Patents by Inventor Erin G. Kline
Erin G. Kline 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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Publication number: 20230399112Abstract: An environmental control system of a vehicle includes a compressor having a compressor inlet configured to receive a first medium and a compressor outlet. A compressed first medium is provided at the compressor outlet. A conduit is configured to receive a second medium and a heat exchanger is mounted to the compressor. The heat exchanger is fluidly connected to a portion of the compressor and to the conduit.Type: ApplicationFiled: September 16, 2022Publication date: December 14, 2023Inventors: Donald E. Army, Louis J. Bruno, Aiden Coutin, Jeffrey Ernst, Kayla Gosse, Erin G. Kline
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Patent number: 11597530Abstract: Fuel tank inerting systems are described. The systems include a fuel tank having an inerting system flow path connected to the fuel tank. A catalytic reactor is arranged along the inerting system flow path configured to receive a reactant mixture of first reactant and a second reactant to generate inert gas. A condenser heat exchanger is arranged between the catalytic reactor and the fuel tank to cool an output from the catalytic reactor. A first ejector is configured to receive the first reactant and the second reactant and output the reactant mixture through an outlet. A second ejector is configured to receive an inert gas and the second reactant to output a mixture of the second reactant and the inert gas.Type: GrantFiled: March 24, 2021Date of Patent: March 7, 2023Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Xiaohong Liao, Erin G. Kline, Beakal T. Woldemariam, Earl Jean LaVallee, Gregory R. Leaper
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Patent number: 11180259Abstract: An aircraft includes one or more engines configured to generate high-pressure bleed air and low-pressure bleed air. An aircraft environmental control system (ECS) is in fluid communication with one or more of the engines to receive the high-pressure bleed air and the low-pressure bleed air. The ECS calculates a synthesized low-pressure value associated with the low-pressure bleed air while still providing bleed air using the high pressure bleed air. The ECS further switches from the high pressure bleed air to the low-bleed pressure air through the ECS while blocking flow of the high-pressure bleed air through the ECS based on the synthesized low-pressure value.Type: GrantFiled: March 21, 2018Date of Patent: November 23, 2021Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Jeffry K. Kamenetz, Erin G. Kline, Jeffrey Ernst, Bruce R. Schroder, Kevin R. DeRoy, Vince Vessella, Darragh McGrath, Adam Fagnani, Michel Labrecque
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Publication number: 20210339883Abstract: Fuel tank inerting systems are described. The systems include a fuel tank having an inerting system flow path connected to the fuel tank. A catalytic reactor is arranged along the inerting system flow path configured to receive a reactant mixture of first reactant and a second reactant to generate inert gas. A condenser heat exchanger is arranged between the catalytic reactor and the fuel tank to cool an output from the catalytic reactor. A first ejector is configured to receive the first reactant and the second reactant and output the reactant mixture through an outlet. A second ejector is configured to receive an inert gas and the second reactant to output a mixture of the second reactant and the inert gas.Type: ApplicationFiled: March 24, 2021Publication date: November 4, 2021Inventors: Xiaohong Liao, Erin G. Kline, Beakal T. Woldemariam, Earl Jean LaVallee, Gregory R. Leaper
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Patent number: 10934881Abstract: A system and method that comprises an air cycle machine, a flow of bleed air, at least one heat exchanger, and an inlet configured to supply the flow of the bleed air is provided. The bleed air flows from a source to mix with recirculated air in accordance with a high pressure mode or a recirculation chilling mode. The system and method also can also utilize the recirculated air flowing from the chamber to drive or maintain the air cycle machine in accordance with the above modes.Type: GrantFiled: April 24, 2015Date of Patent: March 2, 2021Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Louis J. Bruno, Thomas M. Zywiak, Donald E. Army, Jr., Harold W. Hipsky, Richard Rusich, Erin G. Kline, Eric Surawski, John M. Maljanian, Jr., Paul M. D'Orlando
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Patent number: 10926883Abstract: An aircraft includes a first engine that generates first bleed air flow and a second engine that generates second bleed air flow. The aircraft further includes an aircraft environmental control system (ECS) with a bleed manifold to collect the first bleed air flow and the second bleed air flow, and one or more air cycle machines to perform air conditioning consuming bleed air flow from the bleed manifold. The ECS balances the first bleed air flow and the second bleed air flow output from the first engine and second engine, respectively, based on a bleed manifold pressure of the bleed manifold.Type: GrantFiled: March 21, 2018Date of Patent: February 23, 2021Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Jeffry K. Kamenetz, Erin G. Kline, Jeffrey Ernst, James Joyce, Kevin R. DeRoy
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Patent number: 10814988Abstract: A system is provided. The system includes a first environmental control sub-system, operating in a first mode, that receives a first medium at a first flow amount and a first pressure. The system also includes a second environmental control sub-system, operating in a second mode, that receives a second medium at a second flow amount and a second pressure. The first flow amount is greater than the second flow amount, and the second pressure is greater than the first pressure.Type: GrantFiled: June 7, 2016Date of Patent: October 27, 2020Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Louis J. Bruno, Thomas M. Zywiak, Erin G. Kline, Christina W. Millot
