Patents by Inventor Dilip Prasad
Dilip Prasad 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: 9017037Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.Type: GrantFiled: January 24, 2012Date of Patent: April 28, 2015Assignee: United Technologies CorporationInventors: Constantine Baltas, Dilip Prasad, Edward J. Gallagher
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Patent number: 9010495Abstract: An elevator sheave (20) includes a belt guiding surface (26) having a surface profile along at least a portion of the belt guiding surface. The surface profile preferably is defined by an nth order polynomial equation where n is a number greater than 2. In one example, the reference point (40) is a central point along the width of the belt guiding surface (26). In one example, a central portion (42) of the surface profile preferably is aligned to be generally parallel with the central axis (34) of the sheave body. Some examples have curvilinear side portions (44,46) between the central portion (42) and the edges (28,30) of the sheave. Other examples also include second side portions (48,50) that have linear profiles.Type: GrantFiled: August 4, 2004Date of Patent: April 21, 2015Assignee: Otis Elevator CompanyInventors: Dilip Prasad, Brice N. Cassenti, Pedro S. Baranda, William Veronesi, William C. Perron, Ary O. Mello, Jr., Paul A. Stucky, John T. Pitts, John P. Wesson, Mark S. Thompson
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Patent number: 8997494Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.Type: GrantFiled: October 31, 2012Date of Patent: April 7, 2015Assignee: United Technologies CorporationInventors: Sue-Li Chuang, Yuan Dong, Sanjay S. Hingorani, Dilip Prasad
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Publication number: 20130189117Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.Type: ApplicationFiled: January 24, 2012Publication date: July 25, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Constantine Baltas, Dilip Prasad, Edward J. Gallagher
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Publication number: 20130052027Abstract: A hydrofoil includes a hydrofoil body that extends between a base and a tip, a leading end and a trailing end, and a suction side and a pressure side that define a thickness there between. The hydrofoil body includes a discontinuous slope on at least one of the suction side or the pressure side. The discontinuous slope extends in a span-wise direction between the base and the tip such that the discontinuous slope decreases the thickness of the hydrofoil body from the leading end to the trailing end.Type: ApplicationFiled: August 23, 2011Publication date: February 28, 2013Inventor: Dilip Prasad
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Patent number: 8286654Abstract: A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.Type: GrantFiled: May 7, 2010Date of Patent: October 16, 2012Assignee: United Technologies CorporationInventors: Dilip Prasad, Jinzhang Feng, Jayant S. Sabnis
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Patent number: 7861823Abstract: A duct 26 has circumferentially distributed features capable of scattering acoustic energy associated with fluid dynamic shocks 34 extending in a shock orientation direction D. Each feature is oriented, over at least a portion of its length, substantially perpendicular to the shock orientation direction. The features may be splices 42 used to connect segments of an acoustic liner 30, partitions 56 in a stability enhancing casing treatment 32, or other features capable of scattering acoustic energy associated with shocks.Type: GrantFiled: November 4, 2005Date of Patent: January 4, 2011Assignee: United Technologies CorporationInventors: Dilip Prasad, Anil Prasad, John Michael Feiereisen
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Publication number: 20100215479Abstract: A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.Type: ApplicationFiled: May 7, 2010Publication date: August 26, 2010Inventors: Dilip Prasad, Jinzhang Feng, Jayant S. Sabnis
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Patent number: 7739865Abstract: A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.Type: GrantFiled: October 27, 2006Date of Patent: June 22, 2010Assignee: United Technologies CorporationInventors: Dilip Prasad, Jinzhang Feng, Jayant S. Sabnis
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Publication number: 20070252121Abstract: An elevator sheave (20) includes a belt guiding surface (26) having a surface profile along at least a portion of the belt guiding surface. The surface profile preferably is defined by an nth order polynomial equation where n is a number greater than 2. In one example, the reference point (40) is a central point along the width of the belt guiding surface (26). In one example, a central portion (42) of the surface profile preferably is aligned to be generally parallel with the central axis (34) of the sheave body. Some examples have curvilinear side portions (44, 46) between the central portion (42) and the edges (28, 30) of the sheave. Other examples also include second side portions (48, 50) that have linear profiles.Type: ApplicationFiled: August 4, 2004Publication date: November 1, 2007Inventors: Dilip Prasad, Brice Cassenti, Pedro Baranda, William Veronesi, William Perron, Ary Mello, Paul Stucky, John Pitts, John Wesson, Mark Thompson
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Publication number: 20070163229Abstract: A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.Type: ApplicationFiled: October 27, 2006Publication date: July 19, 2007Applicant: United Technologies CorporationInventors: Dilip Prasad, Jinzhang Feng, Jayant Sabnis
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Publication number: 20070102234Abstract: A duct 26 has circumferentially distributed features capable of scattering acoustic energy associated with fluid dynamic shocks 34 extending in a shock orientation direction D. Each feature is oriented, over at least a portion of its length, substantially perpendicular to the shock orientation direction. The features may be splices 42 used to connect segments of an acoustic liner 30, partitions 56 in a stability enhancing casing treatment 32, or other features capable of scattering acoustic energy associated with shocks.Type: ApplicationFiled: November 4, 2005Publication date: May 10, 2007Inventors: Dilip Prasad, Anil Prasad, John Feiereisen
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Publication number: 20060137352Abstract: An augmentor liner is provided that includes an annulus disposed between a first wall and a second wall, and a plurality of baffles. The first wall is disposed radially inside of the second wall. The plurality of baffles extend heightwise between the first wall and the second wall, and are circumferentially spaced apart from one another by a distance. The distance between adjacent baffles is such that an acoustic wave entering an annulus compartment will travel between the first wall and second wall in a direction having a radial component that is substantially greater than a circumferential component. The baffle spacing may alternatively be described as being such that the circumferential component of the acoustic wave is substantially damped and therefore does not materially contribute to undesirable screech.Type: ApplicationFiled: December 29, 2004Publication date: June 29, 2006Applicant: United Technologies CorporationInventors: Dilip Prasad, Jinzhang Feng, William Proscia
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Patent number: 7018172Abstract: In accordance with the present invention, an aircraft engine is provided with a component which helps reduce the noise generated by the engine. The component has a first aerodynamic surface, a second aerodynamic surface, and a system for reducing noise without altering a pressure differential between the first aerodynamic surface and the second aerodynamic surface.Type: GrantFiled: December 22, 2003Date of Patent: March 28, 2006Assignee: United Technologies CorporationInventors: Dilip Prasad, Bruce L. Morin, Wesley K. Lord, Douglas C. Mathews
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Publication number: 20050274103Abstract: A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.Type: ApplicationFiled: June 10, 2004Publication date: December 15, 2005Applicant: United Technologies CorporationInventors: Dilip Prasad, Jinzhang Feng, Jayant Sabnis
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Publication number: 20050135924Abstract: In accordance with the present invention, an aircraft engine is provided with a component which helps reduce the noise generated by the engine. The component has a first aerodynamic surface, a second aerodynamic surface, and a system for reducing noise without altering a pressure differential between the first aerodynamic surface and the second aerodynamic surface.Type: ApplicationFiled: December 22, 2003Publication date: June 23, 2005Inventors: Dilip Prasad, Bruce Morin, Wesley Lord, Douglas Mathews