Patents by Inventor Randal G. McKinney
Randal G. McKinney 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: 11143407Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.Type: GrantFiled: June 11, 2014Date of Patent: October 12, 2021Assignee: Raytheon Technologies CorporationInventors: James B. Hoke, Randal G. McKinney, Albert K. Cheung
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Patent number: 11112115Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.Type: GrantFiled: June 30, 2014Date of Patent: September 7, 2021Assignee: Raytheon Technologies CorporationInventors: Stanislav Kostka, Jr., Randal G. McKinney, James B. Hoke, Timothy S. Snyder, Frank J. Cunha
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Patent number: 10935243Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a liner panel with a perimeter rail and a multiple of intermediate rails. A combustor for a gas turbine engine including a support shell and a multiple of liner panels mounted to the support shell via a multiple of studs, each of the multiple of liner panels having a multiple of intermediate rails to form a multiple of circumferential cavities.Type: GrantFiled: November 30, 2016Date of Patent: March 2, 2021Assignee: Raytheon Technologies CorporationInventors: Mark F. Zelesky, Randal G. McKinney
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Patent number: 10907833Abstract: A combustor for a gas turbine engine comprises a combustion chamber having a pilot injector at one end and at least one main injector spaced radially from the pilot injector. The main injector includes a fluid flow path with a plug that restricts flow at least at an interior portion of the flow path. A gas turbine engine is also disclosed.Type: GrantFiled: January 5, 2015Date of Patent: February 2, 2021Assignee: Raytheon Technologies CorporationInventors: Zhongtao Dai, Adam Takashi Holley, Randal G. McKinney
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Patent number: 10816209Abstract: A fuel injection system may comprise a mixer and a fuel injector disposed within the mixer. The mixer may comprise an outer housing with an exit port and a bluff body extending across the exit port of the outer housing. A flared surface of the mixer may match a contour of the bluff body.Type: GrantFiled: September 19, 2017Date of Patent: October 27, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Albert K. Cheung, James B. Hoke, Randal G. McKinney
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Patent number: 10794595Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.Type: GrantFiled: February 3, 2015Date of Patent: October 6, 2020Assignee: Raytheon Technologies CorporationInventors: Randal G. McKinney, Frank J. Cunha, Stanislav Kostka, Jr.
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Patent number: 10697636Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.Type: GrantFiled: December 4, 2014Date of Patent: June 30, 2020Assignee: Raytheon Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr., Randal G. McKinney
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Publication number: 20200025376Abstract: A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.Type: ApplicationFiled: January 29, 2019Publication date: January 23, 2020Inventors: Timothy S. Snyder, Randal G. McKinney, James B. Hoke
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Patent number: 10260748Abstract: A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.Type: GrantFiled: December 21, 2012Date of Patent: April 16, 2019Assignee: United Technologies CorporationInventors: Timothy S. Snyder, Randal G. McKinney, James B. Hoke
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Publication number: 20180266686Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a liner panel with a perimeter rail and a multiple of intermediate rails. A combustor for a gas turbine engine including a support shell and a multiple of liner panels mounted to the support shell via a multiple of studs, each of the multiple of liner panels having a multiple of intermediate rails to form a multiple of circumferential cavities.Type: ApplicationFiled: November 30, 2016Publication date: September 20, 2018Applicant: United Technologies CorporationInventors: Mark F. Zelesky, Randal G. McKinney
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Patent number: 10066836Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.Type: GrantFiled: July 16, 2015Date of Patent: September 4, 2018Assignee: United Technologies CorporationInventors: Timothy S. Snyder, Steven W. Burd, Randal G. McKinney, George F. Titterton, III
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Publication number: 20180003387Abstract: A fuel injection system may comprise a mixer and a fuel injector disposed within the mixer. The mixer may comprise an outer housing with an exit port and a bluff body extending across the exit port of the outer housing. A flared surface of the mixer may match a contour of the bluff body.Type: ApplicationFiled: September 19, 2017Publication date: January 4, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Albert K. Cheung, James B. Hoke, Randal G. McKinney
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Patent number: 9797601Abstract: A combustor is provided. The combustor may include an axial fuel injection system, and a radial fuel injection system aft of the axial fuel injection system. The axial fuel injection system includes a mixer having a bluff body at an exit port of the mixer, and a fuel injector disposed within the mixer. A fuel and air mixer is also provided and comprises an outer housing with an exit port and a bluff body. The bluff body extends across the exit port of the outer housing. A fuel injection system is also provided. The systems comprise a mixer having a bluff body at an exit port of the mixer and a fuel injector disposed within the mixer.Type: GrantFiled: January 21, 2015Date of Patent: October 24, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Albert K. Cheung, James B. Hoke, Randal G. McKinney
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Publication number: 20170009987Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.Type: ApplicationFiled: February 3, 2015Publication date: January 12, 2017Inventors: Randal G. McKinney, Frank J. Cunha, Stanislav Kostka, JR.
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Publication number: 20160320063Abstract: A combustor for a gas turbine engine comprises a combustion chamber having a pilot injector at one end and at least one main injector spaced radially from the pilot injector. The main injector includes a fluid flow path with a plug that restricts flow at least at an interior portion of the flow path. A gas turbine engine is also disclosed.Type: ApplicationFiled: January 5, 2015Publication date: November 3, 2016Inventors: Zhongtao Dai, Adam Takashi Holley, Randal G. McKinney
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Publication number: 20160298843Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.Type: ApplicationFiled: December 4, 2014Publication date: October 13, 2016Applicant: United Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr., Randal G. McKinney
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Publication number: 20160209039Abstract: A combustor is provided. The combustor may include an axial fuel injection system, and a radial fuel injection system aft of the axial fuel injection system. The axial fuel injection system includes a mixer having a bluff body at an exit port of the mixer, and a fuel injector disposed within the mixer. A fuel and air mixer is also provided and comprises an outer housing with an exit port and a bluff body. The bluff body extends across the exit port of the outer housing. A fuel injection system is also provided. The systems comprise a mixer having a bluff body at an exit port of the mixer and a fuel injector disposed within the mixer.Type: ApplicationFiled: January 21, 2015Publication date: July 21, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Albert K. Cheung, James B. Hoke, Randal G. McKinney
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Publication number: 20160186998Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.Type: ApplicationFiled: June 30, 2014Publication date: June 30, 2016Applicant: United Technologies CorporationInventors: Stanislav Kostka, Jr., Randal G. McKinney, James B. Hoke, Timothy S. Snyder, Frank J. Cunha
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Publication number: 20160123596Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.Type: ApplicationFiled: June 11, 2014Publication date: May 5, 2016Inventors: James B. Hoke, Randal G. McKinney, Albert K. Cheung
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Publication number: 20150316000Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.Type: ApplicationFiled: July 16, 2015Publication date: November 5, 2015Inventors: Timothy S. Snyder, Steven W. Burd, Randal G. McKinney, George F. Titterton, III