Patents by Inventor Pierre Francois Pinard
Pierre Francois Pinard 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: 20240100589Abstract: A setter for an investment casting core is provided. The setter may include: a base section; and a cover section configured to mechanically couple to the base section and having a profile for receiving the investment casting thereon. A setter array for a plurality of investment casting cores is further provided. A method for supporting an investment casting core during heat treatment using the setter is also provided.Type: ApplicationFiled: September 20, 2023Publication date: March 28, 2024Inventors: Keith Joseph DeCarlo, Liam Gabriel Saccucci-Bryan, Pierre Francois Pinard, Rehan Afzal
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Patent number: 8726630Abstract: 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: GrantFiled: December 1, 2006Date of Patent: May 20, 2014Assignee: General Electric CompanyInventors: Pierre Francois Pinard, Kevin Michael Hinckley, Venkat Eswarlu Tangirala, Adam Rasheed, David Michael Chapin, Anthony John Dean
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Patent number: 7828546Abstract: A pulse detonation device for dividing a pulse detonation shock wave into an primary and control portion to reduce the strength of a propagating shock wave and/or change its direction. The device contains a flow separator which directs a portion of the shock wave into itself, thus reducing the shock wave's strength. In one configuration, the control region converges in cross-sectional area so as to accelerate the flow in the control region, while the primary region diverges to slow the flow in the primary region. The flow in the control region is directed, at an angle, into the flow of the primary region to impede and/or redirect the flow of the primary region.Type: GrantFiled: June 30, 2005Date of Patent: November 9, 2010Assignee: General Electric CompanyInventors: James Fredric Wiedenhoefer, Adam Rasheed, Anthony John Dean, Pierre Francois Pinard
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Patent number: 7669405Abstract: 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: GrantFiled: December 22, 2005Date of Patent: March 2, 2010Assignee: General Electric CompanyInventors: Pierre Francois Pinard, Venkat Eswarlu Tangirala, Adam Rasheed, Anthony John Dean, Ronald Scott Bunker, David Michael Chapin
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Patent number: 7634904Abstract: 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: GrantFiled: January 9, 2006Date of Patent: December 22, 2009Assignee: General Electric CompanyInventors: Adam Rasheed, Anthony John Dean, Venkat Eswarlu Tangirala, Pierre Francois Pinard, Christian Lee Vandervort
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Publication number: 20090139203Abstract: 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: ApplicationFiled: November 14, 2008Publication date: June 4, 2009Applicant: General Electric CompanyInventors: Adam Rasheed, Ross Hartley Kenyon, David Chapin, Kevin Hinckley, Pierre Francois Pinard
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Publication number: 20090139199Abstract: 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: ApplicationFiled: November 14, 2008Publication date: June 4, 2009Applicant: General Electric CompanyInventors: 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
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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: 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: 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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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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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