Patents by Inventor Aspi Rustom Wadia
Aspi Rustom Wadia 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: 20100170224Abstract: A booster system is disclosed, comprising a first rotor stage having a plurality of first rotor blades spaced circumferentially around a rotor hub with a longitudinal axis and having a first pitch-line radius extending from the longitudinal axis, a last rotor stage located axially aft from the first rotor stage, the last rotor stage comprising a plurality of last rotor blades spaced circumferentially around the longitudinal axis and having a second pitch-line radius extending from the longitudinal axis, and a gooseneck duct located axially aft from the last rotor stage and capable of receiving an airflow, the gooseneck duct comprising an inlet end and an exit end located at a distance axially aft from the inlet end and having at least one plasma actuator mounted in the gooseneck duct.Type: ApplicationFiled: January 8, 2009Publication date: July 8, 2010Inventors: DAVID SCOTT CLARK, ASPI RUSTOM WADIA, CHING PANG LEE, PETER JOHN WOOD
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Publication number: 20100158696Abstract: A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.Type: ApplicationFiled: December 24, 2008Publication date: June 24, 2010Inventors: Vidhu Shekhar Pandey, Ching-Pang Lee, Jan Christopher Schilling, Aspi Rustom Wadia, Brian David Keith, Jeffrey Donald Clements
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Patent number: 7736123Abstract: A trailing edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction, one or more spanwise extending plasma generators in a trailing edge region around a trailing edge of the airfoil. The plasma generators may be mounted on an outer wall of the airfoil with first and second pluralities of the plasma generators on pressure and suction sides of the airfoil respectively. The plasma generators may include inner and outer electrodes separated by a dielectric material disposed within a grooves in an outer hot surface of the outer wall of the airfoil. The plasma generators may be located at an aft end of the airfoil and the inner electrodes flush with the trailing edge base. A method for operating the system includes energizing one or more of plasma generators in steady state or unsteady modes.Type: GrantFiled: December 15, 2006Date of Patent: June 15, 2010Assignee: General Electric CompanyInventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Je-Chin Han
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Publication number: 20100129203Abstract: A micro-electromechanical system (MEMS) dielectric barrier discharge (DBD) based aerodynamic actuator is configured to modify a shockwave boundary layer interaction and limit incident boundary layer growth caused by a reflected shockwave.Type: ApplicationFiled: November 26, 2008Publication date: May 27, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Robert Carl Murray, Anurag Gupta, Seyed Gholamali Saddoughi, Aspi Rustom Wadia
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Patent number: 7695241Abstract: An downstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator located downstream of the film cooling apertures is used for producing a plasma extending downstream over the film cooling apertures. Each plasma generator includes inner and outer electrodes separated by a dielectric material disposed within a groove in the outer hot surface. The wall may be part of a hollow airfoil or an annular combustor or exhaust liner. A method for operating the downstream plasma boundary layer shielding system includes forming a plasma extending in the downstream direction over the film cooling apertures along the outer hot surface of the wall. The method may further include operating the plasma generator in steady state or unsteady modes.Type: GrantFiled: November 30, 2006Date of Patent: April 13, 2010Assignee: General Electric CompanyInventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Je-Chin Han
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Patent number: 7695243Abstract: A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil.Type: GrantFiled: July 27, 2006Date of Patent: April 13, 2010Assignee: General Electric CompanyInventors: Ching-Pang Lee, Tingfan Pang, Brian Alan Norton, Jan Christopher Schilling, Aspi Rustom Wadia
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Publication number: 20100047060Abstract: A gas turbine engine is disclosed, comprising a compressor having a circumferential row of blades, a casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one plasma generator located on the casing. The plasma generator comprises a first electrode and a second electrode separated by a dielectric material. The gas turbine engine further comprises an engine control system which controls the operation of the plasma generator such that the stable operating range of the compressor is increased.Type: ApplicationFiled: December 28, 2007Publication date: February 25, 2010Inventors: Aspi Rustom Wadia, David Scott Clark, Ching-Pang Lee, Andrew Breeze-Stringfellow, Gregory Scott McNulty
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Publication number: 20100047055Abstract: A compression system is disclosed, the compression system comprising a rotor having a plurality of blades arranged around a centerline axis, each blade having a blade airfoil and a blade tip, and at least one plasma actuator located on a blade. Exemplary embodiments of a detection system for detecting an instability in a compression system rotor and a mitigation system comprising at least one plasma actuator mounted on a blade to facilitate the improvement of the stability of the rotor are disclosed.Type: ApplicationFiled: December 28, 2007Publication date: February 25, 2010Inventors: Aspi Rustom Wadia, Seyed Gholamali Saddoughi, Clark Leonard Applegate
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Patent number: 7628585Abstract: A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading edge region near and around a leading edge of the airfoil and near the fillet. The plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. The plasma generators may be mounted on an outer wall of the airfoil with a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. A method for operating the system includes energizing one or more plasma generators to form the plasma in steady state or unsteady modes.Type: GrantFiled: December 15, 2006Date of Patent: December 8, 2009Assignee: General Electric CompanyInventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Je-Chin Han
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Patent number: 7588413Abstract: An upstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator located upstream of the film cooling apertures is used for producing a plasma extending downstream over the film cooling apertures. Each plasma generator includes inner and outer electrodes separated by a dielectric material disposed within a groove in the outer hot surface. The wall may be part of a hollow airfoil or an annular combustor or exhaust liner. A method for operating the upstream plasma boundary layer shielding system includes forming a plasma extending in the downstream direction over the film cooling apertures along the outer hot surface of the wall. The method may further include operating the plasma generator in steady state or unsteady modes.Type: GrantFiled: November 30, 2006Date of Patent: September 15, 2009Assignee: General Electric CompanyInventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Je-Chin Han
