Patents by Inventor Shahram Farhangi
Shahram Farhangi 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: 20060242907Abstract: A gasifier injection module includes a two-stage slurry splitter and an injector face plate with a coolant system incorporated therein. The two-stage slurry splitter includes a main cavity into which a main slurry flow is provided. The main cavity includes a plurality of first stage flow dividers that divide the main slurry flow into a plurality of secondary slurry flows that flow into a plurality of secondary cavities that extend from the main cavity. Each secondary cavity includes a plurality of second stage flow dividers that divide each secondary slurry flow into a plurality of tertiary slurry flows that flow into a plurality of slurry injection tubes extending from the secondary cavities. The tertiary flows are injected as high pressure slurry streams into the gasification chamber via the slurry injection tubes. A reactant is impinged at high pressure, as an annular shaped spray, on each high pressure slurry stream via a plurality of annular impinging orifices incorporated into the injector face plate.Type: ApplicationFiled: April 29, 2005Publication date: November 2, 2006Inventors: Kenneth Sprouse, Shahram Farhangi, David Matthews
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Patent number: 7127899Abstract: An air/fuel pre-mixer for a gas turbine combustor and a method of pre-mixing air and fuel for a combustor are provided. In one embodiment the pre-mixer includes a first annular premix fuel manifold disposed upstream of the combustor and an annular member concentric with the first premix fuel manifold. Together the annular premix fuel manifold and the annular member define a first venturi shaped air/fuel pre-mix volume between them that has a throat. At or upstream from the throat, the first premix fuel manifold has a plurality of pores whereby the fuel is injected from the first premix fuel manifold to mix with air in the first pre-mix volume. In another embodiment, the annular member is an outer wall, whereas in yet another embodiment, the annular member is a second premix fuel manifold.Type: GrantFiled: February 26, 2004Date of Patent: October 31, 2006Assignee: United Technologies CorporationInventors: Kenneth M. Sprouse, Shahram Farhangi, Mark D. Horn, David R. Matthews
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Patent number: 7124574Abstract: A system to provide a two piece robust fluid injector. According to various embodiments, the fluid injector is a fuel injector for a combustion engine. The injector includes two coaxially formed annuluses. One annulus is formed in a face plate and the second annulus or hole is defined by a tube extending through the face plate. The tube extends through the face plate in a portion of a through bore which also is used to define the second annulus. The second annulus is formed using a throughbore through which the tube extends. This allows the second annulus to always be formed inherently and precisely substantially coaxial with the first annulus. Moreover, the second annulus can be formed with a much greater tolerance than if other independent components needed to be added.Type: GrantFiled: December 4, 2002Date of Patent: October 24, 2006Assignee: United Technologies CorporationInventors: Mark D. Horn, Shinjiro Miyata, Shahram Farhangi
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Publication number: 20060230743Abstract: A system, such as a turbine power production system, including a plurality of combustion chambers. The combustion chamber may be provided with an ignition system that allows for substantially simultaneous ignition of each of the plurality of the combustors. Generally, a detonation wave may be provided to each of the combustion chambers substantially simultaneously from a single ignition combustion wave chamber.Type: ApplicationFiled: June 13, 2006Publication date: October 19, 2006Inventors: Kenneth Sprouse, Shahram Farhangi
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Patent number: 7117676Abstract: A premixer for a combustor to entrain a selected volume of fuel in an oxidizer to be combusted to heat the oxidizer. The combustor is for a gas powered turbine which employs the hypergolic or high energy air stream which will allow a fuel to be combusted in the absence of an additional ignition source. A heat exchanger and a catalyst combusts a first portion of fuel in air without the production of undesired chemical species. The catalyst is employed to lower the combustion temperature of the fuel to substantially eliminate selected chemical species. The fuel premixed in the air then encounters the catalyst and the fuel is combusted to increase the temperature of the air to an auto-ignition temperature so that no other ignition source is needed to combust additional fuel added later.Type: GrantFiled: March 26, 2003Date of Patent: October 10, 2006Assignee: United Technologies CorporationInventors: Shahram Farhangi, Kenneth M Sprouse, David R Matthews
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Patent number: 7117674Abstract: A combustor for a gas powered turbine which employs a heat exchanger and a catalyst to combust a fuel without the emission of undesired chemical species. A gas powered turbine requires expanding gases to power the turbine blades. Fuel is combusted to produce the required gases. A catalyst is employed to lower the combustion temperature of the fuel. The catalyst is placed on a set of tubes in the heat exchanger such that a portion of the thermal energy may be transferred to the air before it engages the catalyst. After encountering the catalyst, the combusted fuel increases the temperature of the air to an auto-ignition temperature so that no other ignition source is needed to combust additional fuel.Type: GrantFiled: December 5, 2003Date of Patent: October 10, 2006Assignee: The Boeing CompanyInventors: Kenneth M Sprouse, Shahram Farhangi, Michael P Moriarty, David R Matthews
