Patents by Inventor Raymond B. Edelman
Raymond B. Edelman 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).
-
Patent number: 8091336Abstract: A pulse detonation wave engine (PDWE) detonation system provides for optical ignition. The detonation system has a plurality of detonation banks, where each detonation bank has a plurality of detonation chambers for receiving a fuel/oxidizer mixture from a propellant source. An optical ignition subsystem generates a plurality of optical pulses. The detonation system also has an optical transport subsystem for transporting the optical pulses from the ignition subsystem to the chambers, where the optical pulses ignite each fuel/oxidizer mixture such that the chambers detonate in a desired order. This allows the banks to be sequentially detonated and the chambers within each bank to be simultaneously detonated, without the increased tankage and toxic ignition associated with conventional approaches.Type: GrantFiled: December 14, 2000Date of Patent: January 10, 2012Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: Raymond B. Edelman, Herbert R. Lander, Jeffrey H. Hunt
-
Publication number: 20080098741Abstract: A dual mode scramjet engine has an isolator that serves to minimize combustor influence on inlet operation, a combustor for operation in both ramjet and scramjet mode, and a centerbody positioned within the isolator. The centerbody has an end at an entrance to the combustor.Type: ApplicationFiled: October 25, 2006Publication date: May 1, 2008Inventors: William W. Follett, Allen Lewis Goldman, Calvin Q. Morrison, Raymond B. Edelman
-
Publication number: 20080087010Abstract: A pulse detonation wave engine (PDWE) detonation system provides for optical ignition. The detonation system has a plurality of detonation banks, where each detonation bank has a plurality of detonation chambers for receiving a fuel/oxidizer mixture from a propellant source. An optical ignition subsystem generates a plurality of optical pulses. The detonation system also has an optical transport subsystem for transporting the optical pulses from the ignition subsystem to the chambers, where the optical pulses ignite each fuel/oxidizer mixture such that the chambers detonate in a desired order. This allows the banks to be sequentially detonated and the chambers within each bank to be simultaneously detonated, without the increased tankage and toxic ignition associated with conventional approaches.Type: ApplicationFiled: December 14, 2000Publication date: April 17, 2008Inventors: Raymond B. Edelman, Herbert R. Lander, Jeffrey H. Hunt
-
Publication number: 20080060361Abstract: A multi-height ramp injection system, for use in a supersonic propulsion system, comprises a plurality of multi-height ramp injectors for variably introducing a fuel into an airflow in a combustor. In one embodiment of the invention, the multi-height ramp injectors comprise a plurality of tall injectors for fueling an inner portion of the airflow, and a plurality of short injectors for fueling an outer portion of the airflow.Type: ApplicationFiled: September 7, 2006Publication date: March 13, 2008Inventors: Calvin Q. Morrison, Raymond B. Edelman
-
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
-
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.
-
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
-
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
-
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.
-
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
-
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
-
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
-
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