Patents by Inventor Adam Rasheed

Adam Rasheed 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).

  • Publication number: 20100071458
    Abstract: A positive displacement flow measurement device includes a rotor portion positioned inside a casing portion to act as a least area rotor that captures a volume of material and moves the volume of material along the length of the device. The device is coupled to a means for counting the number of revolutions of the rotor portion and/or the casing portion over a predetermined period of time. In one embodiment, the counting means comprises a shaft encoder that measures the angular position of a shaft of the rotor portion and sends a signal to a processor of a computing device that determines the volume of material flowing through the device.
    Type: Application
    Filed: November 30, 2009
    Publication date: March 25, 2010
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: James Fredric Wiedenhoefer, Adam Rasheed
  • Patent number: 7669405
    Abstract: A detonation chamber for a pulse detonation combustor including: a plurality of dimples disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of dimples enhance a turbulence of a fluid flow through the detonation chamber.
    Type: Grant
    Filed: December 22, 2005
    Date of Patent: March 2, 2010
    Assignee: General Electric Company
    Inventors: Pierre Francois Pinard, Venkat Eswarlu Tangirala, Adam Rasheed, Anthony John Dean, Ronald Scott Bunker, David Michael Chapin
  • Patent number: 7634904
    Abstract: A turbine disk assembly including a rotatable cylindrical member rotatably coupled to a shaft and a plurality of turbine blades extend circumferentially outward from said cylindrical member. The turbine blades include at least two different geometrical shapes, a first of the geometrical shapes is configured to facilitate extracting power from a first pulsed detonation combustor product stream. A second of said geometrical shapes is configured to facilitate extracting power from a second pulsed detonation combustor product stream that is different from the first pulsed detonation combustor product stream.
    Type: Grant
    Filed: January 9, 2006
    Date of Patent: December 22, 2009
    Assignee: General Electric Company
    Inventors: Adam Rasheed, Anthony John Dean, Venkat Eswarlu Tangirala, Pierre Francois Pinard, Christian Lee Vandervort
  • Publication number: 20090266047
    Abstract: An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is oriented longitudinally and/or tangentially with respect to a centerline of the engine.
    Type: Application
    Filed: November 14, 2008
    Publication date: October 29, 2009
    Applicant: General Electric Company
    Inventors: Ross Hartley Kenyon, Narendra Digamber Joshi, Venkat Eswarlu Tangirala, Anthony John Dean, Adam Rasheed, Aaron Jerome Glaser
  • Publication number: 20090241507
    Abstract: A ground based power generation system contains at least two compressor stages, a combustion stage and a turbine stage. An intercooler is positioned between the two compressor stages and a regenerator is positioned between the compressor stages and the combustion stage. The combustion stage contains at least one of a pulse detonation combustor and constant volume combustor. Downstream of the combustion stage is the turbine stage. Heat for the regenerator is supplied from the turbine stage. Further, a bypass flow device is included which re-directs flow upstream of the combustion stage to downstream of the combustion stage and upstream of the turbine stage.
    Type: Application
    Filed: April 1, 2008
    Publication date: October 1, 2009
    Applicant: General Electric Company
    Inventors: Venkat Eswarlu Tangirala, Adam Rasheed, Narendra Digamber Joshi, Anthony John Dean
  • Publication number: 20090220368
    Abstract: A positive displacement capture apparatus contains a plurality of positive displacement capture devices which each contain 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. The plurality of positive displacement capture devices are positioned, oriented and rotational timed such that eccentric loads created by the rotation of the rotor portions cancel each other out during operation.
    Type: Application
    Filed: February 29, 2008
    Publication date: September 3, 2009
    Applicant: General Electric Company
    Inventors: James Fredric Wiedenhoefer, Adam Rasheed
  • Publication number: 20090220369
    Abstract: A positive displacement capture device 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 portions 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. There is a non-contact seal between the lobes and the grooves, and the lobes have channels or depressions at their ends.
    Type: Application
    Filed: February 29, 2008
    Publication date: September 3, 2009
    Applicant: General Electric Company
    Inventors: James Fredric Wiedenhoefer, Adam Rasheed
  • Publication number: 20090139203
    Abstract: A pulse detonation combustor assembly contains at least one PDC tube, a mechanical air flow valve which directs an air flow into the PDC tube, where the mechanical air flow assembly changes a rate of the air flow into the PDC tube during a fill stage of the PDC tube. The assembly also contains a fuel flow control valve which directs fuel to the PDC tube and changes the rate of the fuel flow into PDC tube. By controlling the flow of the fuel and air into the PDC tube the equivalence ratio profile of the PDC tube can be tailored and controlled.
