Patents by Inventor Anthony John Dean
Anthony John Dean 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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Publication number: 20080310981Abstract: A positive displacement flow separator contains a rotor portion positioned inside a casing portion to act as a least area rotor which captures a volume and moves the volume along the length of the separator. The rotor portion contains a plurality of lobes which interact with grooves in the casing portion, such that the interaction of the lobes and grooves create barriers which capture the volume The creation of the volume creates a flow barrier between a downstream end of the separator and an upstream end of the separator. The flow separator is coupled to a combustion portion to provide a flow of material to the combustion portion.Type: ApplicationFiled: June 12, 2007Publication date: December 18, 2008Applicant: GENERAL ELECTRIC COMPANYInventors: James Fredric Wiedenhoefer, Adam Rasheed, Pierre Francois Pinard, Anthony John Dean, Charles Max Byrd
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Publication number: 20080310982Abstract: A positive displacement flow separator or combustor contains a rotor portion positioned inside a casing portion to act as a least area rotor which captures a volume and moves the volume along the length of the separator. The rotor portion contains a plurality of lobes which interact with grooves in the casing portion, such that the interaction of the lobes and grooves create barriers which capture the volume. The creation of the volume creates a flow barrier between a downstream end of the separator and an upstream end of the separator.Type: ApplicationFiled: June 12, 2007Publication date: December 18, 2008Applicant: GENERAL ELECTRIC COMPANYInventors: James Fredric Wiedenhoefer, Adam Rasheed, Anthony John Dean, Venkat Eswarlu Tangirala
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Publication number: 20080229756Abstract: A pulse detonation device contains a pulse detonation combustor which detonates a mixture of oxidizer and fuel. The fuel is supplied through fuel ducts and the fuel flow is controlled by fuel flow control devices. Oxidizer flow is provided through a main inlet portion and a flow control device directs the oxidizer flow to either the combustor or to a bypass duct, or both. The combustor further contains an ignition source. Each of the flow control devices, fuel flow control devices and ignition source are controlled by a control system to optimize performance at different thrust/power settings for the device.Type: ApplicationFiled: December 1, 2006Publication date: September 25, 2008Applicant: General Electric CompanyInventors: Pierre Francois Pinard, Kevin Michael Hinckley, Venkat Eswarlu Tangirala, Adam Rasheed, David Michael Chapin, Anthony John Dean
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Publication number: 20080155959Abstract: A transition piece for use within a gas turbine engine provides a path between the exhaust from one or more pressure-rise combustors and a downstream turbine for the extraction of work from the exhaust flow. The transition piece provides a non-expanding path for the exhaust flow through the transition piece, and directs the flow so as to be effective in driving the turbine when it reaches the end of the transition piece.Type: ApplicationFiled: December 21, 2007Publication date: July 3, 2008Applicant: GENERAL ELECTRIC COMPANYInventors: Adam Rasheed, Anthony John Dean, James Fredric Wiedenhoefer, Venkat Eswarlu Tangirala, Narendra Digamber Joshi
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Publication number: 20080127728Abstract: A pulse detonation device contains a detonation chamber and a propagation portion, and a plurality of mechanical response gauges coupled to an exterior surface of at least one of the detonation chamber and the propagation portion. Signals from the mechanical response gauges are sent to high frequency AC-coupled amplifiers, and the amplified signals are sent to a high frequency data acquisition system. Based on the data from the mechanical response gauges, the velocity of a detonation pressure wave is determined.Type: ApplicationFiled: November 30, 2006Publication date: June 5, 2008Applicant: General Electric CompanyInventors: Mark Felipe Baptista, Adam Rasheed, Anthony John Dean
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Publication number: 20080127630Abstract: An engine contains at least one pulse detonation combustor which is positioned upstream of a turbine section, a stage of which is a Curtiss type turbine stage. Following the initial Curtiss type turbine stage, is either of a Rateau type turbine stage or a high efficiency turbine stage, or a combination thereof.Type: ApplicationFiled: December 1, 2006Publication date: June 5, 2008Applicant: General Electric CompanyInventors: Christian Lee Vandervort, Adam Rasheed, Anthony John Dean, Pierre Francois Pinard
