Patents by Inventor Atul Kohli
Atul Kohli 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: 20160047251Abstract: A gas turbine engine component has a cooling hole with a metering section. The metering section includes a convex surface and a concave surface, with a first arcuate channel connecting an end of the convex surface and an end of the concave surface. The end of the convex surface and the end of the concave surface define a dimension that is smaller than a diameter of the arcuate channel.Type: ApplicationFiled: July 16, 2015Publication date: February 18, 2016Inventors: Jinquan Xu, Atul Kohli, Dominic J. Mongillo, Glenn Levasseur, Mark F. Zelesky
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Publication number: 20150354365Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.Type: ApplicationFiled: June 2, 2015Publication date: December 10, 2015Inventors: Wolfgang Balzer, Thomas J. Praisner, Atul Kohli, Mark F. Zelesky, Dominic J. Mongillo, JR.
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Publication number: 20150226085Abstract: One exemplary embodiment of this disclosure relates to a component for a gas turbine engine. The component includes a baffle provided in an internal cavity of the component. The baffle includes a wall having an orifice therethrough, and the baffle further includes a lobe extending from the wall and at least partially covering the orifice.Type: ApplicationFiled: February 12, 2015Publication date: August 13, 2015Inventors: Brandon W. Spangler, Atul Kohli
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Patent number: 9022737Abstract: An airfoil has a wall, a cooling channel, a trench, and a plurality of cooling holes. The wall has a leading edge, a trailing edge, a pressure side, a suction side, an outer diameter end, and an inner diameter end to define an interior. The cooling channel extends radially through the interior of the wall between the pressure side and the suction side and along the leading edge. The trench extends radially along an exterior of the wall at the leading edge and is recessed axially into the leading edge to form a back wall. The back wall is contoured to include at least one undulation. The plurality of cooling holes extends through the back wall of the trench to connect the interior of the wall at the cooling channel to the exterior.Type: GrantFiled: August 8, 2011Date of Patent: May 5, 2015Assignee: United Technologies CorporationInventors: Justin D. Piggush, Atul Kohli
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Patent number: 8955576Abstract: A core assembly for a turbine engine blade includes a generally radially extending trunk interconnected to multiple generally axially extending tabs. The tabs are interconnected by a generally radially extending ligament. Multiple generally axially extending protrusions are interconnected to the ligament opposite the trunk. A mold is configured to define an exterior surface of an airfoil. The core is arranged within the mold and is configured such that the tabs and the ligament break through at the exterior surface.Type: GrantFiled: January 15, 2014Date of Patent: February 17, 2015Assignee: United Technologies CorporationInventors: Jason Edward Albert, Atul Kohli, Eric L. Couch
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Publication number: 20140190654Abstract: A core assembly for a turbine engine blade includes a generally radially extending trunk interconnected to multiple generally axially extending tabs. The tabs are interconnected by a generally radially extending ligament. Multiple generally axially extending protrusions are interconnected to the ligament opposite the trunk. A mold is configured to define an exterior surface of an airfoil. The core is arranged within the mold and is configured such that the tabs and the ligament break through at the exterior surface.Type: ApplicationFiled: January 15, 2014Publication date: July 10, 2014Applicant: United Technologies CorporationInventors: Jason Edward Albert, Atul Kohli, Eric L. Couch
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Patent number: 8763402Abstract: A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet.Type: GrantFiled: July 9, 2012Date of Patent: July 1, 2014Assignee: United Technologies CorporationInventors: JinQuan Xu, Mark F. Zelesky, Atul Kohli, Matthew S. Gleiner
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Patent number: 8733111Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.Type: GrantFiled: July 9, 2012Date of Patent: May 27, 2014Assignee: United Technologies CorporationInventors: Matthew S. Gleiner, Atul Kohli, Mark F. Zelesky
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Patent number: 8695683Abstract: An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.Type: GrantFiled: June 14, 2011Date of Patent: April 15, 2014Assignee: United Technologies CorporationInventors: Jason Edward Albert, Atul Kohli, Eric L. Couch
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Patent number: 8689568Abstract: A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.Type: GrantFiled: July 9, 2012Date of Patent: April 8, 2014Assignee: United Technologies CorporationInventors: Atul Kohli, Matthew S. Gleiner, Mark F. Zelesky, JinQuan Xu