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Patent number: 7111463Abstract: A system, such as a turbine power production system, including a plurality of combustion chambers. The combustion chamber may be provided with an ignition system that allows for substantially simultaneous ignition of each of the plurality of the combustors. Generally, a detonation wave may be provided to each of the combustion chambers substantially simultaneously from a single ignition combustion wave chamber.Type: GrantFiled: January 23, 2004Date of Patent: September 26, 2006Assignee: Pratt & Whitney Rocketdyne Inc.Inventors: Kenneth M Sprouse, Shahram Farhangi
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Publication number: 20060210457Abstract: A gasifier system is provided that includes a gasification chamber spool that has a ceramic matrix composite (CMC) liner adapted to form a solidified slag protective layer on an interior surface of the liner from molten slag flowing through the gasification chamber spool. The gasification system additionally includes a heat exchanger (HEX) quench spool that also includes a CMC liner adapted to form a solidified slag protective layer on an interior surface of the liner from molten slag flowing through the HEX quench spool. Additionally, the HEX quench spool includes a parallel plate HEX core having a plurality of CMC panels. The CMC panels are adapted to form a solidified slag protective layer on exterior surfaces of each respective CMC panel from molten slag flowing through the HEX quench spool.Type: ApplicationFiled: March 16, 2005Publication date: September 21, 2006Inventors: Kenneth Sprouse, Shahram Farhangi, David Matthews
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Publication number: 20060156729Abstract: A combustor for a gas powered turbine which employs a heat exchanger and a catalyst to combust a fuel without the emission of undesired chemical species. A gas powered turbine requires expanding gases to power the turbine blades. Fuel is combusted to produce the required gases. A catalyst is employed to lower the combustion temperature of the fuel. The catalyst is placed on a set of tubes in the heat exchanger such that a portion of the thermal energy may be transferred to the air before it engages the catalyst. After encountering the catalyst, the combusted fuel increases the temperature of the air to an auto-ignition temperature so that no other ignition source is needed to combust additional fuel.Type: ApplicationFiled: December 5, 2003Publication date: July 20, 2006Inventors: Kenneth Sprouse, Shahram Farhangi, Michael Moriarty, David Matthews
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Publication number: 20060096294Abstract: A combustor assembly for a gas powered turbine includes a premix section to mix a first selected volume of fuel with a selected oxidizer. The premix section includes an injector plate that includes a porosity according to selected characteristics, such as pore size, pore density, pore distribution, and other selected characteristics. Therefore, the fuel may be provided through the porous plate to the premix area in a selected uniform flux.Type: ApplicationFiled: December 19, 2005Publication date: May 11, 2006Inventors: Shahram Farhangi, David Matthews
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Patent number: 7017329Abstract: A combustor assembly for a gas powered turbine includes a premix section to mix a first selected volume of fuel with a selected oxidizer. The premix section includes an injector plate that includes a porosity according to selected characteristics, such as pore size, pore density, pore distribution, and other selected characteristics. Therefore, the fuel may be provided through the porous plate to the premix area and a selected uniform flux.Type: GrantFiled: October 10, 2003Date of Patent: March 28, 2006Assignee: United Technologies CorporationInventors: Shahram Farhangi, David R Matthews
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Publication number: 20050188703Abstract: An air/fuel pre-mixer for a gas turbine combustor and a method of pre-mixing air and fuel for a combustor are provided. In one embodiment the pre-mixer includes a first annular premix fuel manifold disposed upstream of the combustor and an annular member concentric with the first premix fuel manifold. Together the annular premix fuel manifold and the annular member define a first venturi shaped air/fuel pre-mix volume between them that has a throat. At or upstream from the throat, the first premix fuel manifold has a plurality of pores whereby the fuel is injected from the first premix fuel manifold to mix with air in the first pre-mix volume. In another embodiment, the annular member is an outer wall, whereas in yet another embodiment, the annular member is a second premix fuel manifold.Type: ApplicationFiled: February 26, 2004Publication date: September 1, 2005Inventors: Kenneth Sprouse, Shahram Farhangi, Mark Horn, David Matthews
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Publication number: 20050160717Abstract: A system, such as a turbine power production system, including a plurality of combustion chambers. The combustion chamber may be provided with an ignition system that allows for substantially simultaneous ignition of each of the plurality of the combustors. Generally, a detonation wave may be provided to each of the combustion chambers substantially simultaneously from a single ignition combustion wave chamber.Type: ApplicationFiled: January 23, 2004Publication date: July 28, 2005Inventors: Kenneth Sprouse, Shahram Farhangi
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Publication number: 20050120717Abstract: A combustor and injector system to inject a selected fuel into a combustor of a gas powered turbine. Generally, the injector is able to inject a selected fuel into a stream of an oxidizer to substantially mix the fuel with the oxidizer stream before any of the fuel in the fuel fan reaches an auto ignition temperature. Therefore the fuel may be substantially combusted at once and without any substantial hot spots.Type: ApplicationFiled: December 5, 2003Publication date: June 9, 2005Inventors: Kenneth Sprouse, Shahram Farhangi, Alan von Arx, David Matthews
