Patents by Inventor Kristin Kopp-Vaughan
Kristin Kopp-Vaughan 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: 11408297Abstract: An air seal assembly for a gas turbine includes a flow path platform. The air seal assembly further includes a casing disposed radially outside the flow path platform. The air seal assembly further includes an annular finger seal mounted to the casing and disposed between the flow path platform and the casing. The annular finger seal includes a first circumferential portion mounted to the casing, a second circumferential portion extending from the first circumferential portion, and a third circumferential portion extending from the second circumferential portion and contacting an outer surface of the flow path platform. The third circumferential portion includes a plurality of air cooling holes configured to direct a cooling air stream onto the flow path platform.Type: GrantFiled: January 12, 2021Date of Patent: August 9, 2022Inventors: Jeffrey J. Lienau, Robert Newman, Conway Chuong, Kristin Kopp-Vaughan, Senthil Prasad Mathiyalagan, Krishna Nelanti, Rajendra Prasad Uppara Allabanda
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Publication number: 20210231023Abstract: An air seal assembly for a gas turbine includes a flow path platform. The air seal assembly further includes a casing disposed radially outside the flow path platform. The air seal assembly further includes an annular finger seal mounted to the casing and disposed between the flow path platform and the casing. The annular finger seal includes a first circumferential portion mounted to the casing, a second circumferential portion extending from the first circumferential portion, and a third circumferential portion extending from the second circumferential portion and contacting an outer surface of the flow path platform. The third circumferential portion includes a plurality of air cooling holes configured to direct a cooling air stream onto the flow path platform.Type: ApplicationFiled: January 12, 2021Publication date: July 29, 2021Inventors: Jeffrey J. Lienau, Robert Newman, Conway Chuong, Kristin Kopp-Vaughan, Senthil Prasad Mathiyalagan, Krishna Nelanti, Rajendra Prasad Uppara Allabanda
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Patent number: 10794596Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.Type: GrantFiled: August 19, 2014Date of Patent: October 6, 2020Assignee: Raytheon Technologies CorporationInventors: Zhongtao Dai, Randolph J Smith, Kristin Kopp-Vaughan, Timothy S. Snyder, Donald J Hautman
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Patent number: 10294873Abstract: A method of controlling an aircraft bleed may include the steps of monitoring a temperature of a precooled airflow exiting a precooler, and determining a status of a wing anti-ice system of an aircraft. The wing anti-ice system may be configured to receive the precooled airflow from the precooler. The method may further comprise the steps of determining whether an engine operating condition of the aircraft is within an icing envelope, selecting a temperature set point for the precooled airflow based on the status of the wing anti-ice system and whether the aircraft is within an icing envelope, and modulating a fan airflow from a fan to the precooler to adjust the temperature of the precooled airflow to the temperature set point.Type: GrantFiled: January 31, 2017Date of Patent: May 21, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Federico Papa, Bradley C Farnum, Kristin Kopp-Vaughan, Nathan Roe
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Patent number: 10228137Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler, the annular fuel gas passage terminates with a multiple of skewed slots.Type: GrantFiled: August 19, 2014Date of Patent: March 12, 2019Assignee: United Technologies CorporationInventors: Kristin Kopp-Vaughan, Timothy S Snyder, Randolph J Smith, Zhongtao Dai
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Patent number: 10060629Abstract: A combustor is provided. The combustor may comprise an axial fuel delivery system, and a radial fuel delivery system aft of the axial fuel delivery system. The radial fuel delivery system may be configured to direct fuel at least partially towards the axial fuel delivery system. A radial fuel delivery system is also provided. The system may comprise a combustor including a combustor liner, a mixer coupled to the combustor liner, and a nozzle disposed within the mixer, wherein the mixer and the nozzle are configured to direct fuel in a direction at least partially forward.Type: GrantFiled: February 20, 2015Date of Patent: August 28, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Wookyung Kim, Zhongtao Dai, Kristin Kopp-Vaughan
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Patent number: 10054312Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing. The pilot mixer can further include features to cool portions of the annular housing, such as a radial edge of the annular housing.Type: GrantFiled: February 25, 2015Date of Patent: August 21, 2018Assignee: United Technologies CorporationInventors: Zhongtao Dai, Kristin Kopp-Vaughan
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Publication number: 20180216538Abstract: A method of controlling an aircraft bleed may include the steps of monitoring a temperature of a precooled airflow exiting a precooler, and determining a status of a wing anti-ice system of an aircraft. The wing anti-ice system may be configured to receive the precooled airflow from the precooler. The method may further comprise the steps of determining whether an engine operating condition of the aircraft is within an icing envelope, selecting a temperature set point for the precooled airflow based on the status of the wing anti-ice system and whether the aircraft is within an icing envelope, and modulating a fan airflow from a fan to the precooler to adjust the temperature of the precooled airflow to the temperature set point.Type: ApplicationFiled: January 31, 2017Publication date: August 2, 2018Applicant: United Technologies CorporationInventors: Federico Papa, Bradley C Farnum, Kristin Kopp-Vaughan, Nathan Roe
