Patents by Inventor Pang Lee
Pang Lee 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: 11967570Abstract: A semiconductor package includes a base comprising a top surface and a bottom surface that is opposite to the top surface; a first semiconductor chip mounted on the top surface of the base in a flip-chip manner; a second semiconductor chip stacked on the first semiconductor chip and electrically coupled to the base by wire bonding; an in-package heat dissipating element comprising a dummy silicon die adhered onto the second semiconductor chip by using a high-thermal conductive die attach film; and a molding compound encapsulating the first semiconductor die, the second semiconductor die, and the in-package heat dissipating element.Type: GrantFiled: March 4, 2022Date of Patent: April 23, 2024Assignee: MediaTek Inc.Inventors: Chia-Hao Hsu, Tai-Yu Chen, Shiann-Tsong Tsai, Hsing-Chih Liu, Yao-Pang Hsu, Chi-Yuan Chen, Chung-Fa Lee
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Publication number: 20240087995Abstract: A power semiconductor package includes: a die carrier having first and second opposite sides; and first and second power semiconductor dies each having first and second power electrodes on opposite sides. The second power electrodes face and are electrically coupled to the first side of the carrier. A molded body at least partially encapsulates the dies and has a first and second opposite sides and lateral sides connecting the first and second sides. First and second power contacts and first and second control contacts are arranged laterally next to each other. The first power electrode of the first die is electrically coupled to the first power contact by a first electrical connector. The first power electrode of the second die is electrically coupled to the second power contact by a second electrical connector. A width of each power contact is at least four times the width of each control contact.Type: ApplicationFiled: August 22, 2023Publication date: March 14, 2024Inventors: Ralf Otremba, Thai Kee Gan, Teck Sim Lee, Chwee Pang Tommy Khoo, Christian Schiele, Katrin Unterhofer, Patrick Uredat
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Publication number: 20240076993Abstract: A turbine vane in a gas turbine engine includes an inner platform, an outer platform, and a vane airfoil positioned therebetween. The vane airfoil includes a first cooling passage extending between the outer platform and the inner platform, and a second cooling passage extending between the outer platform and the inner platform. The second cooling passage is arranged downstream of the first cooling passage with respect to a flow direction. The turbine vane includes a jumper tube disposed between the second cooling passage and the inner platform. The jumper tube includes an inlet, an outlet, and a tube wall enclosing a hollow interior. The inlet is positioned a distance within the second cooling passage. The outlet is positioned at least partially through an aperture of the inner platform.Type: ApplicationFiled: January 6, 2021Publication date: March 7, 2024Inventors: Daniel Joo, Ching-Pang Lee, Gm Salam Azad, Sin Chien Siw
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Patent number: 11415000Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.Type: GrantFiled: June 4, 2018Date of Patent: August 16, 2022Assignee: Siemens Energy Global GmbH & Co. KGInventors: Ching-Pang Lee, Jae Y. Um, Sin Chien Siw, Anthony Waywood, Harry Holloman, Steven Koester
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Patent number: 11377956Abstract: A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to an aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from the blade root for cooling the turbine blade.Type: GrantFiled: July 23, 2018Date of Patent: July 5, 2022Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: Peter Schröder, Christopher W. Ross, Santiago R. Salazar, Patrick M. Pilapil, Roger Matthews, Kevin Kampka, Joana Verheyen, Ching-Pang Lee, Javan Albright, James McCoy, Sin Chien Siw, Kok-Mun Tham
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Patent number: 11351473Abstract: The present disclosure provides an integrated design building block with turnable modules inside, the building block comprising: a lower housing, an upper housing, and a plurality of turnable modules mechanism, the lower housing and the upper housing being fitted to form a plurality of receiving spaces, the plurality of turnable modules being disposed within the plurality of receiving spaces, respectively, wherein the turnable modules may be partially or completely received in the receiving spaces, the turnable modules each having a turnable module connection portion; the lower housing and the upper housing are fitted to form a body structure of the building block; a plurality of connection portions are provided on surfaces of the body structure; the turnable module connection portions are fitted to the plurality of connection portions on the surfaces of the body structure. The building block provided by the present disclosure has advantages of a simple mechanical structure and a low cost.Type: GrantFiled: November 27, 2018Date of Patent: June 7, 2022Assignee: TransformCube Product Design LimitedInventor: Kai Pang Lee
