Patents by Inventor Christopher R. Joe
Christopher R. Joe 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: 9995165Abstract: A blade outer air seal member includes a distinct body that has two circumferential sides, a leading edge and a trailing edge, and a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side. The ceramic coating includes a forward coating portion and an aft coating portion. The gas path side has a bare area axially separating the forward coating portion and the aft coating portion. The bare area excludes any of the ceramic coating. One or more cooling passages have an outlet that opens at the bare area. The cooling passage extends in the body in an axial direction under the ceramic coating.Type: GrantFiled: June 10, 2015Date of Patent: June 12, 2018Assignee: United Technologies CorporationInventors: Christopher R. Joe, Paul M. Lutjen, Dominic J. Mongillo, Jr.
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Patent number: 9644490Abstract: An aircraft engine according to an example of the present disclosure includes, among other things, a high pressure turbine having a blade, an engine casing disposed about the blade, a shield disposed around the casing adjacent to the blade and creating an area between the shield and the casing, and a gate disposed along the shield. The gate is rotatable about the engine casing between an opened position and a closed position for selectively controlling entry of cooling air into the area. A method of cooling an engine is also disclosed.Type: GrantFiled: February 9, 2016Date of Patent: May 9, 2017Assignee: United Technologies CorporationInventors: Christopher R. Joe, Daniel A. Ward
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Publication number: 20160153307Abstract: An aircraft engine according to an example of the present disclosure includes, among other things, a high pressure turbine having a blade, an engine casing disposed about the blade, a shield disposed around the casing adjacent to the blade and creating an area between the shield and the casing, and a gate disposed along the shield. The gate is rotatable about the engine casing between an opened position and a closed position for selectively controlling entry of cooling air into the area. A method of cooling an engine is also disclosed.Type: ApplicationFiled: February 9, 2016Publication date: June 2, 2016Inventors: Christopher R. Joe, Daniel A. Ward
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Patent number: 9347334Abstract: An aircraft engine for use in a low-bypass turbofan application has a high pressure turbine having a blade and an engine casing disposed about the blade. A shield is disposed around the casing adjacent to the blade to create an area between the shield and the casing. A gate selectively controls entry of cooling air into the area and may be closed if the engine is maneuvering and may be open if cruising.Type: GrantFiled: March 31, 2010Date of Patent: May 24, 2016Assignee: United Technologies CorporationInventors: Christopher R. Joe, Daniel A. Ward
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Publication number: 20160047264Abstract: A blade outer air seal member includes a distinct body that has two circumferential sides, a leading edge and a trailing edge, and a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side. The ceramic coating includes a forward coating portion and an aft coating portion. The gas path side has a bare area axially separating the forward coating portion and the aft coating portion. The bare area excludes any of the ceramic coating. One or more cooling passages have an outlet that opens at the bare area. The cooling passage extends in the body in an axial direction under the ceramic coating.Type: ApplicationFiled: June 10, 2015Publication date: February 18, 2016Inventors: Christopher R. Joe, Paul M. Lutjen, Dominic J. Mongillo, JR.
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Patent number: 9145779Abstract: An example turbine component cooling arrangement includes a film plate having a plurality of film channels extending from film channel entrances on a first side of the film plate to corresponding film channel exits on an opposing second side of the film plate. The arrangement also includes an impingement plate establishing a plurality of impingement channels. The impingement plate is spaced a distance from the film plate. The plurality of impingement channels are configured to direct a fluid across the distance to contact the film plate between adjacent ones of the film channel entrances. In one example, the distance from the film plate to the impingement plate is between two and four times more than diameter of one of the impingement channels.Type: GrantFiled: March 12, 2009Date of Patent: September 29, 2015Assignee: United Technologies CorporationInventors: Christopher R. Joe, Karen A. Thole
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Patent number: 9062558Abstract: A blade outer air seal member includes a body that extends between two circumferential sides, axially between a leading edge and a trailing edge, and between a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side outside of a blade rub area of the gas path side such that the blade rub area is bare with regard to any ceramic coating.Type: GrantFiled: July 15, 2011Date of Patent: June 23, 2015Assignee: United Technologies CorporationInventors: Christopher R. Joe, Paul M. Lutjen, Dominic J. Mongillo, Jr.
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Patent number: 8529201Abstract: A blade outer air seal for a gas turbine engine has a plurality of stacked panels extending for at least a part circumferential extent, and extending from a radially outer location to a radially inner location. The plurality of stacked panels are mounted together. A turbine section is also claimed.Type: GrantFiled: December 17, 2009Date of Patent: September 10, 2013Assignee: United Technologies CorporationInventors: Paul M. Lutjen, Christopher R. Joe
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Patent number: 8439639Abstract: A gas turbine engine component having a filter mounted adjacent an impingement cavity to filter particles out of a secondary cooling airflow outboard of a cooling channel in communication with the secondary cooling airflow.Type: GrantFiled: February 24, 2008Date of Patent: May 14, 2013Assignee: United Technologies CorporationInventors: Christopher R. Joe, Eric A. Hudson, Keith A. Santeler
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Publication number: 20130089408Abstract: An aircraft engine for use in a low-bypass turbofan application has a high pressure turbine having a blade and an engine casing disposed about the blade. A shield is disposed around the casing adjacent to the blade to create an area between the shield and the casing. A gate selectively controls entry of cooling air into the area and may be closed if the engine is maneuvering and may be open if cruising.Type: ApplicationFiled: March 31, 2010Publication date: April 11, 2013Applicant: United Technologies CorporationInventors: Christopher R. Joe, Daniel A. Ward
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Publication number: 20130017058Abstract: A blade outer air seal member includes a body that extends between two circumferential sides, axially between a leading edge and a trailing edge, and between a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side outside of a blade rub area of the gas path side such that the blade rub area is bare with regard to any ceramic coating.Type: ApplicationFiled: July 15, 2011Publication date: January 17, 2013Inventors: Christopher R. Joe, Paul M. Lutjen, Dominic J. Mongillo, JR.