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Publication number: 20090169356Abstract: A compression system is disclosed, the compression system comprising a rotor having a circumferential row of blades each blade having a blade tip, a static component located radially outwardly and apart from the blade tips, a detection system for detecting an instability in the rotor during the operation of the rotor, and a mitigation system that facilitates the improvement of the stability of the rotor when an instability is detected by the detection system. A gas turbine engine comprising a detection system for detecting an instability during the operation of the fan section and a mitigation system that facilitates the improvement of the stability of the fan section is disclosed.Type: ApplicationFiled: December 28, 2007Publication date: July 2, 2009Inventors: Aspi Rustom Wadia, Seyed Gholamali Saddoughi, Clark Leonard Applegate
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Publication number: 20090169362Abstract: An instability mitigation system is disclosed, comprising a detection system for detecting an onset of an instability in a rotor during the operation of the rotor, a mitigation system that facilitates the improvement of the stability of the rotor when the onset of instability is detected by the detection system, a control system for controlling the detection system and the mitigation system.Type: ApplicationFiled: December 28, 2007Publication date: July 2, 2009Inventors: Aspi Rustom Wadia, Seyed Gholamali Saddoughi, Clark Leonard Applegate
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Publication number: 20090169367Abstract: An instability mitigation system is disclosed, comprising a stator stage located axially proximate to a rotor, the stator stage having a row of a plurality of stator vanes arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on the stator vane that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed.Type: ApplicationFiled: December 28, 2007Publication date: July 2, 2009Inventors: Aspi Rustom Wadia, Seyed Gholamali Saddoughi, Clark Leonard Applegate
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Publication number: 20090169363Abstract: A compression system is disclosed, the compression system comprising a stator stage having a row of a plurality of stator vanes arranged around a centerline axis, each stator vane having a vane airfoil and at least one plasma actuator located on the stator stage. Exemplary embodiments of a detection system for detecting an instability in a compression system rotor and a mitigation system that facilitates the improvement of the stability of the rotor are disclosed.Type: ApplicationFiled: December 28, 2007Publication date: July 2, 2009Inventors: Aspi Rustom Wadia, Seyed Gholamali Saddoughi, Clark Leonard Applegate
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Publication number: 20090155088Abstract: A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil.Type: ApplicationFiled: July 27, 2006Publication date: June 18, 2009Inventors: Ching-Pang Lee, Tingfan Pang, Brian Alan Norton, Jan Christopher Schilling, Aspi Rustom Wadia
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Patent number: 7476086Abstract: A fan blade includes an airfoil having opposite pressure and suction sides extending in span between a root and tip, and extending in chord between opposite leading and trailing edges. From root toward tip, the airfoil includes increasing stagger and decreasing camber, and increasing chord length to barrel the airfoil along both the leading and trailing edges. The airfoil further includes forward aerodynamic sweep at the tip, and non-forward aerodynamic sweep between the maximum barrel and the root.Type: GrantFiled: August 22, 2005Date of Patent: January 13, 2009Assignee: General Electric CompanyInventors: Aspi Rustom Wadia, Peter Nicholas Szucs, Max Robert Farson, Virginia Louise Wilson, William Joseph Solomon
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Publication number: 20080145233Abstract: A trailing edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction, one or more spanwise extending plasma generators in a trailing edge region around a trailing edge of the airfoil. The plasma generators may be mounted on an outer wall of the airfoil with first and second pluralities of the plasma generators on pressure and suction sides of the airfoil respectively. The plasma generators may include inner and outer electrodes separated by a dielectric material disposed within a grooves in an outer hot surface of the outer wall of the airfoil. The plasma generators may be located at an aft end of the airfoil and the inner electrodes flush with the trailing edge base. A method for operating the system includes energizing one or more of plasma generators in steady state or unsteady modes.Type: ApplicationFiled: December 15, 2006Publication date: June 19, 2008Inventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Je-Chin Han
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Publication number: 20080145210Abstract: A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading edge region near and around a leading edge of the airfoil and near the fillet. The plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. The plasma generators may be mounted on an outer wall of the airfoil with a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. A method for operating the system includes energizing one or more plasma generators to form the plasma in steady state or unsteady modes.Type: ApplicationFiled: December 15, 2006Publication date: June 19, 2008Inventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Je-Chin Han
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Publication number: 20080131265Abstract: An downstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator located downstream of the film cooling apertures is used for producing a plasma extending downstream over the film cooling apertures. Each plasma generator includes inner and outer electrodes separated by a dielectric material disposed within a groove in the outer hot surface. The wall may be part of a hollow airfoil or an annular combustor or exhaust liner. A method for operating the downstream plasma boundary layer shielding system includes forming a plasma extending in the downstream direction over the film cooling apertures along the outer hot surface of the wall. The method may further include operating the plasma generator in steady state or unsteady modes.Type: ApplicationFiled: November 30, 2006Publication date: June 5, 2008Inventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Je-Chin Han
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Publication number: 20080128266Abstract: An upstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator located upstream of the film cooling apertures is used for producing a plasma extending downstream over the film cooling apertures. Each plasma generator includes inner and outer electrodes separated by a dielectric material disposed within a groove in the outer hot surface. The wall may be part of a hollow airfoil or an annular combustor or exhaust liner. A method for operating the upstream plasma boundary layer shielding system includes forming a plasma extending in the downstream direction over the film cooling apertures along the outer hot surface of the wall. The method may further include operating the plasma generator in steady state or unsteady modes.Type: ApplicationFiled: November 30, 2006Publication date: June 5, 2008Inventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Je-Chin Han