Patents by Inventor Ethan K. Stearns
Ethan K. Stearns 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).
-
Patent number: 11028730Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.Type: GrantFiled: February 4, 2019Date of Patent: June 8, 2021Assignee: Raytheon Technologies CorporationInventors: Ethan K. Stearns, John Axel Glahn, Daniel J. McKaveney
-
Patent number: 10400671Abstract: A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger. A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.Type: GrantFiled: March 22, 2016Date of Patent: September 3, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Federico Papa, Thomas G. Phillips, Kathleen R. Phillips, Ethan K. Stearns, Justin W. Heiss
-
Publication number: 20190170016Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.Type: ApplicationFiled: February 4, 2019Publication date: June 6, 2019Inventors: Ethan K. Stearns, John Axel Glahn, Daniel J. McKaveney
-
Publication number: 20190120140Abstract: A gas turbine engine includes a bearing compartment that has at least one seal, a bearing disposed in the bearing compartment, a deoiler fluidly connected with the bearing compartment, and a vacuum generator fluidly connected with the deoiler.Type: ApplicationFiled: October 24, 2017Publication date: April 25, 2019Inventors: Jorn A. Glahn, Matthew J. Howlett, Myles R. Kelly, Victor M. Pinedo, Gregory E. Reinhardt, Bradley C. Schafer, Ethan K. Stearns
-
Patent number: 10196936Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.Type: GrantFiled: March 14, 2014Date of Patent: February 5, 2019Assignee: United Technologies CorporationInventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney
-
Patent number: 10107198Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.Type: GrantFiled: March 14, 2014Date of Patent: October 23, 2018Assignee: United Technologies CorporationInventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney
-
Patent number: 9878799Abstract: A method of protecting fuel hardware for a gas turbine engine in an aircraft is disclosed. The method may include determining a current altitude of the aircraft, and controlling a temperature of fuel for the gas turbine engine based at least in part on the current altitude. A thermal management system for a gas turbine engine in an aircraft is also disclosed. The thermal management system may include a sensor configured to detect a current altitude of the aircraft, and a controller in operative communication with the sensor. The controller may be configured to manage a fuel temperature for the gas turbine engine based at least in part on the current altitude detected by the sensor.Type: GrantFiled: October 3, 2014Date of Patent: January 30, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Matthew D. Teicholz, Ethan K. Stearns
-
Patent number: 9879563Abstract: A lubricant supply system for a gas turbine engine has a lubricant lube pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear for an associated gas turbine engine. A method and apparatus are disclosed.Type: GrantFiled: March 12, 2013Date of Patent: January 30, 2018Assignee: United Technologies CorporationInventors: Kathleen R. Phillips, Thomas G. Phillips, Ethan K. Stearns
-
Publication number: 20180016024Abstract: A fuel system for use with a gas turbine engine with a fuel flow and an oil flow includes a fuel-oil cooler in fluid communication with the fuel flow and the oil flow, the fuel-oil cooler to transfer heat between the fuel flow and the oil flow, a fuel filter associated with the fuel-oil cooler, the fuel filter in fluid communication with the fuel flow, and an electric heating element disposed adjacent to at least one of the fuel-oil cooler and the fuel filter.Type: ApplicationFiled: July 12, 2016Publication date: January 18, 2018Inventor: Ethan K. Stearns
-
Publication number: 20160332743Abstract: A method of protecting fuel hardware for a gas turbine engine in an aircraft is disclosed. The method may include determining a current altitude of the aircraft, and controlling a temperature of fuel for the gas turbine engine based at least in part on the current altitude. A thermal management system for a gas turbine engine in an aircraft is also disclosed. The thermal management system may include a sensor configured to detect a current altitude of the aircraft, and a controller in operative communication with the sensor. The controller may be configured to manage a fuel temperature for the gas turbine engine based at least in part on the current altitude detected by the sensor.Type: ApplicationFiled: October 3, 2014Publication date: November 17, 2016Inventors: Matthew D. Teicholz, Ethan K. Stearns
-
Publication number: 20160201563Abstract: A system is provided for a turbine engine that includes a fuel injector and an actuator. The system includes a fuel management system configured to receive fuel from a flow path. The fuel management system is also configured to provide a first portion of the fuel received from the flow path to the fuel injector at a first temperature, and a second portion of the fuel received from the flow path to the actuator at a second temperature different than the first temperature.Type: ApplicationFiled: September 10, 2014Publication date: July 14, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Ethan K. Stearns, Clifton J. Crawley, Jr.
