Patents by Inventor Cheng-Zhang Wang
Cheng-Zhang Wang 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: 20240120317Abstract: A fan-out semiconductor device includes stacked semiconductor dies having die bond pads arranged in columns exposed at a sidewall of the stacked semiconductor dies. The stacked dies are encapsulated in a photo imageable dielectric (PID) material, which is developed to form through-hole cavities that expose the columns of bond pads of each die at the sidewall. The through-hole cavities are plated or filled with an electrical conductor to form conductive through-holes coupling die bond pads within the columns to each other.Type: ApplicationFiled: July 13, 2023Publication date: April 11, 2024Applicant: Western Digital Technologies, Inc.Inventors: Cheng-Hsiung Yang, Chien Te Chen, Cong Zhang, Ching-Chuan Hsieh, Yu-Ying Tan, Juan Zhou, Ai-wen Wang, Yih-Fran Lee, Yu-Wen Huang
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Patent number: 11953409Abstract: A gas extraction device for metal mineral inclusions and a gas extraction method therefor are provided, the device includes a base plate, an annular carrier, sealing covers, a grinding assembly, a vacuum assembly, a gas-gathering assembly and a mass spectrometer. The annular carrier is disposed on the base plate, multiple grinding chambers are defined and evenly distributed in a circular shape on the annular carrier, the sealing covers are disposed at openings of the grinding chambers, the grinding assembly includes grinding hammers, and the grinding hammers penetrate through the sealing covers and extend into the grinding chambers. Side walls of each grinding chamber defines a first through hole and a second through hole. The vacuum assembly is communicated with the grinding chambers through the first through holes. The gas-gathering assembly is communicated with the grinding chambers through the second through holes. The mass spectrometer is communicated with the gas-gathering assembly.Type: GrantFiled: December 23, 2023Date of Patent: April 9, 2024Assignee: INNER MONGOLIA UNIVERSITY OF TECHNOLOGYInventors: Xiang-Guo Guo, Zhu Li, Xu Fu, Xudong Yan, Lin Li, Yue-Xing Wang, Zhi Shang, Cheng-Hao Ren, Dehui Zhang
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Publication number: 20200102886Abstract: A gas turbine engine includes a compressor delivering air into a combustion section. The combustion section and the compressor are housed in a housing. An air supply system communicates through the housing to deliver air from a location between an upstream end of the compressor, and an upstream end of the combustor. A diffuser is positioned downstream of the compressor. An opening in the housing supplies air to the inlet end. The diffuser has an outer shroud and an inner shroud with intermediate vanes. The outer shroud ends at a location upstream of a downstream end of the inner shroud at locations circumferentially aligned with the inlet end. The outer shroud only ends at the upstream location at circumferential locations associated with the inlet end, but extends further downstream at other locations.Type: ApplicationFiled: September 27, 2018Publication date: April 2, 2020Inventors: Cheng-Zhang Wang, Thomas G. Phillips, David F. Cloud, Peter M. Munsell
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Patent number: 10309308Abstract: A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.Type: GrantFiled: January 16, 2015Date of Patent: June 4, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Anthony P. Cherolis, Jeffrey J. Lienau, Robert Newman, Cheng-Zhang Wang
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Patent number: 10119468Abstract: A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.Type: GrantFiled: February 6, 2012Date of Patent: November 6, 2018Assignee: United Technologies CorporationInventors: Cheng-Zhang Wang, Thomas G. Phillips, David F. Cloud, Peter M. Munsell
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Patent number: 10087782Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.Type: GrantFiled: March 12, 2014Date of Patent: October 2, 2018Assignee: United Technologies CorporationInventors: Cheng-Zhang Wang, Jorn A. Glahn, David F. Cloud, Peter M. Munsell, Clifton J. Crawley, Jr., Robert Newman, Michelle Diana Stearns
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Patent number: 9803501Abstract: A turbine engine includes a frame assembly including an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A baffle within the outer cavity includes a plurality of openings for directing cooling airflow into the outer cavity for preventing impingement on a radially inner wall of the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.Type: GrantFiled: January 28, 2015Date of Patent: October 31, 2017Assignee: United Technologies CorporationInventor: Cheng-Zhang Wang