    Type: Application
    Filed: November 14, 2008
    Publication date: June 4, 2009
    Applicant: General Electric Company
    Inventors: Adam Rasheed, Ross Hartley Kenyon, David Chapin, Kevin Hinckley, Pierre Francois Pinard
  • Publication number: 20090139199
    Abstract: A pulse detonation combustor valve assembly contains at least one pulse detonation combustor having an inlet portion through which air and/or fuel enters the chamber of the combustor. An annular rotating valve portion is positioned adjacent to an outer surface of the pulse detonation combustor and concentrically with the pulse detonation combustor so that the annular rotating valve portion can be rotated with respect to the combustor. The annular rotating valve portion contains at least one inlet portion through which air and/or fuel passes to enter the inlet portion of the pulse detonation combustor.
    Type: Application
    Filed: November 14, 2008
    Publication date: June 4, 2009
    Applicant: General Electric Company
    Inventors: Ross Hartley Kenyon, Narendra Digamber Joshi, Venkat Eswarlu Tangirala, Anthony John Dean, Adam Rasheed, Aaron Jerome Glaser, James Fredric Wiedenhoefer, David Chapin, Kevin Hinckley, Pierre Francois Pinard
  • Publication number: 20090133377
    Abstract: An engine contains a compressor stage, a pulse detonation combustion stage and a turbine stage. The pulse detonation combustion stage contains at least one pulse detonation combustor which has an inlet portion. The pulse detonation combustor is positioned such that the inlet portion of the pulse detonation combustor is located forward of an outlet of the compressor stage with respect to the engine. The pulse detonation combustor is angled with respect to a centerline of the engine.
    Type: Application
    Filed: November 14, 2008
    Publication date: May 28, 2009
    Applicant: General Electric Company
    Inventors: Ross Hartley Kenyon, Narendra Digamber Joshi, Venkat Eswarlu Tangirala, Anthony John Dean, Adam Rasheed, Aaron Jerome Glaser
  • Patent number: 7526912
    Abstract: A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum; a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum; a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum; an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly.
    Type: Grant
    Filed: October 31, 2005
    Date of Patent: May 5, 2009
    Assignee: General Electric Company
    Inventors: Venkat Eswarlu Tangirala, Adam Rasheed, Christian Lee Vandervort, Anthony John Dean
  • Publication number: 20080310982
    Abstract: 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: Application
    Filed: June 12, 2007
    Publication date: December 18, 2008
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: James Fredric Wiedenhoefer, Adam Rasheed, Anthony John Dean, Venkat Eswarlu Tangirala
  • Publication number: 20080310981
    Abstract: 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: Application
    Filed: June 12, 2007
    Publication date: December 18, 2008
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: James Fredric Wiedenhoefer, Adam Rasheed, Pierre Francois Pinard, Anthony John Dean, Charles Max Byrd
  • Publication number: 20080229756
    Abstract: 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: Application
    Filed: December 1, 2006
    Publication date: September 25, 2008
    Applicant: General Electric Company
    Inventors: Pierre Francois Pinard, Kevin Michael Hinckley, Venkat Eswarlu Tangirala, Adam Rasheed, David Michael Chapin, Anthony John Dean
  • Publication number: 20080155959
    Abstract: 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: Application
    Filed: December 21, 2007
    Publication date: July 3, 2008
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Adam Rasheed, Anthony John Dean, James Fredric Wiedenhoefer, Venkat Eswarlu Tangirala, Narendra Digamber Joshi
  • Publication number: 20080127630
    Abstract: 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: Application
    Filed: December 1, 2006
    Publication date: June 5, 2008
    Applicant: General Electric Company
    Inventors: Christian Lee Vandervort, Adam Rasheed, Anthony John Dean, Pierre Francois Pinard
  • Publication number: 20080127728
    Abstract: 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: Application
    Filed: November 30, 2006
    Publication date: June 5, 2008
    Applicant: General Electric Company
    Inventors: Mark Felipe Baptista, Adam Rasheed, Anthony John Dean
  • Publication number: 20080115480
    Abstract: 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: Application
    Filed: November 17, 2006
    Publication date: May 22, 2008
    Applicant: General Electric Company
    Inventors: Adam Rasheed, Anthony John Dean, Pierre Francois Pinard, Christian Lee Vandervort, Venkat Eswarlu Tangirala
  • Publication number: 20080098748
    Abstract: 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: Application
    Filed: October 31, 2006
    Publication date: May 1, 2008
    Applicant: General Electric Company
    Inventors: Venkat Eswarlu Tangirala, Adam Rasheed, Anthony John Dean
  • Publication number: 20080006019
    Abstract: A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum; a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum; a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum; an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly.
    Type: Application
    Filed: October 31, 2005
    Publication date: January 10, 2008
    Inventors: Venkat Tangirala, Adam Rasheed, Christian Vandervort, Anthony Dean