Patents by Inventor Monica Pacheco-Tougas
Monica Pacheco-Tougas 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: 11287132Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.Type: GrantFiled: February 24, 2020Date of Patent: March 29, 2022Assignee: Raytheon Technologies CorporationInventors: Dennis M. Moura, Jonathan J. Eastwood, Lee E. Bouldin, Monica Pacheco-Tougas
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Combustor liner panel with a multiple of heat transfer augmentors for a gas turbine engine combustor
Patent number: 10830448Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer augmentors located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer augmentors located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer augmentors define a height that extends about half the distance between a cold surface of the liner panel and the support shell.Type: GrantFiled: October 26, 2016Date of Patent: November 10, 2020Assignee: Raytheon Technologies CorporationInventors: Monica Pacheco-Tougas, Kevin Zacchera, Jonathan Jeffery Eastwood -
Patent number: 10808928Abstract: A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end. A spacing surface is spaced from the boss, and is at an outer position that is inward of the outer end of the boss. The spacing surface spaces the panel from the outer shell. A trough is intermediate the boss and the spacing surface. The trough extends to an outer end which is inward of the outer position of the spacing surface. A gas turbine engine is also disclosed.Type: GrantFiled: August 6, 2014Date of Patent: October 20, 2020Assignee: Raytheon Technologies CorporationInventors: Lee Edward Bouldin, Monica Pacheco-Tougas, Dennis M. Moura, Jonathan Jeffery Eastwood
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Publication number: 20200292172Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.Type: ApplicationFiled: February 24, 2020Publication date: September 17, 2020Inventors: Dennis M. Moura, Jonathan J. Eastwood, Lee E. Bouldin, Monica Pacheco-Tougas
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Patent number: 10731858Abstract: A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.Type: GrantFiled: September 16, 2014Date of Patent: August 4, 2020Assignee: Raytheon Technologies CorporationInventors: Lee E. Bouldin, Jonathan J. Eastwood, Dennis M. Moura, Monica Pacheco-Tougas
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Patent number: 10690348Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell and a heat shield that is attacked to the shell. The heat shield includes a rail and a cooling element connected to the rail in a cavity. The cavity extends in a vertical direction between the shell and the heat shield. The cavity fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.Type: GrantFiled: November 4, 2014Date of Patent: June 23, 2020Assignee: Raytheon Technologies CorporationInventors: Dennis M. Moura, Monica Pacheco-Tougas, Jonathan J. Eastwood, Lee E. Bouldin
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Patent number: 10655856Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.Type: GrantFiled: December 19, 2014Date of Patent: May 19, 2020Assignee: Raytheon Technologies CorporationInventors: Jonathan J. Eastwood, Dennis M. Moura, Lee E. Bouldin, Monica Pacheco-Tougas
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Patent number: 10648666Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle ? therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle ? therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.Type: GrantFiled: September 16, 2014Date of Patent: May 12, 2020Assignee: United Technologies CorporationInventors: Lee E. Bouldin, Dennis M. Moura, Jonathan J. Eastwood, Monica Pacheco-Tougas
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Patent number: 10598382Abstract: A liner associated with an engine of an aircraft is described. The liner includes a panel and an array of projections configured to enhance a cooling of the panel and distributed on at least part of a first side of the panel that corresponds to a cold side of the panel.Type: GrantFiled: November 6, 2015Date of Patent: March 24, 2020Assignee: United Technologies CorporationInventors: John S. Tu, James B. Hoke, Monica Pacheco-Tougas, Alexander W. Williams
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Patent number: 10571125Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.Type: GrantFiled: October 31, 2014Date of Patent: February 25, 2020Assignee: United Technologies CorporationInventors: Dennis M. Moura, Jonathan J. Eastwood, Lee E. Bouldin, Monica Pacheco-Tougas
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Patent number: 10386067Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.Type: GrantFiled: September 15, 2016Date of Patent: August 20, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: San Quach, Scott A. Elliott, Robert M. Sonntag, John S. Tu, Anthony Van, Joseph J. Sedor, Robert Selinsky, Jr., John J. Rup, Jr., Neil B. Ridgeway, Gerard V. Cadieux, Jeffrey Leon, Monica Pacheco-Tougas, Lisa A. Jenkins, Lisa Tse, Andrew Cervoni, Frank J. Trzcinski