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Patent number: 9528391Abstract: An axially extending outer case for a gas turbine engine comprises an arcuate case wall, an opening, a boss and contouring. The arcuate case wall has an inner surface and an outer surface. The opening extends through the arcuate case wall. The boss extends radially from the outer surface of arcuate case wall and surrounds the opening. The contouring surrounds the opening along the inner surface of the arcuate case wall within the boss.Type: GrantFiled: July 17, 2012Date of Patent: December 27, 2016Assignee: United Technologies CorporationInventors: Donald Dougan, Jr., Daniel Carminati, Cheng-Zhang Wang
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Publication number: 20160245114Abstract: A turbine engine includes a frame assembly including an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A baffle within the outer cavity includes a plurality of openings for directing cooling airflow into the outer cavity for preventing impingement on a radially inner wall of the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.Type: ApplicationFiled: January 28, 2015Publication date: August 25, 2016Inventor: Cheng-Zhang Wang
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Publication number: 20160208701Abstract: A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.Type: ApplicationFiled: January 16, 2015Publication date: July 21, 2016Inventors: Anthony P. Cherolis, Jeffrey J. Lienau, Robert Newman, Cheng-Zhang Wang
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Publication number: 20160032775Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.Type: ApplicationFiled: March 12, 2014Publication date: February 4, 2016Inventors: Cheng-Zhang Wang, Jorn A. Glahn, David F. Cloud, Peter M. Munsell, Clifton J. Crawley, JR., Robert Newman, Michelle Diana Stearns
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Publication number: 20140023487Abstract: An axially extending outer case for a gas turbine engine comprises an arcuate case wall, an opening, a boss and contouring. The arcuate case wall has an inner surface and an outer surface. The opening extends through the arcuate case wall. The boss extends radially from the outer surface of arcuate case wall and surrounds the opening. The contouring surrounds the opening along the inner surface of the arcuate case wall within the boss.Type: ApplicationFiled: July 17, 2012Publication date: January 23, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Donald Dougan, Daniel Carminati, Cheng-Zhang Wang
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Publication number: 20130199205Abstract: A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.Type: ApplicationFiled: February 6, 2012Publication date: August 8, 2013Inventors: Cheng-Zhang Wang, Thomas G. Phillips, David F. Cloud, Peter M. Munsell
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Publication number: 20100303610Abstract: A stator assembly for a gas turbine engine is provided having an annular body, an inner gas path platform, a plurality of fairings, and at least one nozzle. The annular body has an outer gas path platform and a circumferentially extending annular cavity disposed radially outside of the outer gas path platform. The fairings extend radially between the inner gas path platform and the outer gas path platform. Each fairing includes a gas passage extending from the annular cavity through the inner gas path platform. The at least one nozzle has an inlet orifice disposed outside of the annular cavity and an exit orifice disposed within the annular cavity. The exit orifice is oriented within the annular cavity such that cooling air exiting the nozzle travels in a substantially circumferential direction within the annular cavity.Type: ApplicationFiled: May 29, 2009Publication date: December 2, 2010Applicant: United Technologies CorporationInventors: Cheng-Zhang Wang, William A. Daniels, Robert M. Sonntag
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Patent number: 7708520Abstract: A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.Type: GrantFiled: November 29, 2006Date of Patent: May 4, 2010Assignee: United Technologies CorporationInventors: Roger E. Paolillo, Ioannis Alvanos, Cheng-Zhang Wang
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Publication number: 20080124215Abstract: A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.Type: ApplicationFiled: November 29, 2006Publication date: May 29, 2008Inventors: Roger E. Paolillo, Ioannis Alvanos, Cheng-Zhang Wang