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Patent number: 8683813Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet at the first wall surface, an outlet at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally from the metering section, a third lobe adjacent the second lobe and diverging longitudinally and laterally from the metering section, and a transition region having an end adjacent the outlet and a portion that extends between the lobes and the outlet. The first and third lobes each include a curved outer portion.Type: GrantFiled: July 9, 2012Date of Patent: April 1, 2014Assignee: United Technologies CorporationInventors: JinQuan Xu, Mark F. Zelesky, Atul Kohli, Matthew S. Gleiner
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Patent number: 8584470Abstract: A gas turbine engine component includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section positioned between the inlet and the outlet. The diffusing section includes a first lobe, a second lobe adjacent the first lobe and a third lobe adjacent the second lobe. The first lobe and the second lobe meet at a first ridge and the second lobe and the third lobe meet at a second ridge.Type: GrantFiled: July 9, 2012Date of Patent: November 19, 2013Assignee: United Technologies CorporationInventors: Mark F. Zelesky, Atul Kohli, Scott D. Lewis
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Publication number: 20130205786Abstract: A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.Type: ApplicationFiled: July 9, 2012Publication date: August 15, 2013Applicant: United Technologies CorporationInventors: Atul Kohli, Matthew S. Gleiner, Mark F. Zelesky, JinQuan Xu
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Publication number: 20130205790Abstract: A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet.Type: ApplicationFiled: July 9, 2012Publication date: August 15, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: JinQuan Xu, Mark F. Zelesky, Atul Kohli, Matthew S. Gleiner
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Publication number: 20130209269Abstract: A component for a gas turbine engine includes a wall and a cooling hole extending through the wall. The wall has a first surface and a second surface. The cooling hole includes a metering section extending downstream from an inlet in the first surface of the wall and a diffusion section extending from the metering section to an outlet in the second surface of the wall. The diffusion section includes a first plurality of lobes diverging longitudinally and laterally from the metering section on a first side of a centerline axis of the cooling hole and a second plurality of lobes diverging longitudinally and laterally from the metering section on a second side of the centerline axis.Type: ApplicationFiled: July 9, 2012Publication date: August 15, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Matthew S. Gleiner, Mark F. Zelesky, Atul Kohli
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Publication number: 20130205801Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet at the first wall surface, an outlet at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally from the metering section, a third lobe adjacent the second lobe and diverging longitudinally and laterally from the metering section, and a transition region having an end adjacent the outlet and a portion that extends between the lobes and the outlet. The first and third lobes each include a curved outer portion.Type: ApplicationFiled: July 9, 2012Publication date: August 15, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: JinQuan Xu, Mark F. Zelesky, Atul Kohli, Matthew S. Gleiner
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Publication number: 20130205787Abstract: A gas turbine engine component includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section positioned between the inlet and the outlet. The diffusing section includes a first lobe, a second lobe adjacent the first lobe and a third lobe adjacent the second lobe. The first lobe and the second lobe meet at a first ridge and the second lobe and the third lobe meet at a second ridge.Type: ApplicationFiled: July 9, 2012Publication date: August 15, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Mark F. Zelesky, Atul Kohli, Scott D. Lewis
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Publication number: 20130205792Abstract: A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.Type: ApplicationFiled: July 9, 2012Publication date: August 15, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Matthew S. Gleiner, Atul Kohli, Mark F. Zelesky
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Publication number: 20130039777Abstract: A airfoil comprises a wall, a cooling channel, a trench and a plurality of leading edge cooling holes. The wall has a leading edge, a trailing edge, a pressure side, a suction side, an outer diameter end and an inner diameter end to define an interior. The cooling channel extends radially through the interior of the wall between the pressure side and the suction side and along the leading edge. The trench extends radially along an exterior of the wall at the leading edge and is recessed axially into the leading edge to form a back wall. The back wall is contoured to include at least one undulation. The plurality of leading edge cooling holes extends through the back wall of the trench to connect the interior of the wall at the cooling channel to the exterior.Type: ApplicationFiled: August 8, 2011Publication date: February 14, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Justin D. Piggush, Atul Kohli
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Publication number: 20120027619Abstract: An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.Type: ApplicationFiled: June 14, 2011Publication date: February 2, 2012Inventors: Jason Edward Albert, Atul Kohli, Eric L. Couch