Patents by Inventor Donald H. Morris
Donald H. Morris 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: 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
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Patent number: 5109669Abstract: This invention relates to a passive self-contained auto ignition system for a hydrogen-oxygen fueled rocket engine. When the fuel for the engine is turned on, the gas pressure in the inlet tube 1 can be used to heat a small portion of the hydrogen in a resonance tube 4 and inject hot hydrogen into the combustion chamber 11 to ignite the hydrogen-oxygen fuel mixture. Once the ignition has started, the pressure in the combustion chamber changes the pressures in the resonance cavity 3, which then shuts off the resonance tubes' heating ability and so shuts off the ignition. If the fuel supply is shut off the engine is turned off and can be restarted by turning the hydrogen-oxygen supplies back on causing the resonance tube to re-ignite the engine.Type: GrantFiled: November 19, 1990Date of Patent: May 5, 1992Assignee: Rockwell International CorporationInventors: Donald H. Morris, Gary L. Briley
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Patent number: 4790721Abstract: An airfoil-shaped blade assembly having a metallic core, thin coolant liner and ceramic blade jacket includes variable-size cooling passages and a circumferential stagnant air gap to provide a substantially cooler core temperature during high temperature operations.Type: GrantFiled: April 25, 1988Date of Patent: December 13, 1988Assignee: Rockwell International CorporationInventors: Donald H. Morris, Daniel M. Shea
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Patent number: 4759528Abstract: A lightweight propellant valve is provided which incorporates a magnetic flux-shifting actuator associated with a magnetic coil for determining a flux flow path therein.Type: GrantFiled: November 16, 1987Date of Patent: July 26, 1988Assignee: Rockwell International CorporationInventor: Donald H. Morris
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Patent number: 4745670Abstract: A method for making chemical laser nozzle arrays in which individual mandrels are molded of plastic material in the shape of the nozzle openings. The mandrels are secured with the mouth end attached to a base plate. Metal is electrodeposited on the base plate to a thickness in excess of the length the mandrels project above the base plate. The surface of the deposited metal is ground down to expose the throat ends of the nozzle-forming mandrels. The deposited metal is separated from the base plate and the arbors removed to provide an array of nozzle openings in the deposited metal.Type: GrantFiled: October 28, 1980Date of Patent: May 24, 1988Assignee: Rockwell International CorporationInventor: Donald H. Morris
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Patent number: 4307842Abstract: A plurality of arcuate, secondary (fuel) nozzle members are juxtaposed, so that respective two of them define between them a curved, primary slit nozzle, producing a primary (oxidizer) expansion flow while the two flows mix downstream, predominantly transversely to the expansion. The nozzle members are mounted in the aperture of a plate; large-scale assemblies are described.Type: GrantFiled: October 5, 1979Date of Patent: December 29, 1981Assignee: Rockwell International CorporationInventor: Donald H. Morris