Patents by Inventor Sunil James
Sunil James 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: 11922945Abstract: Implementations relate to dynamically, and in a context-sensitive manner, biasing voice to text conversion. In some implementations, the biasing of voice to text conversions is performed by a voice to text engine of a local agent, and the biasing is based at least in part on content provided to the local agent by a third-party (3P) agent that is in network communication with the local agent. In some of those implementations, the content includes contextual parameters that are provided by the 3P agent in combination with responsive content generated by the 3P agent during a dialog that: is between the 3P agent, and a user of a voice-enabled electronic device; and is facilitated by the local agent. The contextual parameters indicate potential feature(s) of further voice input that is to be provided in response to the responsive content generated by the 3P agent.Type: GrantFiled: March 23, 2023Date of Patent: March 5, 2024Assignee: GOOGLE LLCInventors: Barnaby James, Bo Wang, Sunil Vemuri, David Schairer, Ulas Kirazci, Ertan Dogrultan, Petar Aleksic
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Patent number: 11287133Abstract: A combustion system and a method of combustion for a gas turbine engine includes a combustor liner defining a combustion chamber. A plurality of fuel nozzle sets extend into, and supply fuel flow to, the combustion chamber. A pilot fuel nozzle injects a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber. A main fuel nozzle injects a second fuel spray toward the exit end of the combustion chamber. At ignition conditions, a majority of the fuel flow is injected through the pilot fuel nozzles, and at high power conditions a majority of the fuel flow is injected through the main fuel nozzles. At high power conditions, a fuel rich mixture is supplied to the combustion chamber, and a row of quench jets are configured to supply air to the combustion chamber, providing rich-quench-lean combustion.Type: GrantFiled: August 7, 2020Date of Patent: March 29, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Sunil James
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Publication number: 20210116128Abstract: A combustion system and a method of combustion for a gas turbine engine includes a combustor liner defining a combustion chamber. A plurality of fuel nozzle sets extend into, and supply fuel flow to, the combustion chamber. A pilot fuel nozzle injects a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber. A main fuel nozzle injects a second fuel spray toward the exit end of the combustion chamber. At ignition conditions, a majority of the fuel flow is injected through the pilot fuel nozzles, and at high power conditions a majority of the fuel flow is injected through the main fuel nozzles. At high power conditions, a fuel rich mixture is supplied to the combustion chamber, and a row of quench jets are configured to supply air to the combustion chamber, providing rich-quench-lean combustion.Type: ApplicationFiled: August 7, 2020Publication date: April 22, 2021Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Sunil James
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Patent number: 10816211Abstract: A combustion system and a method of combustion for a gas turbine engine includes a combustor liner defining a combustion chamber. A plurality of fuel nozzle sets extend into, and supply fuel flow to, the combustion chamber. A pilot fuel nozzle injects a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber. A main fuel nozzle injects a second fuel spray toward the exit end of the combustion chamber. At ignition conditions, a majority of the fuel flow is injected through the pilot fuel nozzles, and at high power conditions a majority of the fuel flow is injected through the main fuel nozzles. At high power conditions, a fuel rich mixture is supplied to the combustion chamber, and a row of quench jets are configured to supply air to the combustion chamber, providing rich-quench-lean combustion.Type: GrantFiled: August 25, 2017Date of Patent: October 27, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Sunil James
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Patent number: 10775044Abstract: A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.Type: GrantFiled: October 26, 2018Date of Patent: September 15, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Atul Verma, Sunil James, Hamdullah Ozogul, John Gintert
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Publication number: 20200132304Abstract: A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.Type: ApplicationFiled: October 26, 2018Publication date: April 30, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Atul Verma, Sunil James, Hamdullah Ozogul, John Gintert
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Publication number: 20190063754Abstract: A combustion system and a method of combustion for a gas turbine engine includes a combustor liner defining a combustion chamber. A plurality of fuel nozzle sets extend into, and supply fuel flow to, the combustion chamber. A pilot fuel nozzle injects a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber. A main fuel nozzle injects a second fuel spray toward the exit end of the combustion chamber. At ignition conditions, a majority of the fuel flow is injected through the pilot fuel nozzles, and at high power conditions a majority of the fuel flow is injected through the main fuel nozzles. At high power conditions, a fuel rich mixture is supplied to the combustion chamber, and a row of quench jets are configured to supply air to the combustion chamber, providing rich-quench-lean combustion.Type: ApplicationFiled: August 25, 2017Publication date: February 28, 2019Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Sunil James
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Patent number: 9400110Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.Type: GrantFiled: October 19, 2012Date of Patent: July 26, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Terrel Kuhn, Vinayender Kuchana, Veeraraghava Raju Hasti, Raymond Gage, Sunil James
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Patent number: 9080770Abstract: A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.Type: GrantFiled: June 6, 2011Date of Patent: July 14, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Veeraraghave Raju Hasti, Terrel Kuhn, Sunil James, Mario Scaini
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Publication number: 20140109581Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.Type: ApplicationFiled: October 19, 2012Publication date: April 24, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Terrel Kuhn, Vinayender Kuchana, Veeraraghava Raju Hasti, Raymond Gage, Sunil James
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Publication number: 20120304647Abstract: A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.Type: ApplicationFiled: June 6, 2011Publication date: December 6, 2012Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Veeraraghava Raju Hasti, Terrel Kuhn, Sunil James, Mario Scaini