Patents by Inventor Matthew D. Parekh
Matthew D. Parekh 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).
-
Patent number: 11937429Abstract: Some embodiments include an integrated structure having vertically-stacked conductive levels alternating with dielectric levels. A layer over the conductive levels includes silicon, nitrogen, and one or more of carbon, oxygen, boron and phosphorus. In some embodiments the vertically-stacked conductive levels are wordline levels within a NAND memory array. Some embodiments include an integrated structure having vertically-stacked conductive levels alternating with dielectric levels. Vertically-stacked NAND memory cells are along the conductive levels within a memory array region. A staircase region is proximate the memory array region. The staircase region has electrical contacts in one-to-one correspondence with the conductive levels. A layer is over the memory array region and over the staircase region. The layer includes silicon, nitrogen, and one or more of carbon, oxygen, boron and phosphorus.Type: GrantFiled: December 20, 2021Date of Patent: March 19, 2024Assignee: Micron Technology, Inc.Inventors: Justin B. Dorhout, Fei Wang, Chet E. Carter, Ian Laboriante, John D. Hopkins, Kunal Shrotri, Ryan Meyer, Vinayak Shamanna, Kunal R. Parekh, Martin C. Roberts, Matthew Park
-
Patent number: 11384654Abstract: A gas turbine engine includes one of a turbine section and a compressor section having multiple stages. At least one of the stages defines an outer diameter comprised of a plurality of circumferentially arranged blade outer air seals. Each blade outer air seal is spaced from each adjacent blade outer air seal in the plurality of circumferentially arranged blade outer air seals via a mateface gap. The mateface gap is oblique to a radius of the gas turbine engine, such that air entering the mateface gap is directed to an inner diameter surface of at least one of the blade outer air seals in the plurality of blade outer air seals.Type: GrantFiled: November 18, 2019Date of Patent: July 12, 2022Assignee: Raytheon Technologies CorporationInventors: Winston Gregory Smiddy, San Quach, Matthew D. Parekh, Jeffrey T. Morton
-
Patent number: 11156359Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a cold side; and a rail that extends from the cold side, the rail includes a first diffusion interface passage surface and a second diffusion interface passage surface, the first diffusion interface passage surface angled with respect to the second diffusion interface passage surface.Type: GrantFiled: December 26, 2019Date of Patent: October 26, 2021Assignee: Raytheon Technologies CorporationInventors: Donald W. Peters, San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Patent number: 11098612Abstract: A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a core flowpath, and a turbine fluidly connected to the combustor via the core flowpath. The turbine includes at least one stage having a plurality of rotors and a plurality of vanes. An outer diameter of the core flowpath at at least one stage is at least partially defined by a set of circumferentially arranged blade outer air seals. Each blade outer air seal includes a platform. An internal cooling cavity is defined within the platform. At least one mateface of the platform includes a cooling trench, and a first set of cooling holes connecting the internal cavity to the cooling trench.Type: GrantFiled: November 18, 2019Date of Patent: August 24, 2021Assignee: Raytheon Technologies CorporationInventors: Winston Gregory Smiddy, San Quach, Matthew D. Parekh, Jeffrey T. Morton
-
Publication number: 20210148245Abstract: A gas turbine engine includes one of a turbine section and a compressor section having multiple stages. At least one of the stages defines an outer diameter comprised of a plurality of circumferentially arranged blade outer air seals. Each blade outer air seal is spaced from each adjacent blade outer air seal in the plurality of circumferentially arranged blade outer air seals via a mateface gap. The mateface gap is oblique to a radius of the gas turbine engine, such that air entering the mateface gap is directed to an inner diameter surface of at least one of the blade outer air seals in the plurality of blade outer air seals.Type: ApplicationFiled: November 18, 2019Publication date: May 20, 2021Inventors: Winston Gregory Smiddy, San Quach, Matthew D. Parekh, Jeffrey T. Morton
-
Publication number: 20210148247Abstract: A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a core flowpath, and a turbine fluidly connected to the combustor via the core flowpath. The turbine includes at least one stage having a plurality of rotors and a plurality of vanes. An outer diameter of the core flowpath at at least one stage is at least partially defined by a set of circumferentially arranged blade outer air seals. Each blade outer air seal includes a platform. An internal cooling cavity is defined within the platform. At least one mateface of the platform includes a cooling trench, and a first set of cooling holes connecting the internal cavity to the cooling trench.Type: ApplicationFiled: November 18, 2019Publication date: May 20, 2021Inventors: Winston Gregory Smiddy, San Quach, Matthew D. Parekh, Jeffrey T. Morton
-
Patent number: 10830434Abstract: A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel such that the rail is non-perpendicular to the cold side and includes a concave surface to at least partially form a curved interface passage; and a second liner panel mounted to the support shell via a multiple of studs, the first liner panel including a second rail that extends from a cold side of the second liner panel and includes a convex surface to at least partially form the curved interface passage.Type: GrantFiled: February 23, 2017Date of Patent: November 10, 2020Assignee: Raytheon Technologies CorporationInventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Patent number: 10823411Abstract: A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel; a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to the first rail to form an interface passage; and at least one heat transfer feature within the interface passage.Type: GrantFiled: February 23, 2017Date of Patent: November 3, 2020Assignee: Raytheon Technologies CorporationInventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Patent number: 10718521Abstract: A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel; and a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail, the second rail includes a discontinuous rail end surface.Type: GrantFiled: February 23, 2017Date of Patent: July 21, 2020Assignee: Raytheon Technologies CorporationInventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Patent number: 10677462Abstract: A combustor for a gas turbine engine includes a support shell with an angled shell interface; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel adjacent to the angled shell interface; and a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail, the second rail adjacent to the angled shell interface.Type: GrantFiled: February 23, 2017Date of Patent: June 9, 2020Assignee: Raytheon Technologies CorporationInventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Publication number: 20200149742Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a cold side; and a rail that extends from the cold side, the rail includes a first diffusion interface passage surface and a second diffusion interface passage surface, the first diffusion interface passage surface angled with respect to the second diffusion interface passage surface.Type: ApplicationFiled: December 26, 2019Publication date: May 14, 2020Applicant: United Technologies CorporationInventors: Donald W. Peters, San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Patent number: 10551066Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a cold side; and a rail that extends from the cold side, the rail includes a first diffusion interface passage surface and a second diffusion interface passage surface, the first diffusion interface passage surface angled with respect to the second diffusion interface passage surface.Type: GrantFiled: June 15, 2017Date of Patent: February 4, 2020Assignee: United Technologies CorporationInventors: Donald W. Peters, San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Patent number: 10473331Abstract: A combustor of a gas turbine engine may include a combustor shell, a first combustor panel coupled to the combustor shell, and a second combustor panel coupled to the combustor shell. The first combustor panel may have a first endrail and the second combustor panel may have a second endrail. An annular cooling cavity may be defined between the combustor shell and the first and second combustor panels and a channel may be defined between the first endrail and the second endrail, wherein direct line-of-sight through the channel from the annular cooling cavity to a combustor chamber is obstructed. Said differently, the interface between the adjacent endrails may be non-linear, in a direction from the annular cooling cavity to the combustor chamber.Type: GrantFiled: May 18, 2017Date of Patent: November 12, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Patent number: 10378573Abstract: A retaining pin having anti-rotation features is provided. The retaining pin may comprise a pin shaft coupled to a retaining flange. The pin shaft may be inserted into a structural member proximate a shaft and a nut. The retaining flange may comprise an anti-rotation void defined by a first arm and a second arm and configured to engage the shaft. In response to the nut coupling the retaining flange to the shaft, the retaining pin may at least partially reduce movement and rotation of the shaft relative to the retaining pin.Type: GrantFiled: July 24, 2017Date of Patent: August 13, 2019Assignee: United Technologies CorporationInventors: Andrew Chuckta, Matthew D. Parekh
-
Publication number: 20190024694Abstract: A retaining pin having anti-rotation features is provided. The retaining pin may comprise a pin shaft coupled to a retaining flange. The pin shaft may be inserted into a structural member proximate a shaft and a nut. The retaining flange may comprise an anti-rotation void defined by a first arm and a second arm and configured to engage the shaft. In response to the nut coupling the retaining flange to the shaft, the retaining pin may at least partially reduce movement and rotation of the shaft relative to the retaining pin.Type: ApplicationFiled: July 24, 2017Publication date: January 24, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Andrew Chuckta, Matthew D. Parekh
-
Publication number: 20180363902Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a cold side; and a rail that extends from the cold side, the rail includes a first diffusion interface passage surface and a second diffusion interface passage surface, the first diffusion interface passage surface angled with respect to the second diffusion interface passage surface.Type: ApplicationFiled: June 15, 2017Publication date: December 20, 2018Applicant: United Technologies CorporationInventors: Donald W. Peters, San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Publication number: 20180335211Abstract: A combustor of a gas turbine engine may include a combustor shell, a first combustor panel coupled to the combustor shell, and a second combustor panel coupled to the combustor shell. The first combustor panel may have a first endrail and the second combustor panel may have a second endrail. An annular cooling cavity may be defined between the combustor shell and the first and second combustor panels and a channel may be defined between the first endrail and the second endrail, wherein direct line-of-sight through the channel from the annular cooling cavity to a combustor chamber is obstructed. Said differently, the interface between the adjacent endrails may be non-linear, in a direction from the annular cooling cavity to the combustor chamber.Type: ApplicationFiled: May 18, 2017Publication date: November 22, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: SAN QUACH, JEFFREY T. MORTON, MATTHEW D. PAREKH
-
Publication number: 20180238546Abstract: A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel; a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to the first rail to form an interface passage; and at least one heat transfer feature within the interface passage.Type: ApplicationFiled: February 23, 2017Publication date: August 23, 2018Applicant: United Technologies CorporationInventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Publication number: 20180238179Abstract: A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel such that the rail is non-perpendicular to the cold side and includes a concave surface to at least partially form a curved interface passage; and a second liner panel mounted to the support shell via a multiple of studs, the first liner panel including a second rail that extends from a cold side of the second liner panel and includes a convex surface to at least partially form the curved interface passage.Type: ApplicationFiled: February 23, 2017Publication date: August 23, 2018Applicant: United Technologies CorporationInventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
-
Publication number: 20180238545Abstract: A combustor for a gas turbine engine includes a support shell with an angled shell interface; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel adjacent to the angled shell interface; and a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail, the second rail adjacent to the angled shell interface.Type: ApplicationFiled: February 23, 2017Publication date: August 23, 2018Applicant: United Technologies CorporationInventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh