pressure and temperature so as to regulate a relationship between the rotational speeds of the low and high pressure spools of the two-spool turboshaft engine so as to provide for operating the low pressure compressor attached to the low pressure spool with sufficient surge margin.Type: GrantFiled: February 9, 2012Date of Patent: June 11, 2013Assignee: Williams International Co., L.L.C.Inventors: Ray D. Lickfold, Gregg Williams, Robert S. Thompson, Jr.
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Patent number: 8057163Abstract: Fuel (12) supplied to a rotary fluid trap (42) is centrifugally accelerated within a first cavity (46) adjacent a first side (48) of a rotor (24), and is then directed though a plurality of first passages (66) extending through the rotor (24) between and proximate to the blades (26), and shaped so as to at least partially conform to the shape of the blades (26). Second passages (100) extend within the blades (26) from the first passages (66) and terminate within associated cavities (110) proximate to the tips (112) of the blades (26). Relatively cooler fuel (12.2) in the first passages (66) is thermosiphon exchanged for relatively hotter fuel (12.3) in the second passages (100) so as to cool the blades (26). The heated fuel (12.3) flows into a second cavity (74) adjacent to a second side (72) of the rotor (24) and is discharged from the rotating frame of reference directly into the combustion chamber (16) through a second rotary fluid trap (96).Type: GrantFiled: April 25, 2005Date of Patent: November 15, 2011Assignee: Williams International Co., L.L.C.Inventors: Robert S Thompson, Jr., Gregg Williams
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Publication number: 20110208400Abstract: A controller receives a power-level command representative of a level of power to be transmitted by a single-spool turboshaft engine to a controllable load. A torque command determined responsive to a measure of inlet pressure, from a control schedule responsive to the power-level command, is representative of a level of torque to be transmitted by an element to drive the controllable load. Under some operating conditions, a rotational speed command provides for at least nearly minimizing a measure of associated fuel consumption when the transmitted torque is regulated to the level corresponding to the torque command by controlling one of the controllable load and a fuel flow to the engine, and the other of the controllable load and the fuel flow to the engine is controlled so as to regulate an associated rotational speed to a level corresponding to the rotational speed command.Type: ApplicationFiled: February 23, 2011Publication date: August 25, 2011Applicant: WILLIAMS INTERNATIONAL CO., L.L.C.Inventors: Ray D. LICKFOLD, Gregg WILLIAMS, Robert S. THOMPSON, JR.
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Publication number: 20110041509Abstract: Fuel (12) is supplied to a rotatable portion (118) of a gas turbine engine (10) comprising a rotor (24) and at least one blade (26, 26.1) operatively coupled thereto, so as to provide for cooling at least one of the rotor (24) and the at least one blade (26, 26.1) by transforming the fuel (12) to a vapor or gaseous state. The fuel (12) is discharged is a vapor or gaseous state from the rotatable portion (118) directly into a combustion chamber (16) of the gas turbine engine (10).Type: ApplicationFiled: April 9, 2009Publication date: February 24, 2011Inventors: Robert S. Thompson, JR., Gregg Williams
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Publication number: 20110007991Abstract: Lubrication fluid is discharged through an axial gap between a outer bearing race and a bearing housing from an enclosed volume bounded in part by a forward surface of the outer bearing race that is axially slideable within the bearing housing so as to provide for changing the axial gap. The pressure in the enclosed volume is automatically controlled responsive to an axial force on outer bearing race by an axial position of the outer bearing race that determines a size of the axial gap, so as to provide for increasing the pressure responsive to increasing axial force over at least a portion of an operating range. The lubrication fluid in the axial gap provides for isolating axial vibrations of the outer bearing race relative to the bearing housing.Type: ApplicationFiled: July 8, 2010Publication date: January 13, 2011Applicant: WILLIAMS INTERNATIONAL CO., L.L.C.Inventors: Craig R. Miller, Robert S. Thompson, JR.
