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).
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Patent number: 11983569Abstract: One embodiment provides a method, including: producing, for each of a plurality of containers, a resource profile for each thread in each of the plurality of containers; identifying, for each of the plurality of containers and from, at least in part, the resource profiles, container dependencies between threads on a single of the plurality of containers; determining service dependencies between threads across different of the plurality of containers; scheduling, based upon the container dependencies and the service dependencies, threads to cores, wherein the scheduling is based upon minimizing thread processing times; and publishing the container dependencies and the service dependencies on a registry of the node clusters.Type: GrantFiled: August 18, 2021Date of Patent: May 14, 2024Assignee: International Business Machines CorporationInventors: Priyanka Prakash Naik, Kavya G, Chander Govindarajan, Sayandeep Sen, Palanivel Andiappan Kodeswaran
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Publication number: 20240090116Abstract: The present disclosure relates to a thermal solution using a heat exchanger mounted inside an outdoor telecom unit. More specifically, a hardened optical platform includes a base chassis and a lid configured to seal an interior of the base chassis, wherein each of the base chassis and the lid include a plurality of fins. The hardened optical platform also including a vapor chamber in the interior including a heat exchanger. The heat exchanger including a second plurality of fins that are intertwined with a third plurality of fins on the base chassis in the interior.Type: ApplicationFiled: October 28, 2022Publication date: March 14, 2024Inventors: Chander Prakash Gupta, Sachin Singla, Ranjeet Chaurasiya, Rampratap Mahawar, Shubham Kumar
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Patent number: 11617285Abstract: An outdoor, hardened telecommunications clamshell platform includes a base half and a top cover half. The platform also includes a Printed Circuit Board (PCB) disposed between two cooling plates within the platform, and a heat distributing mechanism surrounding the PCB within the platform and configured to distribute heat substantially evenly between the base half and the top cover half.Type: GrantFiled: May 3, 2021Date of Patent: March 28, 2023Assignee: Ciena CorporationInventors: Simon J. E. Shearman, Michael R. Bishop, Marko Nicolici, Chander Prakash Gupta
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Publication number: 20220304193Abstract: An outdoor, hardened telecommunications clamshell platform includes a base half and a top cover half. The platform also includes a Printed Circuit Board (PCB) disposed between two cooling plates within the platform, and a heat distributing mechanism surrounding the PCB within the platform and configured to distribute heat substantially evenly between the base half and the top cover half.Type: ApplicationFiled: May 3, 2021Publication date: September 22, 2022Inventors: Simon J. E. Shearman, Michael R. Bishop, Marko Nicolici, Chander Prakash Gupta
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Patent number: 9810081Abstract: A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.Type: GrantFiled: June 11, 2010Date of Patent: November 7, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Ching-Pang Lee, Chander Prakash, Reinhard Schilp, David A. Little
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Patent number: 9546558Abstract: A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.Type: GrantFiled: July 8, 2010Date of Patent: January 17, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Ching-Pang Lee, Danning You, Reinhard Schilp, Chander Prakash
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Patent number: 9334741Abstract: A wall structure (32, 42, 68, 70, 80) with layers (A, B, C, D, E) of non-random voids (26A, 26B, 28B, 30B) that interconnect to form discretely defined tortuous passages between an interior (21) and an exterior surface (23) of the wall for transpiration cooling of the wall. A coolant flow (38) through the wall may be metered by restrictions in coolant outlets (31) and/or within the passages to minimize the coolant requirement. Pockets (44) may be formed on the exterior surface of the wall for thermal Insulation (46). The layers may be formed by lamination, additive manufacturing, or casting. Layer geometries include alternating layers (A, B, C) with different overlapping void patterns (42), 3-D lattice structures (70), and offset waffle structures (80).Type: GrantFiled: April 22, 2010Date of Patent: May 10, 2016Assignees: Siemens Energy, Inc., Mikro Systems, Inc.Inventors: Ching-Pang Lee, Chander Prakash, Gary B. Merrill, Andreas Heselhaus, Andrew J. Burns
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Patent number: 9288558Abstract: A control module for an optical switch node, comprising a TIM having a plurality of operating modes in which a first mode is identified by a first byte sequence; a communication interface unit transmitting a second byte sequence for placing the TIM in the first mode, the first byte sequence different from the second byte sequence, and a gate array receiving the second byte sequence, storing a list of predetermined unique values, each value indicative of a particular operating mode command, receiving at least a portion of the second byte sequence and receiving instructions to apply an algorithm to at least a portion of the second byte sequence to transform the portion into a checksum value, comparing the checksum value to the list to determine the operating mode command, and transmitting the first byte sequence to the TIM to place the TIM into the first mode.Type: GrantFiled: March 28, 2014Date of Patent: March 15, 2016Assignee: Infinera CorporationInventors: Soven Kumar Dana, Chander Prakash Singh Dogra, Sandeep Kumar, Eric Heistermann
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Patent number: 9206904Abstract: A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.Type: GrantFiled: July 8, 2010Date of Patent: December 8, 2015Assignee: Siemens Energy, Inc.Inventors: Ching-Pang Lee, Vincent P. Laurello, Chander Prakash, Kok-Mun Tham
