Patents by Inventor Scott Michael Carson
Scott Michael Carson 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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Patent number: 9222437Abstract: A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end.Type: GrantFiled: September 21, 2012Date of Patent: December 29, 2015Assignee: General Electric CompanyInventors: Joseph Machnaim, Brian David Keith, Scott Michael Carson
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Publication number: 20140086739Abstract: A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end.Type: ApplicationFiled: September 21, 2012Publication date: March 27, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Joseph Machnaim, Brian David Keith, Scott Michael Carson
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Patent number: 7870719Abstract: A plasma enhanced rapidly expanded duct system includes a gas turbine engine inter-turbine transition duct having radially spaced apart conical inner and outer duct walls extending axially between a duct inlet and a duct outlet. A conical plasma generator produces a conical plasma along the outer duct wall. An exemplary embodiment of the conical plasma generator is mounted to the outer duct wall and including radially inner and outer electrodes separated by a dielectric material. The dielectric material is disposed within a conical groove in a radially inwardly facing surface of the outer duct wall. An AC power supply is connected to the electrodes to supply a high voltage AC potential to the electrodes.Type: GrantFiled: October 13, 2006Date of Patent: January 18, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Scott Michael Carson
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Patent number: 7819626Abstract: A gas turbine engine plasma blade tip clearance control system includes an annular shroud surrounding rotatable blade tips and an annular plasma generator spaced radially outwardly and apart from the blade tips. An exemplary embodiment of the annular plasma generator is mounted to the annular shroud and includes radially inner and outer electrodes separated by a dielectric material disposed within an annular groove in a radially inwardly facing surface of the annular shroud. The plasma generator is operable for producing an annular plasma between the annular shroud and blade tips and an effective clearance produced by the annular plasma between the annular shroud and blade tips that is smaller than a clearance between the annular shroud and blade tips.Type: GrantFiled: October 13, 2006Date of Patent: October 26, 2010Assignee: General Electric CompanyInventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Scott Michael Carson
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Publication number: 20100251696Abstract: A plasma enhanced rapidly expanded duct system includes a gas turbine engine inter-turbine transition duct having radially spaced apart conical inner and outer duct walls extending axially between a duct inlet and a duct outlet. A conical plasma generator produces a conical plasma along the outer duct wall. An exemplary embodiment of the conical plasma generator is mounted to the outer duct wall and including radially inner and outer electrodes separated by a dielectric material. The dielectric material is disposed within a conical groove in a radially inwardly facing surface of the outer duct wall. An AC power supply is connected to the electrodes to supply a high voltage AC potential to the electrodes.Type: ApplicationFiled: October 13, 2006Publication date: October 7, 2010Inventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Scott Michael Carson
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Patent number: 7806653Abstract: A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.Type: GrantFiled: December 22, 2006Date of Patent: October 5, 2010Assignee: General Electric CompanyInventors: Scott Andrew Burton, Chander Prakash, Joseph Machnaim, David Glenn Cherry, Robert John Beacock, Ching-Pang Lee, Scott Michael Carson
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Patent number: 7758306Abstract: A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.Type: GrantFiled: December 22, 2006Date of Patent: July 20, 2010Assignee: General Electric CompanyInventors: Scott Andrew Burton, Chander Prakash, Joseph Machnaim, David Glenn Cherry, Robert John Beacock, Ching-Pang Lee, Scott Michael Carson
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Patent number: 7513102Abstract: A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation. First stage stator vanes in the low pressure turbine have camber and twist for carrying swirl directly between the rotor blades of the high and low pressure turbines.Type: GrantFiled: June 6, 2005Date of Patent: April 7, 2009Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Scott Michael Carson, Robert Joseph Orlando, Ching-Pang Lee, David Glenn Cherry
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Patent number: 7510371Abstract: A turbine nozzle includes a row of vanes joined to radially outwardly inclined outer and inner bands. Each vane has camber and an acute twist angle for importing swirl in combustion gases discharged at trailing edges thereof. The trailing edges are tilted forwardly from the inner band to the outer band for increasing aerodynamic efficiency.Type: GrantFiled: June 6, 2005Date of Patent: March 31, 2009Assignee: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz, Ching-Pang Lee, David Glenn Cherry, Robert John Beacock, William Larson Clifford, Scott Michael Carson
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Publication number: 20080152505Abstract: A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.Type: ApplicationFiled: December 22, 2006Publication date: June 26, 2008Inventors: Scott Andrew Burton, Chander Prakash, Joseph Machnaim, David Glenn Cherry, Robert John Beacock, Ching-Pang Lee, Scott Michael Carson
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Publication number: 20080148564Abstract: A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.Type: ApplicationFiled: December 22, 2006Publication date: June 26, 2008Inventors: Scott Andrew Burton, Chander Prakash, Joseph Machnaim, David Glenn Cherry, Robert John Beacock, Ching-Pang Lee, Scott Michael Carson
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Publication number: 20080089775Abstract: A gas turbine engine plasma blade tip clearance control system includes an annular shroud surrounding rotatable blade tips and an annular plasma generator spaced radially outwardly and apart from the blade tips. An exemplary embodiment of the annular plasma generator is mounted to the annular shroud and includes radially inner and outer electrodes separated by a dielectric material disposed within an annular groove in a radially inwardly facing surface of the annular shroud. The plasma generator is operable for producing an annular plasma between the annular shroud and blade tips and an effective clearance produced by the annular plasma between the annular shroud and blade tips that is smaller than a clearance between the annular shroud and blade tips.Type: ApplicationFiled: October 13, 2006Publication date: April 17, 2008Inventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Scott Michael Carson
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Patent number: 7249928Abstract: A turbine nozzle for a gas turbine engine includes a nozzle segment having an airfoil-shaped vane with a root, a tip, a leading edge, a trailing edge and opposed curved pressure and suction sides. An arcuate inner band segment is attached to the root of the vane. The inner band segment includes an inner flowpath surface bounded at forward and aft ends thereof by a forward-facing surface and an aft-facing surface, respectively. A convex curved blended corner is formed between the inner flowpath surface and the aft-facing surface.Type: GrantFiled: April 1, 2005Date of Patent: July 31, 2007Assignee: General Electric CompanyInventors: Kevin Samuel Klasing, Scott Michael Carson
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Patent number: 7134842Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a bulge adjoining the pressure side adjacent the leading edge, and a bowl adjoining the suction side aft of the leading edge.Type: GrantFiled: December 24, 2004Date of Patent: November 14, 2006Assignee: General Electric CompanyInventors: Anna Tam, Ching-Pang Lee, Kevin Richard Kirtley, Ronald Scott Bunker, Scott Henry Lamson, Scott Michael Carson