Patents by Inventor Stephen N. Schmotolocha
Stephen N. Schmotolocha 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: 7762058Abstract: An ultra-compact aerovortical swirl-enhanced combustion (ASC) system features an aerovortical swirl generator for use in rocket thrusters utilizing hypergolic or non-hypergolic propellants. The ACS thruster can be sized for diameters ranging from about 0.5 to about 2.0 inches, and producing thrust levels of approximately 5 lbf to about 250 lbf. A plurality of helicoid flow channels in the swirl generator introduces swirl into a flow stream of a first propellant within ultra-compact sized rocket thrusters. The ASC system also includes injectors for introducing a second liquid propellant into the swirling flowfield to promote rapid and efficient atomization, mixing and vigorous combustion, which, results in major improvements in combustion and propulsion performance over current rocket thrusters, but in much shorter combustor systems.Type: GrantFiled: April 17, 2007Date of Patent: July 27, 2010Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: Robert J. Pederson, Stephen N. Schmotolocha
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Patent number: 7762077Abstract: A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet/rocket engine depending requirements.Type: GrantFiled: December 5, 2006Date of Patent: July 27, 2010Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: Robert J. Pederson, Stephen N. Schmotolocha, William W. Follett
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Patent number: 7690192Abstract: A rocket engine includes a combustor assembly for carrying out a combustion process of fuel and oxidizer rocket propellants to produce thrust. A swirl generator is positioned within the combustor assembly to produce a turbulent flowfield of the fuel and oxidizer rocket propellants within the combustor assembly.Type: GrantFiled: May 22, 2007Date of Patent: April 6, 2010Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: Robert J. Pederson, Stephen N. Schmotolocha
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Publication number: 20080283677Abstract: A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet/rocket engine depending requirements.Type: ApplicationFiled: December 5, 2006Publication date: November 20, 2008Applicant: Pratt & Whitney Rocketdyne, Inc.Inventors: Robert J. Pederson, Stephen N. Schmotolocha, William W. Follett
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Publication number: 20080256925Abstract: A compact rocket engine with advanced swirl combustion can generate vacuum thrust in the 500 lbf to 100,000 lbf range. The rocket engine includes a feed system, combustor assembly, swirl generator and nozzle. The feed system delivers the oxidizer and fuel to the combustor assembly in the proper phase suitable for use with the swirl generator, which is positioned within the combustor assembly. This causes a highly turbulent three-dimensional swirling flowfield produced for rapid and efficient mixing and burning of the fuel/oxidizer combustion products, which are expanded through the nozzle to produce thrust. The aerothermochemical processes are extremely efficient, and consequently produce nearly ideal thrust levels. Swirl enhanced combustion significantly reduces combustor length, weight, complexity and cost, yet provides high propulsion efficiencies and wide rocket engine throttling operability.Type: ApplicationFiled: May 22, 2007Publication date: October 23, 2008Applicant: Pratt & Whitney Rocketdyne, Inc.Inventors: Robert J. Pederson, Stephen N. Schmotolocha
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Publication number: 20080256924Abstract: An ultra-compact aerovortical swirl-enhanced combustion (ASC) system features an aerovortical swirl generator for use in rocket thrusters utilizing hypergolic or non-hypergolic propellants. The ACS thruster can be sized for diameters ranging from about 0.5 to about 2.0 inches, and producing thrust levels of approximately 5 lbf to about 250 lbf. A plurality of helicoid flow channels in the swirl generator introduces swirl into a flow stream of a first propellant within ultra-compact sized rocket thrusters. The ASC system also includes injectors for introducing a second liquid propellant into the swirling flowfield to promote rapid and efficient atomization, mixing and vigorous combustion, which, results in major improvements in combustion and propulsion performance over current rocket thrusters, but in much shorter combustor systems.Type: ApplicationFiled: April 17, 2007Publication date: October 23, 2008Applicant: Pratt & Whitney Rocketdyne, Inc.Inventors: Robert J. Pederson, Stephen N. Schmotolocha