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Patent number: 8061146Abstract: A compact heat exchanger pedestal array for augmenting heat transfer in a machine is disclosed. The compact heat exchanger pedestal array includes a wall having first and second surfaces. The first surface faces a heated flow path and the second surface partially forms a flow path for cooling fluid. A plurality of pedestals extend from the second surface of the wall. At least one turbulator strip extends between adjacent pedestals. The turbulator strips and pedestals are operable for mixing the cooling fluid to increase heat transfer from the wall to the cooling fluid.Type: GrantFiled: April 8, 2010Date of Patent: November 22, 2011Assignee: United Technologies CorporationInventors: Christopher R. Joe, Paul M. Lutjen
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Publication number: 20110171011Abstract: A blade outer air seal for a gas turbine engine has a plurality of stacked panels extending for at least a part circumferential extent, and extending from a radially outer location to a radially inner location. The plurality of stacked panels are mounted together. A turbine section is also claimed.Type: ApplicationFiled: December 17, 2009Publication date: July 14, 2011Inventors: Paul M. Lutjen, Christopher R. Joe
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Publication number: 20100232929Abstract: An example turbine component cooling arrangement includes a film plate having a plurality of film channels extending from film channel entrances on a first side of the film plate to corresponding film channel exits on an opposing second side of the film plate. The arrangement also includes an impingement plate establishing a plurality of impingement channels. The impingement plate is spaced a distance from the film plate. The plurality of impingement channels are configured to direct a fluid across the distance to contact the film plate between adjacent ones of the film channel entrances. In one example, the distance from the film plate to the impingement plate is between two and four times more than diameter of one of the impingement channels.Type: ApplicationFiled: March 12, 2009Publication date: September 16, 2010Inventors: Christopher R. Joe, Karen A. Thole
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Patent number: 7775053Abstract: A compact heat exchanger pedestal array for augmenting heat transfer in a machine is disclosed. The compact heat exchanger pedestal array includes a wall having first and second surfaces. The first surface faces a heated flow path and the second surface partially forms a flow path for cooling fluid. A plurality of pedestals extend from the second surface of the wall. At least one turbulator strip extends between adjacent pedestals. The turbulator strips and pedestals are operable for mixing the cooling fluid to increase heat transfer from the wall to the cooling fluid.Type: GrantFiled: September 20, 2004Date of Patent: August 17, 2010Assignee: United Technologies CorporationInventors: Christopher R. Joe, Paul M. Lutjen
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Publication number: 20100186419Abstract: A compact heat exchanger pedestal array for augmenting heat transfer in a machine is disclosed. The compact heat exchanger pedestal array includes a wall having first and second surfaces. The first surface faces a heated flow path and the second surface partially forms a flow path for cooling fluid. A plurality of pedestals extend from the second surface of the wall. At least one turbulator strip extends between adjacent pedestals. The turbulator strips and pedestals are operable for mixing the cooling fluid to increase heat transfer from the wall to the cooling fluid.Type: ApplicationFiled: April 8, 2010Publication date: July 29, 2010Inventors: Christopher R. Joe, Paul M. Lutjen
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Patent number: 7665961Abstract: A turbine outer air seal includes, in a radially inner major surface thereof, at least one circumferential groove accommodating a plurality of holes which supply air for film cooling the radially inner surface of the air seal.Type: GrantFiled: November 29, 2006Date of Patent: February 23, 2010Assignee: United Technologies CorporationInventors: Paul M. Lutjen, John D. Wiedemer, James N. Knapp, Dominic J. Mongillo, Jr., Christopher R. Joe, Blake J. Luczak, Gary L. Grogg, Michael F. Benamati
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Publication number: 20090214329Abstract: A gas turbine engine component having a filter mounted adjacent an impingement cavity to filter particles out of a secondary cooling airflow outboard of a cooling channel in communication with the secondary cooling airflow.Type: ApplicationFiled: February 24, 2008Publication date: August 27, 2009Inventors: Christopher R. Joe, Eric A. Hudson, Keith A. Santeler
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Publication number: 20080124214Abstract: A turbine outer air seal includes, in a radially inner major surface thereof, at least one circumferential groove accommodating a plurality of holes which supply air for film cooling the radially inner surface of the air seal.Type: ApplicationFiled: November 29, 2006Publication date: May 29, 2008Applicant: United Technologies CorporationInventors: Paul M. Lutjen, John D. Wiedemer, James N. Knapp, Dominic J. Mongillo, Christopher R. Joe, Blake J. Luczak, Gary L. Grogg, Michael F. Benamati
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Patent number: 6514042Abstract: A cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.Type: GrantFiled: September 26, 2001Date of Patent: February 4, 2003Assignee: United Technologies CorporationInventors: William S. Kvasnak, Ronald S. LaFleur, Friedrich O. Soechting, Christopher R. Joe, Joe Moroso, Douglas A. Hayes