Patents by Inventor Aspi R. Wadia
Aspi R. 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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Patent number: 7270519Abstract: An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip, a first side wall that extends in radial span between an airfoil root and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall connected to the first side wall at the leading edge and the trailing edge, wherein the second side wall extends in radial span between the airfoil root and the tip, such that the second side wall defines a second side of the airfoil. The airfoil also includes a rib extending outwardly from at least one of the first side wall and the second side wall, wherein the rib is configured to reduce airflow spillage past the tip.Type: GrantFiled: November 12, 2002Date of Patent: September 18, 2007Assignee: General Electric CompanyInventors: Aspi R. Wadia, Rolf Hetico, Robert Bruce Dickman, Hsin-Yi Yen, Peter Wood
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Patent number: 6779979Abstract: An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip, a first side wall that extends in radial span between an airfoil root and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall connected to the first side wall at the leading edge and the trailing edge, wherein the second side wall extends in radial span between the airfoil root and the tip, such that the second side wall defines a second side of the airfoil. The airfoil also includes a rib that extends outwardly from at least one of the first side wall and the second side wall, such that a natural frequency of chordwise vibration of the airfoil is increased to a frequency that is not present within the gas turbine engine during engine operations.Type: GrantFiled: April 23, 2003Date of Patent: August 24, 2004Assignee: General Electric CompanyInventors: Aspi R. Wadia, Rolf Hetico, Robert Bruce Dickman, Hsin-Yi Yen, Peter Wood
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Publication number: 20040091361Abstract: An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip, a first side wall that extends in radial span between an airfoil root and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall connected to the first side wall at the leading edge and the trailing edge, wherein the second side wall extends in radial span between the airfoil root and the tip, such that the second side wall defines a second side of the airfoil. The airfoil also includes a rib extending outwardly from at least one of the first side wall and the second side wall, wherein the rib is configured to reduce airflow spillage past the tip.Type: ApplicationFiled: November 12, 2002Publication date: May 13, 2004Inventors: Aspi R. Wadia, Rolf Hetico, Robert Bruce Dickman, Hsin-Yi Yen, Peter Wood
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Patent number: 6725645Abstract: A system and method are provided for preventing the formation of ice on or removing ice from an internal surface of a turbofan engine. A splitter region, associated with a booster compressor of the turbofan engine, is identified. The splitter region has surfaces internal to the turbofan engine subject to inlet icing conditions. A resin is molded along a leading edge of the splitter region, and electric coils are installed within the resin to prevent ice build-up on the splitter region or to remove ice from the splitter region during icing conditions.Type: GrantFiled: October 3, 2002Date of Patent: April 27, 2004Assignee: General Electric CompanyInventors: Aspi R. Wadia, Raymond G. Holm
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Publication number: 20040065092Abstract: A system and method are provided for preventing the formation of ice on or removing ice from an internal surface of a turbofan engine. A splitter region, associated with a booster compressor of the turbofan engine, is identified. The splitter region has surfaces internal to the turbofan engine subject to inlet icing conditions. A resin is molded along a leading edge of the splitter region, and electric coils are installed within the resin to prevent ice build-up on the splitter region or to remove ice from the splitter region during icing conditions.Type: ApplicationFiled: October 3, 2002Publication date: April 8, 2004Applicant: General Electric CompanyInventors: Aspi R. Wadia, Raymond G. Holm
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Patent number: 6195983Abstract: A gas turbine engine fan assembly has a plurality of axially swept fan exit guide vanes circumferentially disposed around an axially extending centerline, a plurality of fan frame struts having axially swept strut leading edges and circumferentially disposed around the centerline directly aft of the exit guide vanes, and an axially extending annular gap between the trailing edges of the fan exit guide vanes and the strut leading edges. Each of the fan exit guide vanes has pressure and suction sides, vane trailing edges, and is circumferentially leaned such that the pressure side facing radially inward. Preferably, the axially swept vane trailing edges and the axially swept strut leading edges generally conform to each other in shape. An annular splitter is radially disposed at a spanwise position to split airflow from the fan into fan bypass airflow and core engine airflow and includes a splitter leading edge preferably positioned aft of the strut leading edges.Type: GrantFiled: February 12, 1999Date of Patent: March 6, 2001Assignee: General Electric CompanyInventors: Aspi R. Wadia, Peter N. Szucs, Bruce A. Hemmelgarn
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Patent number: 5725354Abstract: A gas turbine engine fan blade includes a main body having a radially spaced apart root and tip, and axially spaced apart leading and trailing edges. A front shell is fixedly joined to a portion of the body leading edge to collectively define with the body an airfoil having first and second opposite sides extending between the root, tip, shell, and trailing edge for pressurizing air flowing thereover. The shell is hollow to offset toward the trailing edge a collective center of gravity of the airfoil to reduce steady stress at the airfoil leading edge.Type: GrantFiled: November 22, 1996Date of Patent: March 10, 1998Assignee: General Electric CompanyInventors: Aspi R. Wadia, Ian F. Prentice, David W. Crall, Carl C. Koch
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Patent number: 5480284Abstract: A self bleeding rotor blade and method of operation are disclosed for reducing boundary layer thickness for improved performance. The rotor blade includes an outer surface configured for pressurizing air flowable thereover with bleed apertures being disposed therein for bleeding a portion of boundary layer air from the outer surface during operation and thereby decreasing its thickness for improving aerodynamic performance of the blade.Type: GrantFiled: December 20, 1993Date of Patent: January 2, 1996Assignee: General Electric CompanyInventors: Aspi R. Wadia, Mark J. Mielke
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Patent number: 5167489Abstract: A rotor blade includes a root, tip, leading edge, trailing edge, forward surface, and aft surface, and a pitch section disposed equidistantly between the root and tip. The blade has a forward sweep from at least the pitch section to the blade tip relative to incoming streamsurfaces of a fluid flowable over the blade.Type: GrantFiled: April 15, 1991Date of Patent: December 1, 1992Assignee: General Electric CompanyInventors: Aspi R. Wadia, Peter N. Szucs, Padmakar M. Niskode, Pamela A. Battle