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Patent number: 9958162Abstract: A combustor assembly includes a first wall, a second wall, a bulkhead and a plurality of fuel injectors. The bulkhead forms a combustion chamber with the first and the second walls. The fuel injectors are configured with the first wall in a unique and/or a fluctuating pattern.Type: GrantFiled: July 18, 2014Date of Patent: May 1, 2018Assignee: United Technologies CorporationInventors: Zhongtao Dai, Jeffrey M. Cohen, Kristin Kopp-Vaughan, James B. Hoke
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Patent number: 9791153Abstract: In various embodiments, a fuel injector may comprise a fuel nozzle and a pilot stage. The fuel nozzle may define a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area. The main fuel channel may be disposed about at least a portion of the simplex fuel channel. The secondary fuel channel may be disposed about at least a portion of the simplex fuel channel. The heat shield area may be configured to separate and protect the fuel channels from a heat load to prevent fuel coking. The pilot stage may be operatively coupled to the fuel nozzle and may be configured to receive fuel from the secondary fuel channel or the simplex fuel channel. The main stage may be operatively coupled to the fuel nozzle. The main stage may be configured to receive fuel from the main fuel channel.Type: GrantFiled: February 27, 2015Date of Patent: October 17, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Zhongtao Dai, Kristin Kopp-Vaughan, Dave Hyland, Russell B. Hanson, Lexia Kironn
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Publication number: 20160252252Abstract: In various embodiments, a fuel injector may comprise a fuel nozzle and a pilot stage. The fuel nozzle may define a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area. The main fuel channel may be disposed about at least a portion of the simplex fuel channel. The secondary fuel channel may be disposed about at least a portion of the simplex fuel channel. The heat shield area may be configured to separate and protect the fuel channels from a heat load to prevent fuel coking. The pilot stage may be operatively coupled to the fuel nozzle and may be configured to receive fuel from the secondary fuel channel or the simplex fuel channel. The main stage may be operatively coupled to the fuel nozzle. The main stage may be configured to receive fuel from the main fuel channel.Type: ApplicationFiled: February 27, 2015Publication date: September 1, 2016Applicant: United Technologies CorporationInventors: Zhongtao Dai, Kristin Kopp-Vaughan, Dave Hyland, Russell B. Hanson, Lexia Kironn
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Publication number: 20160245522Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing. The pilot mixer can further include features to cool portions of the annular housing, such as a radial edge of the annular housing.Type: ApplicationFiled: February 25, 2015Publication date: August 25, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: ZHONGTAO DAI, KRISTIN KOPP-VAUGHAN
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Publication number: 20160245523Abstract: A combustor is provided. The combustor may comprise an axial fuel delivery system, and a radial fuel delivery system aft of the axial fuel delivery system. The radial fuel delivery system may be configured to direct fuel at least partially towards the axial fuel delivery system. A radial fuel delivery system is also provided. The system may comprise a combustor including a combustor liner, a mixer coupled to the combustor liner, and a nozzle disposed within the mixer, wherein the mixer and the nozzle are configured to direct fuel in a direction at least partially forward.Type: ApplicationFiled: February 20, 2015Publication date: August 25, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Wookyung Kim, Zhongtao Dai, Kristin Kopp-Vaughan
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Publication number: 20160209038Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler, the annular fuel gas passage terminates with a multiple of skewed slots.Type: ApplicationFiled: August 19, 2014Publication date: July 21, 2016Inventors: Kristin Kopp-Vaughan, Timothy S Snyder, Randolph J Smith, Zhongtao Dai
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Publication number: 20160209037Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.Type: ApplicationFiled: August 19, 2014Publication date: July 21, 2016Applicant: United Technologies CorporationInventors: Zhongtao Dai, Randolph J Smith, Kristin Kopp-Vaughan, Timothy S. Snyder, Donald J Hautman
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Publication number: 20160201897Abstract: In various embodiments, a dual fuel nozzle (200) for use in a gas 200 turbine engine is provided. The nozzle may be configured to supply and gas and a liquid. The dual fuel nozzle (200) may include an interior wall (217). The interior wall (217) may include a shoulder (219). The shoulder (219) may include one or more gas ports (216). Gas may be discharged through the gas ports (216) and penetrate a mixing zone.Type: ApplicationFiled: August 19, 2014Publication date: July 14, 2016Inventors: Timothy S Snyder, Zhongtao Dai, Randolph J Smith, Kristin Kopp-Vaughan
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Publication number: 20150219338Abstract: A combustor assembly includes a first wall, a second wall, a bulkhead and a plurality of fuel injectors. The bulkhead forms a combustion chamber with the first and the second walls. The fuel injectors are configured with the first wall in a unique and/or a fluctuating pattern.Type: ApplicationFiled: July 18, 2014Publication date: August 6, 2015Inventors: Zhongtao Dai, Jeffrey M. Cohen, Kristin Kopp-Vaughan, James B. Hoke