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Publication number: 20080128547Abstract: The present invention is directed toward a two-stage hypersonic vehicle, comprising a first-stage vehicle and a second stage vehicle. The first-stage vehicle includes a combined-cycle engine and a swirl generator for propelling the first-stage vehicle and the second-stage vehicle to a threshold velocity, which in one embodiment is about Mach 6. In one embodiment, the first-stage combined-cycle engine integrates a swirl generator into a gas turbine engine, providing a highly compact afterburner and a ramjet engine within the gas turbine engine. One benefit of the integrated swirl generator is the ability to significantly reduce overall first-stage gas turbine and afterburner-ramjet size and weight, while retaining high performance. The second-stage vehicle is detachably secured to the first-stage vehicle and includes a hypersonic engine.Type: ApplicationFiled: December 5, 2006Publication date: June 5, 2008Applicant: Pratt & Whitney Rocketdyne, Inc.Inventors: Robert J. Pederson, Stephen N. Schmotolocha, William W. Follett
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Patent number: 7168236Abstract: A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and an inner central recirculation zone, both of which are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers and stabilizes flame propagation and accelerates combustion throughout the entire combustor. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L/D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits and high combustion efficiency and thrust performance.Type: GrantFiled: March 31, 2005Date of Patent: January 30, 2007Assignee: United Technologies CorporationInventors: Stephen N Schmotolocha, Robert J Pederson, Calvin Q Morrison, Jr., Raymond B Edelman, Donald H Morris
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Patent number: 7137255Abstract: An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel and an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length.Type: GrantFiled: March 31, 2005Date of Patent: November 21, 2006Assignee: United Technologies CorporationInventors: Stephen N Schmotolocha, Donald H Morris, Robert J Pederson, Raymond B Edelman, Calvin Q Morrison, Jr.
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Patent number: 6968695Abstract: A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and an inner central recirculation zone, both of which are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers and stabilizes flame propagation and accelerates combustion throughout the entire combustor. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L/D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits and high combustion efficiency and thrust performance.Type: GrantFiled: February 6, 2003Date of Patent: November 29, 2005Assignee: The Boeing CompanyInventors: Stephen N. Schmotolocha, Robert J. Pederson, Calvin Q. Morrison, Jr., Raymond B. Edelman, Donald H. Morris
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Patent number: 6912857Abstract: An improved torch igniter for use in devices such as thrust augmenters, gas turbine engines, ramjets, combined-cycle engines and industrial burners. The torch igniter includes a housing with a combustion chamber. Fuel and oxidizer are delivered into the combustion chamber and ignited by an electronic ignition source, such as a plasma jet igniter or a spark igniter, so that an upstream recirculation zone and a downstream recirculation zone are created. The upstream recirculation zone stabilizes and pilots combustion within the combustion chamber, while the downstream recirculation zone augments the combustion event. Byproducts of the combustion event within the torch igniter provide a high mass flux with high thermal energy and strong ignition source radicals that are discharged through a neck portion of the housing and are thereafter employed to initiate a primary combustion event in a primary combustor.Type: GrantFiled: March 4, 2004Date of Patent: July 5, 2005Assignee: The Boeing CompanyInventors: Stephen N. Schmotolocha, Donald H. Morris, Calvin Q. Morrison, Jr., Robert J. Pederson
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Patent number: 6907724Abstract: A combined-cycle engine having at least one core engine and at least one ramjet engine. The ramjet utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and an inner central recirculation zone, both of which are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers, which accelerate flame propagation throughout the core flowfield. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L/D ratio of the combustor.Type: GrantFiled: February 6, 2003Date of Patent: June 21, 2005Assignee: The Boeing CompanyInventors: Raymond B. Edelman, Calvin Q. Morrison, Jr., Robert J. Pederson, Donald H. Morris, Stephen N. Schmotolocha
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Patent number: 6895756Abstract: An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length.Type: GrantFiled: February 6, 2003Date of Patent: May 24, 2005Assignee: The Boeing CompanyInventors: Stephen N. Schmotolocha, Donald H. Morris, Robert J. Pederson, Raymond B. Edelman, Calvin Q. Morrison, Jr.
