Patents by Inventor Chander Prakash
Chander Prakash 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).
-
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
-
Patent number: 7794201Abstract: A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.Type: GrantFiled: December 22, 2006Date of Patent: September 14, 2010Assignee: General Electric CompanyInventors: Scott Andrew Burton, Chander Prakash, Joseph Machnaim, David Glenn Cherry, Robert John Beacock, Ching-Pang Lee, Craig Miller Kuhne
-
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
-
Publication number: 20080152504Abstract: A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.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, Craig Miller Kuhne
-
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
-
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
-
Patent number: 7290986Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.Type: GrantFiled: September 9, 2005Date of Patent: November 6, 2007Assignee: General Electric CompanyInventors: Mark Edward Stegemiller, Chander Prakash, Leslie Eugene Leeke, Kevin Samuel Klasing, Ching-Pang Lee
-
Patent number: 7281894Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil. At least a portion of the pressure-side tip wall is recessed from the pressure sidewall to define an outwardly facing tip shelf, such that the pressure-side tip wall and the tip shelf define a trough therebetween.Type: GrantFiled: September 9, 2005Date of Patent: October 16, 2007Assignee: General Electric CompanyInventors: Ching-Pang Lee, Chander Prakash
-
Publication number: 20070059173Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil. At least a portion of the pressure-side tip wall is recessed from the pressure sidewall to define an outwardly facing tip shelf, such that the pressure-side tip wall and the tip shelf define a trough therebetween.Type: ApplicationFiled: September 9, 2005Publication date: March 15, 2007Applicant: GENERAL ELECTRIC COMPANYInventors: Ching-Pang Lee, Chander Prakash
-
Publication number: 20070059182Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.Type: ApplicationFiled: September 9, 2005Publication date: March 15, 2007Applicant: GENERAL ELECTRIC COMPANYInventors: Mark Stegemiller, Chander Prakash, Leslie Leeke, Kevin Klasing, Ching-Pang Lee
-
Patent number: 6984103Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.Type: GrantFiled: November 20, 2003Date of Patent: January 10, 2006Assignee: General Electric CompanyInventors: Ching-Pang Lee, Steven Robert Brassfield, Chander Prakash
-
Patent number: 6981840Abstract: A turbine airfoil includes pressure and suction sidewalls extending in chord between leading and trailing edges and in span between a root and a tip. A septum is spaced between the sidewalls to define two cooling circuits on opposite sides of the septum which converge between the leading and trailing edges. An array of pins extends inwardly from the pressure sidewall at a discharge end of the circuits, and the pins decrease in length to conform with the converging circuit.Type: GrantFiled: October 24, 2003Date of Patent: January 3, 2006Assignee: General Electric CompanyInventors: Ching-Pang Lee, Ronald Scott Bunker, Chander Prakash
-
Publication number: 20050169752Abstract: A turbine airfoil includes pressure and suction sidewalls extending in chord between leading and trailing edges and in span between a root and a tip. A septum is spaced between the sidewalls to define two cooling circuits on opposite sides of the septum which converge between the leading and trailing edges. An array of pins extends inwardly from the pressure sidewall at a discharge end of the circuits, and the pins decrease in length to conform with the converging circuit.Type: ApplicationFiled: October 24, 2003Publication date: August 4, 2005Inventors: Ching-Pang Lee, Ronald Bunker, Chander Prakash
-
Publication number: 20050111977Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.Type: ApplicationFiled: November 20, 2003Publication date: May 26, 2005Inventors: Ching-Pang Lee, Steven Brassfield, Chander Prakash
-
Publication number: 20040225025Abstract: Provided are curable compositions for the preparation of displays. The compositions are particularly suitable as adhesives, sealants, and/or encapsulants for displays. Compositions according to the invention include those having an epoxy resin and a hydroxy-functional compound, wherein the compositions provide good barrier properties after cure.Type: ApplicationFiled: February 2, 2004Publication date: November 11, 2004Inventors: Michael G. Sullivan, Chander Prakash Chawla
-
Patent number: 6790005Abstract: A gas turbine engine blade includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The pressure sidewall includes an inclined tip rib offset therein by a ramp defining a tip notch having compound inclinations.Type: GrantFiled: December 30, 2002Date of Patent: September 14, 2004Assignee: General Electric CompanyInventors: Ching-Pang Lee, David Glenn Cherry, Chander Prakash, Aspi Rustom Wadia
-
Publication number: 20040126236Abstract: A gas turbine engine blade includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The pressure sidewall includes an inclined tip rib offset therein by a ramp defining a tip notch having compound inclinations.Type: ApplicationFiled: December 30, 2002Publication date: July 1, 2004Inventors: Ching-Pang Lee, David Glenn Cherry, Chander Prakash, Aspi Rustom Wadia
-
Publication number: 20040013515Abstract: A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross.Type: ApplicationFiled: July 16, 2002Publication date: January 22, 2004Inventors: David Glenn Cherry, Ching-Pang Lee, Chander Prakash, Aspi Rustom Wadia, Brian David Keith, Steven Robert Brassfield
-
Patent number: 6672829Abstract: A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross.Type: GrantFiled: July 16, 2002Date of Patent: January 6, 2004Assignee: General Electric CompanyInventors: David Glenn Cherry, Ching-Pang Lee, Chander Prakash, Aspi Rustom Wadia, Brian David Keith, Steven Robert Brassfield
-
Patent number: 6422821Abstract: A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.Type: GrantFiled: January 9, 2001Date of Patent: July 23, 2002Assignee: General Electric CompanyInventors: Ching-Pang Lee, Chander Prakash, Monty Lee Shelton, John Howard Starkweather, Hardev Singh, Gerard Anthony Rinck