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Patent number: 11319819Abstract: A blade (10) for a turbine engine that includes an internal cooling system (56) formed from at least one cavity (58) positioned within a generally elongated airfoil (12). A squealer tip (36) and at least one densified oxide dispersion strengthened layer (38) extend radially from a radially outer tip cap (70) of the blade (10), the tip cap (70) having a tip cap upper surface (50).Type: GrantFiled: May 1, 2018Date of Patent: May 3, 2022Assignee: Siemens Energy Global GmbH & Co. KGInventors: Kok-Mun Tham, Ching-Pang Lee, Li Shing Wong, Sin Chien Siw
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Patent number: 11248472Abstract: A trailing edge cooling feature for a turbine airfoil (10) includes a plurality of pins (22a-l) positioned in an airfoil interior (11) toward the trailing edge 20), each extending from the pressure side (14) to the suction side (16) and further being elongated in a radial direction (R). The pins (22a-l) are arranged in multiple radial rows (A-L) spaced along the chordal axis (30), with the pins (22a-l) in each row (A-L) being interspaced to define coolant passages (24a-l) therebetween. A row of radially spaced apart partition walls (26) are positioned aft of the pins (22a-l). Each partition wall (26) extends from the pressure side (14) to the suction side (16) and is elongated in a generally axial direction, extending along the chordal axis (30) to terminate at the trailing edge (20).Type: GrantFiled: October 30, 2015Date of Patent: February 15, 2022Assignee: Siemens Energy Global GmbH & Co. KGInventor: Ching-Pang Lee
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Patent number: 11193378Abstract: A turbine airfoil (10) includes a trailing edge coolant cavity (41f) located in an airfoil interior (11) between a pressure sidewall (14) and a suction sidewall (16). The trailing edge coolant cavity (41f) is positioned adjacent to a trailing edge (20) of the turbine airfoil (10) and is in fluid communication with a plurality of coolant exit slots (28) positioned along the trailing edge (20). At least one framing passage (70, 80) is formed at a span-wise end of the trailing edge coolant cavity (41f). The airfoil (10) further includes framing features (72A-B, 82A-B) located in the framing passage (70, 80). The framing features are configured as ribs (72A-B, 82A-B) protruding from the pressure sidewall (14) and/or the suction sidewall (16). The ribs (72A-B, 82A-B) extend partially between the pressure sidewall (14) and the suction sidewall (16).Type: GrantFiled: October 24, 2016Date of Patent: December 7, 2021Assignee: Siemens Energy Global GmbH & Co. KGInventor: Ching-Pang Lee
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Publication number: 20210301664Abstract: A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from blade root for cooling the turbine blade.Type: ApplicationFiled: July 23, 2018Publication date: September 30, 2021Inventors: Peter Schröder, Christopher W. Ross, Santiago R. Salazar, Patrick M. Pilapil, Roger Matthews, Kevin Kampka, Joana Verheyen, Ching-Pang Lee, Javan Albright, James McCoy, Sin Chien Siw, Kok-Mun Tham
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Turbine rotor airfoil and corresponding method for reducing pressure loss in a cavity within a blade
Patent number: 11111795Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.Type: GrantFiled: August 7, 2018Date of Patent: September 7, 2021Assignee: Siemens Energy Global GmbH & Co. KGInventors: Ching-Pang Lee, Harry Holloman, Steven Koester, Jae Y. Um, Sin Chien Siw -
Patent number: 11085306Abstract: An integrated airfoil and platform cooling system (30) for a turbine rotor blade (10) includes an inlet (38, 48) located at the root (24) for receiving a supply of a coolant (K), and at least one cooling leg (32a, 32c, 42a, 42c) fluidly connected to the inlet (38, 48) and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg (32a, 32c, 42a, 42c) is defined at least partially by a span-wise extending internal cavity (26) within a blade airfoil (12). An entrance of the cooling leg (32a, 32c, 42a, 42c) comprises a flow passage (92, 102) that extends radially outboard and laterally into a blade platform (50), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side (60) of a radially outer surface (52) of the blade platform (50), before leading the coolant (K) into the cooling leg (32a, 32c, 42a, 42c).Type: GrantFiled: March 20, 2018Date of Patent: August 10, 2021Assignee: Siemens Energy Global GmbH & Co. KGInventors: Ching-Pang Lee, Anthony Waywood, Steven Koester
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Patent number: 11009914Abstract: An electronic device includes a housing and a buffer component. The housing has a corner portion and two side edges adjacent to the corner portion. The buffer component is embedded in the corner portion and includes a strengthened layer and a buffer layer. The strengthened layer includes an arc-shaped side edge and an embedded portion. The embedded portion is embedded in the corner portion, such that the arc-shaped side edge is aligned with the two side edges. The strengthened layer is a strengthened material structure. The buffer layer is disposed between the strengthened layer and the housing, and the buffer layer is an elastic material structure.Type: GrantFiled: November 14, 2019Date of Patent: May 18, 2021Assignee: PEGATRON CORPORATIONInventors: Chien-I Chen, Wei-Pang Lee, Hsin-Lan Liao, Chen-Wei Lai, Yi-Lun Tsao, Jyun-Yi Lee
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Publication number: 20210140321Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.Type: ApplicationFiled: June 4, 2018Publication date: May 13, 2021Inventors: Ching-Pang Lee, Jae Y. Um, Sin Chien Siw, Anthony Waywood, Harry Holloman, Steven Koester
