Patents by Inventor Shantanu P. Mhetras
Shantanu P. Mhetras 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: 20240102394Abstract: A ring segment for a gas turbine engine includes a forward mate face with respect to a circumferential flow component of a working fluid of the gas turbine engine, an aft mate face opposite to the forward mate face, an arcuate body extending between the forward mate face and the aft mate face, the arcuate body having a first surface facing to the working fluid and a second surface opposite to the first surface. The first surface includes an arcuate surface extending from the aft mate face toward the forward mate face, the arcuate surface having an arcuate cross section taken in a section plane that is normal to a central axis of the gas turbine engine, and a chamfered surface extending from the forward mate face toward the aft mate face, the chamfered surface having a non-arcuate cross section taken in the section plane.Type: ApplicationFiled: August 25, 2023Publication date: March 28, 2024Inventors: Atin Sharma, Jesus Velez-Quinones, Shantanu P. Mhetras, Patrick M. Sedillo
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Publication number: 20240035386Abstract: A turbine blade includes a blade platform, a blade airfoil that extends from the blade platform toward a blade tip, the blade airfoil having a pressure side wall and a suction side wall joined at a blade leading edge and a blade trailing edge, a tip cap surface defined at an end of the blade airfoil facing the blade tip, a squealer tip wall that extends along a portion of the pressure side wall and a portion of the suction side wall from the tip cap surface to the blade tip and from the blade leading edge toward the blade trailing edge, and a chamfered surface formed as a part of the squealer tip wall at a region that is adjacent to the blade trailing edge.Type: ApplicationFiled: June 20, 2023Publication date: February 1, 2024Inventors: Nan Jiang, Shantanu P. Mhetras, Stephen Williamson, John Harrington
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Patent number: 9062557Abstract: A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).Type: GrantFiled: September 7, 2011Date of Patent: June 23, 2015Assignee: Siemens AktiengesellschaftInventors: Kok-Mun Tham, Ching-Pang Lee, Abdullatif M. Chehab, Gm Salam Azad, Shantanu P. Mhetras, Manjit Shivanand, Vincent P. Laurello, Christopher Rawlings
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Patent number: 8961135Abstract: In a gas turbine engine, adjoining pairs of airfoil structures include airfoils mounted to respective platforms. The platforms have side edges defining matefaces that form a mateface gap extending from an upstream edge of the platforms to a downstream edge of the platforms. A flow field of working gas adjacent to endwalls of the platform comprises streamlines extending generally transverse to the axial direction from a first airfoil toward an adjacent second airfoil. To achieve improved aerodynamic performance, the mateface gap has portions oriented transverse to the streamlines and oriented aligned with the streamlines. A step in elevation of the side edges at the transverse portion can include injected cooling flow in a direction that enhances attachment of the flow at a downstream side.Type: GrantFiled: June 29, 2011Date of Patent: February 24, 2015Assignee: Siemens Energy, Inc.Inventors: Alexander R. Beeck, Shantanu P. Mhetras
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Patent number: 8684691Abstract: A squealer tip formed from a pressure side rib and a suction side rib extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure and suction side ribs may include chamfered leading edges with film cooling holes having exhaust outlets positioned therein. The film cooling holes may be configured to be diffusion cooling holes with one or more tapered sections for reducing the velocity of cooling fluids and increasing the size of the convective surfaces.Type: GrantFiled: May 3, 2011Date of Patent: April 1, 2014Assignee: Siemens Energy, Inc.Inventors: Ching-Pang Lee, Shantanu P. Mhetras, Glenn E. Brown
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Publication number: 20130058756Abstract: A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).Type: ApplicationFiled: September 7, 2011Publication date: March 7, 2013Inventors: Kok-Mun THAM, Ching-Pang LEE, Abdullatif M. CHEHAB, Gm Salam AZAD, Shantanu P. MHETRAS, Manjit SHIVANAND, Vincent P. LAURELLO, Christopher RAWLINGS