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Publication number: 20150281812Abstract: A control module for an optical switch node, comprising a TIM having a plurality of operating modes in which a first mode is identified by a first byte sequence; a communication interface unit transmitting a second byte sequence for placing the TIM in the first mode, the first byte sequence different from the second byte sequence, and a gate array receiving the second byte sequence, storing a list of predetermined unique values, each value indicative of a particular operating mode command, receiving at least a portion of the second byte sequence and receiving instructions to apply an algorithm to at least a portion of the second byte sequence to transform the portion into a checksum value, comparing the checksum value to the list to determine the operating mode command, and transmitting the first byte sequence to the TIM to place the TIM into the first mode.Type: ApplicationFiled: March 28, 2014Publication date: October 1, 2015Inventors: Soven Kumar Dana, Chander Prakash Singh Dogra, Sandeep Kumar, Eric Heistermann
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Patent number: 8721291Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.Type: GrantFiled: July 12, 2011Date of Patent: May 13, 2014Assignee: Siemens Energy, Inc.Inventors: Ching-Pang Lee, Kok-Mun Tham, Paul H. Vitt, Stephen R. Williamson, Matthew D. Montgomery, Chander Prakash, Melissa Harris
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Patent number: 8500404Abstract: A film cooling apparatus with a cooling hole (46) in a component wall (40). A first surface (42) of the wall is subject to a hot gas flow (48). A second surface (44) receives a coolant gas (50). The coolant flows through the hole, then downstream over the first surface (42). One or more pairs of cooperating electrodes (60-61, 62-63, 80-81) generates and accelerates a plasma (70) that creates a body force acceleration (71, 82) in the coolant flow that urges the coolant flow to turn around the entry edge (57) and/or the exit edge (58) of the cooling hole without separating from the adjacent surface (47, 42). The electrodes may have a geometry that spreads the coolant into a fan shape over the hot surface (42) of the component wall (40).Type: GrantFiled: April 30, 2010Date of Patent: August 6, 2013Assignee: Siemens Energy, Inc.Inventors: Matthew D. Montgomery, Chander Prakash
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Patent number: 8435001Abstract: Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.Type: GrantFiled: December 17, 2009Date of Patent: May 7, 2013Assignee: Siemens Energy, Inc.Inventors: Matthew D. Montgomery, Ching-Pang Lee, Chander Prakash
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Publication number: 20130017095Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.Type: ApplicationFiled: July 12, 2011Publication date: January 17, 2013Inventors: Ching-Pang Lee, Kok-Mun Tham, Paul H. Vitt, Stephen R. Williamson, Matthew D. Montgomery, Chander Prakash, Melissa Harris
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Publication number: 20120006028Abstract: A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.Type: ApplicationFiled: July 8, 2010Publication date: January 12, 2012Inventors: Ching-Pang Lee, Danning You, Reinhard Schilp, Chander Prakash
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Publication number: 20120007318Abstract: A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.Type: ApplicationFiled: July 8, 2010Publication date: January 12, 2012Inventors: Ching-Pang Lee, Vincent P. Laurello, Chander Prakash, Kok-Mun Tham
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Publication number: 20110302924Abstract: A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.Type: ApplicationFiled: June 11, 2010Publication date: December 15, 2011Inventors: Ching-Pang Lee, Chander Prakash, Reinhard Schilp, David A. Little
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Publication number: 20110268556Abstract: A film cooling apparatus with a cooling hole (46) in a component wall (40). A first surface (42) of the wall is subject to a hot gas flow (48). A second surface (44) receives a coolant gas (50). The coolant flows through the hole, then downstream over the first surface (42). One or more pairs of cooperating electrodes (60-61, 62-63, 80-81) generates and accelerates a plasma (70) that creates a body force acceleration (71, 82) in the coolant flow that urges the coolant flow to turn around the entry edge (57) and/or the exit edge (58) of the cooling hole without separating from the adjacent surface (47, 42). The electrodes may have a geometry that spreads the coolant into a fan shape over the hot surface (42) of the component wall (40).Type: ApplicationFiled: April 30, 2010Publication date: November 3, 2011Inventors: Matthew D. Montgomery, Chander Prakash
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Publication number: 20110262695Abstract: A wall structure (32, 42, 68, 70, 80) with layers (A, B, C, D, E) of non-random voids (26A, 26B, 28B, 30B) that interconnect to form discretely defined tortuous passages between an interior (21) and an exterior surface (23) of the wall for transpiration cooling of the wall. A coolant flow (38) through the wall may be metered by restrictions in coolant outlets (31) and/or within the passages to minimize the coolant requirement. Pockets (44) may be formed on the exterior surface of the wall for thermal Insulation (46). The layers may be formed by lamination, additive manufacturing, or casting. Layer geometries include alternating layers (A, B, C) with different overlapping void patterns (42), 3-D lattice structures (70), and offset waffle structures (80).Type: ApplicationFiled: April 22, 2010Publication date: October 27, 2011Inventors: Ching-Pang Lee, Chander Prakash, Gary B. Merrill, Andreas Heselhaus, Andrew J. Burns
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Publication number: 20110150653Abstract: Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.Type: ApplicationFiled: December 17, 2009Publication date: June 23, 2011Inventors: Matthew D. Montgomery, Ching-Pang Lee, Chander Prakash