-
Publication number: 20160201557Abstract: A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger. A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.Type: ApplicationFiled: March 22, 2016Publication date: July 14, 2016Inventors: Federico PAPA, Thomas G. PHILLIPS, Kathleen R. PHILLIPS, Ethan K. STEARNS, Justin W. HEISS
-
Patent number: 9341080Abstract: A gas turbine engine includes a fan, a compressor section, a combustion section, and a turbine section. A fan drive gear system is configured for driving the fan at a speed different than the turbine section. A lubricant system includes a lubricant pump delivering lubricant to an outlet line. The outlet line splits into at least a hot line and into a cool line. The hot line is directed primarily to locations in the gas turbine engine that are not intended to receive cooler lubricant. The cool line is directed through one or more heat exchangers at which the lubricant is cooled, and the cool line then is routed to the fan drive gear system. At least one of the one or more heat exchangers is a fuel/oil cooler at which lubricant will be cooled by fuel leading to the combustion section. The fuel/oil cooler is downstream of a point where the outlet line splits into the at least the hot line and the cool line, such that the hot line is not directed through the fuel/oil cooler. A method is also disclosed.Type: GrantFiled: April 4, 2014Date of Patent: May 17, 2016Assignee: United Technologies CorporationInventors: Kathleen R. Phillips, Thomas G. Phillips, Ethan K. Stearns, Federico Papa
-
Patent number: 9334802Abstract: A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.Type: GrantFiled: March 13, 2013Date of Patent: May 10, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Federico Papa, Thomas G. Phillips, Kathleen R. Phillips, Ethan K. Stearns, Justin W. Heiss
-
Publication number: 20160024968Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.Type: ApplicationFiled: March 14, 2014Publication date: January 28, 2016Inventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney
-
Publication number: 20150361887Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.Type: ApplicationFiled: March 14, 2014Publication date: December 17, 2015Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney
-
Patent number: 9038397Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan. A turbine section is configured for driving the geared architecture. A thermal management system that includes a first fluid circuit and a second fluid circuit that manage heat generated in at least a portion of the gas turbine engine. A first heat exchanger is incorporated into each of the first fluid circuit and the second fluid circuit. A second heat exchanger is incorporated into the first fluid circuit. A valve controls an amount of a first fluid that is communicated to the first heat exchanger and the second heat exchanger. A controller is configured to control a positioning of the valve.Type: GrantFiled: April 8, 2014Date of Patent: May 26, 2015Assignee: United Technologies CorporationInventors: Federico Papa, Thomas G. Phillips, Kathleen R. Phillips, Ethan K. Stearns, Justin W. Heiss
-
Patent number: 9039013Abstract: A hydrodynamic non-contacting seal wherein the sealing surface of a rotatable sealing member is grooved in a spiral pattern such that the depth of the grooves decreases in a direction opposite to the direction of rotation of the rotatable sealing member.Type: GrantFiled: May 4, 2011Date of Patent: May 26, 2015Assignee: United Technologies CorporationInventors: Antonio F. Artiles, Ethan K. Stearns
-
Publication number: 20140360153Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan. A turbine section is configured for driving the geared architecture. A thermal management system that includes a first fluid circuit and a second fluid circuit that manage heat generated in at least a portion of the gas turbine engine. A first heat exchanger is incorporated into each of the first fluid circuit and the second fluid circuit. A second heat exchanger is incorporated into the first fluid circuit. A valve controls an amount of a first fluid that is communicated to the first heat exchanger and the second heat exchanger. A controller is configured to control a positioning of the valve.Type: ApplicationFiled: April 8, 2014Publication date: December 11, 2014Applicant: United Technologies CorporationInventors: Federico Papa, Thomas G. Phillips, Kathleen R. Phillips, Ethan K. Stearns, Justin W. Heiss
-
Publication number: 20140216003Abstract: A gas turbine engine includes a fan, a compressor section, a combustion section, and a turbine section. A fan drive gear system is configured for driving the fan at a speed different than the turbine section. A lubricant system includes a lubricant pump delivering lubricant to an outlet line. The outlet line splits into at least a hot line and into a cool line. The hot line is directed primarily to locations in the gas turbine engine that are not intended to receive cooler lubricant. The cool line is directed through one or more heat exchangers at which the lubricant is cooled, and the cool line then is routed to the fan drive gear system. At least one of the one or more heat exchangers is a fuel/oil cooler at which lubricant will be cooled by fuel leading to the combustion section. The fuel/oil cooler is downstream of a point where the outlet line splits into the at least the hot line and the cool line, such that the hot line is not directed through the fuel/oil cooler. A method is also disclosed.Type: ApplicationFiled: April 4, 2014Publication date: August 7, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Kathleen R. Phillips, Thomas G. Phillips, Ethan K. Stearns, Federico Papa