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Publication number: 20080115480Abstract: An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one converging-diverging structure to dampen or choke the upstream propagation of shock waves from the pulse detonation combustor through the bypass flow air duct. The bypass air also serves to cool the outer surfaces of the pulse detonation combustor. The bypass air flow is controlled in tandem with the heat release from the PDC to provide the appropriate amount of thermal energy to a downstream energy conversion device, such as a turbine. A mixing plenum is positioned downstream of the pulse detonation combustor and bypass flow air duct.Type: ApplicationFiled: November 17, 2006Publication date: May 22, 2008Applicant: General Electric CompanyInventors: Adam Rasheed, Anthony John Dean, Pierre Francois Pinard, Christian Lee Vandervort, Venkat Eswarlu Tangirala
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Publication number: 20080098748Abstract: A dual mode combustor of a gas turbine engine contains at least one dual mode combustor device having a combustion chamber, a fuel air mixing element, a high frequency solenoid valve and a fuel injector. During a first mode of operation the dual mode combustor device operates in a steady, constant pressure deflagration mode, receiving its fuel from the fuel injector. In a second mode of operation the dual mode combustor device operates in a pulse detonation mode, receiving its fuel from the high frequency solenoid valve.Type: ApplicationFiled: October 31, 2006Publication date: May 1, 2008Applicant: General Electric CompanyInventors: Venkat Eswarlu Tangirala, Adam Rasheed, Anthony John Dean
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Publication number: 20080098710Abstract: A pulse detonation engine contains a mechanically driven timing device coupled with a stator device, where the timing device has both an opening portion and a blocking portion. The opening and blocking portions open and close air flow access to a detonation chamber of the pulse detonation engine at appropriate times during the pulse detonation cycle.Type: ApplicationFiled: October 31, 2006Publication date: May 1, 2008Applicant: General Electric CompanyInventors: Jonathan Sebastian Janssen, Venkat Eswarlu Tangirala, Anthony John Dean, James Fredric Wiedenhoefer
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Patent number: 7260935Abstract: A low emission turbine includes a reverse flow can-type combustor that generally includes a primary and secondary fuel delivery system that can be independently controlled to produce low CO, UHC, and NOx emissions at design set point and at conditions other than design set point. The reverse flow can-type combustor generally includes an annularly arranged array of swirler and mixer assemblies within the combustor, wherein each swirler and mixer in the array includes a primary and secondary fuel delivery system that can be independently controlled. Also disclosed herein is a can-type combustor that includes fluid passageways that perpendicularly impinge the outer surface of a heat shield. Processes for operating the can-type combustors are also disclosed.Type: GrantFiled: June 2, 2005Date of Patent: August 28, 2007Assignee: General Electric CompanyInventors: Andrei Colibaba-Evulet, Michael John Bowman, Simon Ralph Sanderson, Anthony John Dean
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Patent number: 7200987Abstract: The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation tube in the pulse detonation stage. The off-axis pulse detonation tube detonates a mixture containing the compressed flow and a fuel to create a detonation wave, which is routed to an inlet portion of a reverse flow turbine. The exhaust flow from the reverse flow turbine is then directed away from the engine through ducting.Type: GrantFiled: June 18, 2004Date of Patent: April 10, 2007Assignee: General Electric CompanyInventors: Edward Joseph Hall, Adam Rasheed, Anthony John Dean
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Patent number: 7150143Abstract: A power system includes a fuel cell module adapted to receive a first fuel and a pulse detonation combustor adapted to receive and detonate a second fuel and exhaust a number of detonation products to create thrust for propulsion, mechanical work extraction or electrical power production.Type: GrantFiled: July 21, 2003Date of Patent: December 19, 2006Assignee: General Electric CompanyInventors: Louis Andrew Schick, Anthony John Dean
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Patent number: 7131260Abstract: The present invention is a pulse detonation combustion system, having a plurality of detonation initiation devices coupled to a main combustion chamber, where each of the detonation initiation devices is operating out-of-phase with each other. Each of the detonation initiation devices assists in the initiation of a detonation in the main combustion chamber, out-of-phase from each other such that the operational frequency of the pulse detonation combustion system is related to the number of detonation initiation devices multiplied by the operational frequency of a single detonation initiation device.Type: GrantFiled: June 18, 2004Date of Patent: November 7, 2006Assignee: General Electric CompanyInventors: Anthony John Dean, Keith Robert McManus, Venkat Eswarlu Tangirala