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Publication number: 20080199303Abstract: Fuel (12) supplied to a rotary fluid trap (42) is centrifugally accelerated within a first cavity (46) adjacent a first side (48) of a rotor (24), and is then directed though a plurality of first passages (66) extending through the rotor (24) between and proximate to the blades (26), and shaped so as to at least partially conform to the shape of the blades (26). Second passages (100) extend within the blades (26) from the first passages (66) and terminate within associated cavities (110) proximate to the tips (112) of the blades (26). Relatively cooler fuel (12.2) in the first passages (66) is thermosiphon exchanged for relatively hotter fuel (12.3) in the second passages (100) so as to cool the blades (26). The heated fuel (12.3) flows into a second cavity (74) adjacent to a second side (72) of the rotor (24) and is discharged from the rotating frame of reference directly into the combustion chamber (16) through a second rotary fluid trap (96).Type: ApplicationFiled: April 25, 2005Publication date: August 21, 2008Applicant: WILLIAMS INTERNATIONAL CO., L.L.C.Inventors: Robert S. Thompson Jr, Gregg Williams
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Patent number: 6988367Abstract: Fuel supplied to a rotary fluid trap is centrifugally accelerated within a first cavity adjacent a first side of a rotor, and is then directed though a plurality of first passages extending through the rotor between and proximate to the blades, and shaped so as to at least partially conform to the shape of the blades. Second passages extend within the blades from the first passages and terminate within associated cavities proximate to the tips of the blades. Relatively cooler fuel in the first passages is thermosiphon exchanged for relatively hotter fuel in the second passages so as to cool the blades. The heated fuel flows into a second cavity adjacent to a second side of the rotor and is discharged from the rotating frame of reference directly into the combustion chamber through a second rotary fluid trap. A separate fuel distribution circuit is used for starting and warm-up.Type: GrantFiled: April 20, 2004Date of Patent: January 24, 2006Assignee: Williams International Co. L.L.C.Inventors: Robert S. Thompson Jr., Gregg Williams
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Patent number: 6269647Abstract: A rotor system for a rocket engine comprises a first hollow shaft portion and a surrounding annular duct. The interior of the first hollow shaft portion is adapted to receive a first propellant component, and is in fluid communication with a first rotary orifice. The annular duct is adapted to receive a second propellant component, and is in fluid communication with a second rotary orifice located proximate to the first rotary orifice. The rotor system further comprises a third rotary orifice operatively connected to second hollow shaft portion and in fluid communication with the interior of the first hollow shaft portion for discharging a second portion of the first propellant component at second location. The rotary orifices are operatively connected to respective rotary pressure traps that isolate the pressure at the respective rotary orifices from the respective inlet pressures of the respective propellant components.Type: GrantFiled: March 10, 2000Date of Patent: August 7, 2001Inventors: Robert S. Thompson, Jr., Gregg G. Williams
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Patent number: 6220016Abstract: A rocket engine comprises first and second combustion chambers with respective combustion chamber liners bounding respective annular passages, wherein the first combustion chamber discharges into the second, and the respective annular passages are in fluid communication with one another. A portion of the effluent from the first combustion chamber flows from the first combustion chamber to the second combustion chamber through the respective annular passages via orifices in the respective combustion chamber liners, so as to provide for effusion cooling of a surface of the second combustion chamber. The first combustion chamber preferably operates fuel rich, reducing the temperature of the effusion cooling gases, which may be further cooled by a portion of unburned fuel. A flow restriction such as a turbine between the first and second combustion chambers provides a pressure differential therebetween that induces flow of effusion cooling gases.Type: GrantFiled: March 10, 2000Date of Patent: April 24, 2001Inventors: Guido D. Defever, Robert S. Thompson, Jr.
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Patent number: 6205770Abstract: A rocket engine comprises first and second rotary injectors for injecting respective fuel and oxidizer propellant components into a first combustion chamber, and the effluent therefrom drives a turbine that rotates the rotary injectors. The mixture within the first combustion chamber is preferably fuel-rich so as to reduce the associated combustion temperature, and the fuel-rich effluent mixes in a second combustion chamber with additional oxidizer injected by a third rotary injector so as to generate a high temperature effluent suitable for propulsion. The rotary injectors are adapted so as to isolate the low pressure propellant supply from the relatively high pressures in the respective combustion chambers.Type: GrantFiled: March 10, 2000Date of Patent: March 27, 2001Inventors: Gregg G. Williams, Robert S. Thompson, Jr., Richard D. Stephens, Dean S. Musgrave, John F. Jones, Guido D. Defever
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Patent number: 6189324Abstract: An environmental control unit to supply cool dry air to an aircraft cabin has a plurality of bleed air sources from an aircraft engine compressor supplying working fluid to an air cycle cooling circuit. An electronic control computer having a plurality of inputs and selects a bleed air source depending upon cabin cooling and pressurization requirements. A speed control valve responsive to an output from the control computer, modulates the flow of working fluid through a turbo-alternator, thereby synchronizing the frequency of electrical power produced by the turbo-alternator with that of an aircraft engine alternator. The turbo-alternator supplies additional electrical power to the aircraft, thereby minimizing the deleterious effect of warm air bled from the engine compressor on aircraft performance.Type: GrantFiled: October 5, 1999Date of Patent: February 20, 2001Inventors: Samuel B. Williams, John F. Jones, Robert S. Thompson, Jr.