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Publication number: 20050076648Abstract: A combustor assembly including an injector element able to inject and substantially mix a fuel with a vitiated air stream, so that the substantially all of the fuel injected into the vitiated air stream reaches an auto ignition temperature before it combusts. Generally, the injector element expels the fuel from the injector orifice at a rate, a velocity, a trajectory, or a flow geometry able to mix the fuel with the vitiated air. Generally, the fuel is able to mix with the vitiated air in such a manner that the fuel is substantially mixed and no substantially high or substantially low concentrations of fuel exist in the air stream at the time that the fuel reaches the auto ignition temperature.Type: ApplicationFiled: October 10, 2003Publication date: April 14, 2005Inventor: Shahram Farhangi
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Publication number: 20050076647Abstract: A combustor assembly for a gas powered turbine includes a premix section to mix a first selected volume of fuel with a selected oxidizer. The premix section includes an injector plate that includes a porosity according to selected characteristics, such as pore size, pore density, pore distribution, and other selected characteristics. Therefore, the fuel may be provided through the porous plate to the premix area and a selected uniform flux.Type: ApplicationFiled: October 10, 2003Publication date: April 14, 2005Inventors: Shahram Farhangi, David Matthews
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Publication number: 20040187499Abstract: A premixer for a combustor to entrain a selected volume of fuel in an oxidizer to be combusted to heat the oxidizer. The combustor is for a gas powered turbine which employs the hypergolic or high energy air stream which will allow a fuel to be combusted in the absence of an additional ignition source. A heat exchanger and a catalyst combusts a first portion of fuel in air without the production of undesired chemical species. The catalyst is employed to lower the combustion temperature of the fuel to substantially eliminate selected chemical species. The fuel premixed in the air then encounters the catalyst and the fuel is combusted to increase the temperature of the air to an auto-ignition temperature so that no other ignition source is needed to combust additional fuel added later.Type: ApplicationFiled: March 26, 2003Publication date: September 30, 2004Inventors: Shahram Farhangi, Kenneth M. Sprouse, David R. Matthews
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Publication number: 20040107692Abstract: A system to provide a two piece robust fluid injector. According to various embodiments, the fluid injector is a fuel injector for a combustion engine. The injector includes two coaxially formed annuluses. One annulus is formed in a face plate and the second annulus or hole is defined by a tube extending through the face plate. The tube extends through the face plate in a portion of a through bore which also is used to define the second annulus. The second annulus is formed using a throughbore through which the tube extends. This allows the second annulus to always be formed inherently and precisely substantially coaxial with the first annulus. Moreover, the second annulus can be formed with a much greater tolerance than if other independent components needed to be added.Type: ApplicationFiled: December 4, 2002Publication date: June 10, 2004Inventors: Mark D. Horn, Shinjiro Miyata, Shahram Farhangi
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Publication number: 20040003598Abstract: A combustor for a gas powered turbine which employs a hypergolic or high energy air stream and an injector design to mix fuel with the high energy hypergolic air stream faster than the combustion rate of the fuel. A heat exchanger and a catalyst combusts a first portion of fuel in air without the production of undesired chemical species. A gas powered turbine requires expanding gases to power the turbine fans or blades. Fuel is generally combusted to produce the required gases. A catalyst is employed to lower the combustion temperature of the fuel. The catalyst is placed on a set of tubes in a heat exchanger such that a portion of the thermal energy may be transferred to the air before it engages the catalyst. After encountering the catalyst, the fuel that was combusted increases the temperature of the air to an auto-ignition temperature so that no other ignition source is needed to combust additional fuel added later.Type: ApplicationFiled: July 3, 2002Publication date: January 8, 2004Inventor: Shahram Farhangi
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Publication number: 20030192319Abstract: A combustor for a gas powered turbine which employs a heat exchanger and a catalyst to combust a fuel without the emission of undesired chemical species. A gas powered turbine requires expanding gases to power the turbine blades. Fuel is combusted to produce the required gases. A catalyst is employed to lower the combustion temperature of the fuel. The catalyst is placed on a set of tubes in the heat exchanger such that a portion of the thermal energy may be transferred to the air before it engages the catalyst. After encountering the catalyst, the combusted fuel increases the temperature of the air to an auto-ignition temperature so that no other ignition source is needed to combust additional fuel.Type: ApplicationFiled: March 26, 2003Publication date: October 16, 2003Inventors: Kenneth Michael Sprouse, Shahram Farhangi, Michael Patrick Moriarty, David Robert Matthews