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Patent number: 10215410Abstract: A combustor for a turbine engine is provided that includes a combustor wall. The combustor wall includes a shell and heat shield, which is attached to the shell. One or more cooling cavities are defined between the shell and the heat shield, and fluidly couple a plurality of apertures defined in the shell with a plurality of apertures defined in the heat shield. The apertures in the heat shield include a first aperture and a second aperture. An angle of incidence between the first aperture and a surface of the heat shield is different than an angle of incidence between the second aperture and the surface.Type: GrantFiled: November 4, 2014Date of Patent: February 26, 2019Assignee: United Technologies CorporationInventors: Dennis M. Moura, Monica Pacheco-Tougas, Jonathan J. Eastwood, Lee E. Bouldin
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Patent number: 10107497Abstract: A liner for a combustor of a turbine engine includes a cooling feature which projects from a backside and one or more effusion holes that communicate(s) through the liner. The effusion hole(s) surround an opening through said liner. The cooling feature may include a trip strip or a pyramid pin fin (e.g., a three-side pyramid pin fin, a conical pyramid pin fin). The effusion hole(s) may penetrate said cooling feature. The effusion hole(s) may define an angle less than or equal to ninety (90) degrees with respect to a face of said liner. The effusion hole(s) may be proximate an opening through said liner.Type: GrantFiled: October 4, 2012Date of Patent: October 23, 2018Assignee: United Technologies CorporationInventors: James P. Bangerter, Alexander W. Williams, Nicholas Mule, Monica Pacheco-Tougas
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Patent number: 10088159Abstract: A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.Type: GrantFiled: March 11, 2014Date of Patent: October 2, 2018Assignee: United Technologies CorporationInventors: Nurhak Erbas-Sen, James B. Hoke, John S. Tu, Monica Pacheco-Tougas
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Patent number: 10077903Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.Type: GrantFiled: October 19, 2015Date of Patent: September 18, 2018Assignee: United Technologies CorporationInventors: John S. Tu, James B. Hoke, Monica Pacheco-Tougas, Timothy S. Snyder, Dennis M. Moura, Anthony Van
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Publication number: 20180128485Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a stud free zone downstream of a combustor swirler. A combustor for a gas turbine engine, the combustor including a liner panel mounted to the support shell via a multiple of studs, the liner panel including a stud free zone downstream of each respective combustor swirler, the stud free zone including a multiple of film cooling holes. A method of directing airflow through a wall assembly within a combustor of a gas turbine engine including providing a stud free zone in a forward liner panel downstream of a combustor swirler, the stud free zone including a multiple of film cooling holes.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Applicant: United Technologies CorporationInventors: Jonathan Jeffery Eastwood, Monica Pacheco-Tougas, Kevin Zacchera
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COMBUSTOR LINER PANEL WITH A MULTIPLE OF HEAT TRANSFER AUGMENTORS FOR A GAS TURBINE ENGINE COMBUSTOR
Publication number: 20180112878Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer augmentors located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer augmentors located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer augmentors define a height that extends about half the distance between a cold surface of the liner panel and the support shell.Type: ApplicationFiled: October 26, 2016Publication date: April 26, 2018Applicant: United Technologies CorporationInventors: Monica Pacheco-Tougas, Kevin Zacchera, Jonathan Jeffery Eastwood -
Publication number: 20180073737Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.Type: ApplicationFiled: September 15, 2016Publication date: March 15, 2018Inventors: San Quach, Scott A. Elliott, Robert M. Sonntag, John S. Tu, Anthony Van, Joseph J. Sedor, Robert selinsky, JR., John J. Rup, JR., Neil B. Ridgeway, Gerard V. Cadieux, Jeffrey Leon, Monica Pacheco-Tougas, Lisa A. Jenkins, Lisa Tse, Andrew Cervoni, Frank J. Trzcinski
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Publication number: 20160356500Abstract: A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.Type: ApplicationFiled: September 16, 2014Publication date: December 8, 2016Inventors: Lee E. Bouldin, Jonathan J. Eastwood, Dennis M. Moura, Monica Pacheco-Tougas
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Publication number: 20160334103Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.Type: ApplicationFiled: December 19, 2014Publication date: November 17, 2016Applicant: United Technologies CorporationInventors: Jonathan J. Eastwood, Dennis M. Moura, Lee E. Bouldin, Monica Pacheco-Tougas