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Patent number: 11002144Abstract: A shroud assembly for a turbine engine includes a seal for sealing a gap between a first mate face of a first shroud segment and a second mate face of a circumferentially adjacent second shroud segment. The seal is received in first and second slots formed respectively on the first and second mate faces. The first and second slots extend axially between a leading edge and a trailing edge of the respective shroud segment. The first slot is open at the leading and the trailing edges while the second slot is open at the leading edge and closed at the trailing edge. The seal has axially extending first and second sides which are receivable respectively within the first and second slots. The seal has an axial length substantially equal to tan axial length of the shroud segments and has a cutout on the second side at a trailing edge end of the seal.Type: GrantFiled: March 30, 2018Date of Patent: May 11, 2021Assignee: Siemens Energy Global GmbH & Co. KGInventors: Gm Salam Azad, Runzhong Chen, Ching-Pang Lee
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TURBINE ROTOR AIRFOIL AND CORRESPONDING METHOD FOR REDUCING PRESSURE LOSS IN A CAVITY WITHIN A BLADE
Publication number: 20210025278Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.Type: ApplicationFiled: August 7, 2018Publication date: January 28, 2021Inventors: Ching-Pang Lee, Harry Holloman, Steven Koester, Jae Y. Um, Sin Chien Siw -
Publication number: 20210010381Abstract: A shroud assembly for a turbine engine includes a seal for sealing a gap between a first mate face of a first shroud segment and a second mate face of a circumferentially adjacent second shroud segment. The seal is received in first and second slots formed respectively on the first and second mate faces. The first and second slots extend axially between a leading edge and a trailing edge of the respective shroud segment. The first slot is open at the leading and the trailing edges while the second slot is open at the leading edge and closed at the trailing edge. The seal has axially extending first and second sides which are receivable respectively within the first and second slots. The seal has an axial length substantially equal to tan axial length of the shroud segments and has a cutout on the second side at a trailing edge end of the seal.Type: ApplicationFiled: March 30, 2018Publication date: January 14, 2021Inventors: Gm Salam Azad, Runzhong Chen, Ching-Pang Lee
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Patent number: 10787911Abstract: A gas turbine engine airfoil includes an outer wall including a suction side, a pressure side, a leading edge, and a trailing edge, the outer wall defining an interior chamber of the airfoil. The airfoil further includes cooling structure provided in the interior chamber. The cooling structure defines an interior cooling cavity and includes a plurality of cooling fluid outlet holes, at least one of which is in communication with a pressure side cooling circuit and at least one of which is in communication with a suction side cooling circuit. At least one of the pressure and suction side cooling circuits includes: a plurality of rows of airfoils, wherein radially adjacent airfoils within a row define segments of cooling channels. Outlets of the segments in one row align aerodynamically with inlets of segments in an adjacent downstream row such that the cooling channels have a serpentine shape.Type: GrantFiled: June 11, 2018Date of Patent: September 29, 2020Assignees: SIEMENS ENERGY, INC., MIKRO SYSTEMS, INC.Inventors: Ching-Pang Lee, Benjamin Heneveld
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Publication number: 20200291787Abstract: A turbine airfoil (10) includes a trailing edge coolant cavity (41f) located in an airfoil interior (11) between a pressure sidewall (14) and a suction sidewall (16). The trailing edge coolant cavity (41f) is positioned adjacent to a trailing edge (20) of the turbine airfoil (10) and is in fluid communication with a plurality of coolant exit slots (28) positioned along the trailing edge (20). At least one framing passage (70, 80) is formed at a span-wise end of the trailing edge coolant cavity (41f). The airfoil (10) further includes framing features (72A-B, 82A-B) located in the framing passage (70, 80). The framing features are configured as ribs (72A-B, 82A-B) protruding from the pressure sidewall (14) and/or the suction sidewall (16). The ribs (72A-B, 82A-B) extend partially between the pressure sidewall (14) and the suction sidewall (16).Type: ApplicationFiled: October 24, 2016Publication date: September 17, 2020Inventor: Ching-Pang Lee
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Publication number: 20200225709Abstract: An electronic device includes a housing and a buffer component. The housing has a corner portion and two side edges adjacent to the corner portion. The buffer component is embedded in the corner portion and includes a strengthened layer and a buffer layer. The strengthened layer includes an arc-shaped side edge and an embedded portion. The embedded portion is embedded in the corner portion, such that the arc-shaped side edge is aligned with the two side edges. The strengthened layer is a strengthened material structure. The buffer layer is disposed between the strengthened layer and the housing, and the buffer layer is an elastic material structure.Type: ApplicationFiled: November 14, 2019Publication date: July 16, 2020Inventors: Chien-I Chen, Wei-Pang Lee, Hsin-Lan Liao, Chen-Wei Lai, Yi-Lun Tsao, Jyun-Yi Lee