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Publication number: 20130004315Abstract: In a gas turbine engine, adjoining pairs of airfoil structures include airfoils mounted to respective platforms. The platforms have side edges defining matefaces that form a mateface gap extending from an upstream edge of the platforms to a downstream edge of the platforms. A flow field of working gas adjacent to endwalls of the platform comprises streamlines extending generally transverse to the axial direction from a first airfoil toward an adjacent second airfoil. To achieve improved aerodynamic performance, the mateface gap has portions oriented transverse to the streamlines and oriented aligned with the streamlines. A step in elevation of the side edges at the transverse portion can include injected cooling flow in a direction that enhances attachment of the flow at a downstream side.Type: ApplicationFiled: June 29, 2011Publication date: January 3, 2013Inventors: Alexander R. Beeck, Shantanu P. Mhetras
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Publication number: 20120282108Abstract: A squealer tip formed from a pressure side rib and a suction side rib extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure and suction side ribs may include chamfered leading edges with film cooling holes having exhaust outlets positioned therein. The film cooling holes may be configured to be diffusion cooling holes with one or more tapered sections for reducing the velocity of cooling fluids and increasing the size of the convective surfaces.Type: ApplicationFiled: May 3, 2011Publication date: November 8, 2012Inventors: Ching-Pang Lee, Shantanu P. Mhetras, Glenn E. Brown
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Patent number: 8262357Abstract: The tip cooling arrangement of the present application reduces large cooling flow requirements which can compromise turbine performance. The tip cooling arrangement of the present application provides convective cooling of a turbine blade tip end, whether a flat tip or a squealer, by extending holes that provide fluid for film cooling the tip end. The holes are thus lengthened and extend from the relatively cooler suction side of the blade to the pressure side of the blade in close proximity to the floor of the tip end.Type: GrantFiled: May 15, 2009Date of Patent: September 11, 2012Assignee: Siemens Energy, Inc.Inventor: Shantanu P. Mhetras
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Publication number: 20120183389Abstract: A sealing system for a rotor assembly in a gas turbine engine is disclosed. The sealing system may include a seal formed from a side block and an upper seal that seals a gap between a radially outward extending first rotor supply channel in a rotor assembly terminating at an inlet of an axially extending second rotor supply channel that is in fluid communication with an internal blade cooling system of a turbine blade. The seal may include components that enhance the flow of cooling fluids over conventional configurations. In another embodiment, the sealing system may include an integrated sealing block configured to seal a gap between adjacent turbine blades at an intersection between the first and second rotor supply channels. The integrated sealing block may be formed from a radially inward extending leg and central body.Type: ApplicationFiled: January 13, 2011Publication date: July 19, 2012Inventors: Shantanu P. Mhetras, Manjit Shivanand, Abdullatif M. Chehab, Ching-Pang Lee
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Publication number: 20100290921Abstract: The tip cooling arrangement of the present application reduces large cooling flow requirements which can compromise turbine performance. The tip cooling arrangement of the present application provides convective cooling of a turbine blade tip end, whether a flat tip or a squealer, by extending holes that provide fluid for film cooling the tip end. The holes are thus lengthened and extend from the relatively cooler suction side of the blade to the pressure side of the blade in close proximity to the floor of the tip end.Type: ApplicationFiled: May 15, 2009Publication date: November 18, 2010Inventor: Shantanu P. Mhetras
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Publication number: 20100196139Abstract: A sealing system is applied to the interface between a stator and a rotor in a turbine engine to minimize fluid leakage across the interface. One interface can be defined between portions of neighboring rotor disks and a stator. The sealing system includes one or more rows of flow guides, such as airfoils, provided on the rotor disk near the upstream end of the interface. These flow guides can impart tangential velocity on the leakage flow. One or more undulating seal structures can be connected to the stator downstream of the flow guides. These undulating seals can have a periodic waveform conformation. The undulating seals can create unsteadiness in the flow and recirculation of the leakage flow, which causes losses. The sealing system can also include other types of seals, such as labyrinth seals and brush seals, to further create a tortuous path for any leakage flow.Type: ApplicationFiled: February 2, 2009Publication date: August 5, 2010Inventors: Alexander R. Beeck, Shantanu P. Mhetras