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Patent number: 7093794Abstract: An aircraft includes at least one airfoil having a leading edge and a trailing edge. A number of pulse detonation engines are distributed along one of the leading and trailing edges of the airfoil and are positioned beneath the airfoil. Each pulse detonation engine is adapted for impulsively detonating a fuel/oxidizer mixture to generate a thrust force and to apply the thrust force to the aircraft. At least one of the pulse detonation engines is movably configured for altering a direction of the thrust force relative to the airfoil.Type: GrantFiled: November 22, 2002Date of Patent: August 22, 2006Assignee: General Electric CompanyInventors: Ivett Alejancra Leyva, Anthony John Dean
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Patent number: 7055308Abstract: An engine includes at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer. The pulse detonation chamber has an outlet end and includes a porous liner adapted to fit within an inner surface of the pulse detonation chamber within a vicinity of the outlet end. The engine also includes a casing housing the pulse detonation chamber.Type: GrantFiled: May 30, 2003Date of Patent: June 6, 2006Assignee: General Electric CompanyInventors: Pierre Francois Pinard, Anthony John Dean, Adam Rasheed
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Patent number: 6983586Abstract: A two-stage pulse detonation system includes a pre-combustor and a geometric resonator connected via a converging-diverging nozzle to the pre-combustor to create a high temperature and high pressure conditions in the resonator in order to create optimal conditions for detonation initiation. A mixture of a fuel and a gas is burned in the pre-combustor and is passed through the nozzle into the geometric resonator, where the burned mixture is detonated. The detonation propagates through the resonator exit nozzle thus generating thrust.Type: GrantFiled: December 8, 2003Date of Patent: January 10, 2006Assignee: General Electric CompanyInventors: Venkat Eswarlu Tangirala, Anthony John Dean, Ivett Alejandra Leyva
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Patent number: 6968693Abstract: A low emission turbine includes a reverse flow can-type combustor that generally includes a primary and secondary fuel delivery system that can be independently controlled to produce low CO, UHC, and NOx emissions at design set point and at conditions other than design set point. The reverse flow can-type combustor generally includes an annularly arranged array of swirler and mixer assemblies within the combustor, wherein each swirler and mixer in the array includes a primary and secondary fuel delivery system that can be independently controlled. Also disclosed herein is a can-type combustor that includes fluid passageways that perpendicularly impinge the outer surface of a heat shield. Processes for operating the can-type combustors are also disclosed.Type: GrantFiled: September 22, 2003Date of Patent: November 29, 2005Assignee: General Electric CompanyInventors: Andrei Colibaba-Evulet, Michael John Bowman, Simon Ralph Sanderson, Anthony John Dean
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Patent number: 6910853Abstract: A structure for attaching together or sealing a space between a first component and a second component that have different rates or amounts of dimensional change upon being exposed to temperatures other than ambient temperature. The structure comprises a first attachment structure associated with the first component that slidably engages a second attachment structure associated with the second component, thereby allowing for an independent floating movement of the second component relative to the first component. The structure can comprise split rings, laminar rings, or multiple split rings.Type: GrantFiled: November 27, 2002Date of Patent: June 28, 2005Assignee: General Electric CompanyInventors: Gregory Scot Corman, Anthony John Dean, Leonardo Tognarelli, Mario Pecchioli
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Publication number: 20040237504Abstract: An engine includes at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer. The pulse detonation chamber has an outlet end and includes a porous liner adapted to fit within an inner surface of the pulse detonation chamber within a vicinity of the outlet end. The engine also includes a casing housing the pulse detonation chamber.Type: ApplicationFiled: May 30, 2003Publication date: December 2, 2004Applicant: General Electric CompanyInventors: Pierre Francois Pinard, Anthony John Dean, Adam Rasheed
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Publication number: 20040099764Abstract: An aircraft includes at least one airfoil having a leading edge and a trailing edge. A number of pulse detonation engines are distributed along one of the leading and trailing edges of the airfoil and are positioned beneath the airfoil. Each pulse detonation engine is adapted for impulsively detonating a fuel/oxidizer mixture to generate a thrust force and to apply the thrust force to the aircraft. At least one of the pulse detonation engines is movably configured for altering a direction of the thrust force relative to the airfoil.Type: ApplicationFiled: November 22, 2002Publication date: May 27, 2004Applicant: General Electric CompanyInventors: Ivett Alejandra Leyva, Anthony John Dean