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Patent number: 6820411Abstract: An apparatus for providing propulsive power that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The swirl generator is compatible with the throttle range of conventional gas turbine engines, provides smooth combustion with no instabilities and minimum total pressure losses, enables significant reductions the in L/D ratio of the combustor and is readily packaged into various applications.Type: GrantFiled: September 13, 2002Date of Patent: November 23, 2004Assignee: The Boeing CompanyInventors: Robert J. Pederson, Stephen N. Schmotolocha, Donald H. Morris, Calvin Q. Morrison, Jr., Raymond B. Edelman
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Publication number: 20040168442Abstract: An improved torch igniter for use in devices such as thrust augmenters, gas turbine engines, ramjets, combined-cycle engines and industrial burners. The torch igniter includes a housing with a combustion chamber. Fuel and oxidizer are delivered into the combustion chamber and ignited by an electronic ignition source, such as a plasma jet igniter or a spark igniter, so that an upstream recirculation zone and a downstream recirculation zone are created. The upstream recirculation zone stabilizes and pilots combustion within the combustion chamber, while the downstream recirculation zone augments the combustion event. Byproducts of the combustion event within the torch igniter provide a high mass flux with high thermal energy and strong ignition source radicals that are discharged through a neck portion of the housing and are thereafter employed to initiate a primary combustion event in a primary combustor.Type: ApplicationFiled: March 4, 2004Publication date: September 2, 2004Inventors: Stephen N. Schmotolocha, Donald H. Morris, Calvin Q. Morrison, Robert J. Pederson
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Patent number: 6748735Abstract: An improved torch igniter for use in devices such as thrust augmenters, gas turbine engines, ramjets, combined-cycle engines and industrial burners. The torch igniter includes a housing with a combustion chamber. Fuel and oxidizer are delivered into the combustion chamber and ignited by an electronic ignition source, such as a plasma jet igniter or a spark igniter, so that an upstream recirculation zone and a downstream recirculation zone are created. The upstream recirculation zone stabilizes and pilots combustion within the combustion chamber, while the downstream recirculation zone augments the combustion event. Byproducts of the combustion event within the torch igniter provide a high mass flux with high thermal energy and strong ignition source radicals that are discharged through a neck portion of the housing and are thereafter employed to initiate a primary combustion event in a primary combustor.Type: GrantFiled: August 13, 2002Date of Patent: June 15, 2004Assignee: The Boeing CompanyInventors: Stephen N. Schmotolocha, Donald H. Morris, Calvin Q. Morrison, Jr., Robert J. Pederson
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Publication number: 20040050063Abstract: A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and an inner central recirculation zone, both of which are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers and stabilizes flame propagation and accelerates combustion throughout the entire combustor. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L/D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits and high combustion efficiency and thrust performance.Type: ApplicationFiled: February 6, 2003Publication date: March 18, 2004Inventors: Stephen N. Schmotolocha, Robert J. Pederson, Calvin Q. Morrison, Raymond B. Edelman, Donald H. Morris
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Publication number: 20040050061Abstract: An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length.Type: ApplicationFiled: February 6, 2003Publication date: March 18, 2004Inventors: Stephen N. Schmotolocha, Donald H. Morris, Robert J. Pederson, Raymond B. Edelman, Calvin Q. Morrison
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Publication number: 20040050056Abstract: An apparatus for providing propulsive power that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The swirl generator is compatible with the throttle range of conventional gas turbine engines, provides smooth combustion with no instabilities and minimum total pressure losses, enables significant reductions the in L/D ratio of the combustor and is readily packaged into various applications.Type: ApplicationFiled: September 13, 2002Publication date: March 18, 2004Inventors: Robert J. Pederson, Stephen N. Schmotolocha, Donald H. Morris, Calvin Q. Morrison, Raymond B. Edelman
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Publication number: 20040031257Abstract: An improved torch igniter for use in devices such as thrust augmenters, gas turbine engines, ramjets, combined-cycle engines and industrial burners. The torch igniter includes a housing with a combustion chamber. Fuel and oxidizer are delivered into the combustion chamber and ignited by an electronic ignition source, such as a plasma jet igniter or a spark igniter, so that an upstream recirculation zone and a downstream recirculation zone are created. The upstream recirculation zone stabilizes and pilots combustion within the combustion chamber, while the downstream recirculation zone augments the combustion event. Byproducts of the combustion event within the torch igniter provide a high mass flux with high thermal energy and strong ignition source radicals that are discharged through a neck portion of the housing and are thereafter employed to initiate a primary combustion event in a primary combustor.Type: ApplicationFiled: August 13, 2002Publication date: February 19, 2004Inventors: Stephen N. Schmotolocha, Donald H. Morris, Calvin Q. Morrison, Robert J. Pederson