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Patent number: 10711916Abstract: An aircraft environmental control system (ECS) includes a first valve that is adjustable between a plurality of first positions to open or shut-off a bleed air flow that flows from an inlet of the first valve to an outlet of the first valve. A second valve includes an inlet in fluid communication with the first valve outlet, and is adjustable between a plurality of second positions to throttle the bleed air that flows from the inlet of the second valve to an outlet of the second valve. A valve position sensor outputs a position signal indicating a measured position among the plurality of second positions. A controller is in signal communication with the valve position sensor. The controller is configured to determine a primary effective area of the second valve based on the measured position, and to diagnose operation of the first valve based on the primary effective area.Type: GrantFiled: March 21, 2018Date of Patent: July 14, 2020Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Jeffry K. Kamenetz, James Joyce, Erin G. Kline, John M. Maljanian, Jay H. Hartman
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Patent number: 10569887Abstract: A system and method onboard an aircraft includes a ram air temperature sensor, a bleed air temperature sensor, a valve, and a controller. The ram air temperature sensor is positioned to sense a ram air temperature of a ram air flow. The bleed air temperature sensor is positioned to sense a bleed air temperature of a bleed air flow, wherein the bleed air flow is cooled by a heat exchanger using the ram air flow. The valve is configured to control the bleed air flow upstream of the heat exchanger. The controller is configured to determine a bleed air threshold based on the ram air temperature, and control the valve to reduce the bleed air flow in response to the bleed air temperature reaching the bleed air threshold.Type: GrantFiled: March 16, 2018Date of Patent: February 25, 2020Assignee: Hamilton Sundstrand CorporationInventors: Patrick Valiquette, Erin G. Kline, Christopher McAuliffe, Thomas M. Zywiak, James Joyce, Lauren Kodet
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Publication number: 20190291872Abstract: An aircraft includes a first engine that generates first bleed air flow and a second engine that generates second bleed air flow. The aircraft further includes an aircraft environmental control system (ECS) with a bleed manifold to collect the first bleed air flow and the second bleed air flow, and one or more air cycle machines to perform air conditioning consuming bleed air flow from the bleed manifold. The ECS balances the first bleed air flow and the second bleed air flow output from the first engine and second engine, respectively, based on a bleed manifold pressure of the bleed manifold.Type: ApplicationFiled: March 21, 2018Publication date: September 26, 2019Inventors: Jeffry K. Kamenetz, Erin G. Kline, Jeffrey Ernst, James Joyce, Kevin R. DeRoy
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Publication number: 20190291876Abstract: An aircraft includes one or more engines configured to generate high-pressure bleed air and low-pressure bleed air. An aircraft environmental control system (ECS) is in fluid communication with one or more of the engines to receive the high-pressure bleed air and the low-pressure bleed air. The ECS calculates a synthesized low-pressure value associated with the low-pressure bleed air while still providing bleed air using the high pressure bleed air. The ECS further switches from the high pressure bleed air to the low-bleed pressure air through the ECS while blocking flow of the high-pressure bleed air through the ECS based on the synthesized low-pressure value.Type: ApplicationFiled: March 21, 2018Publication date: September 26, 2019Inventors: Jeffry K. Kamenetz, Erin G. Kline, Jeffrey Ernst, Bruce R. Schroder, Kevin R. DeRoy, Vince Vessella, Darragh McGrath, Adam Fagnani, Michel Labrecque
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Publication number: 20190293204Abstract: An aircraft environmental control system (ECS) includes a first valve that is adjustable between a plurality of first positions to open or shut-off a bleed air flow that flows from an inlet of the first valve to an outlet of the first valve. A second valve includes an inlet in fluid communication with the first valve outlet, and is adjustable between a plurality of second positions to throttle the bleed air that flows from the inlet of the second valve to an outlet of the second valve. A valve position sensor outputs a position signal indicating a measured position among the plurality of second positions. A controller is in signal communication with the valve position sensor. The controller is configured to determine a primary effective area of the second valve based on the measured position, and to diagnose operation of the first valve based on the primary effective area.Type: ApplicationFiled: March 21, 2018Publication date: September 26, 2019Inventors: Jeffry K. Kamenetz, James Joyce, Erin G. Kline, John M. Maljanian, Jay H. Hartman
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Publication number: 20190285324Abstract: A system and method onboard an aircraft includes a ram air temperature sensor, a bleed air temperature sensor, a valve, and a controller. The ram air temperature sensor is positioned to sense a ram air temperature of a ram air flow. The bleed air temperature sensor is positioned to sense a bleed air temperature of a bleed air flow, wherein the bleed air flow is cooled by a heat exchanger using the ram air flow. The valve is configured to control the bleed air flow upstream of the heat exchanger. The controller is configured to determine a bleed air threshold based on the ram air temperature, and control the valve to reduce the bleed air flow in response to the bleed air temperature reaching the bleed air threshold.Type: ApplicationFiled: March 16, 2018Publication date: September 19, 2019Inventors: Patrick Valiquette, Erin G. Kline, Christopher McAuliffe, Thomas M. Zywiak, James Joyce, Lauren Kodet
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Patent number: 10160547Abstract: An environmental control system (ECS) pack is provided including a primary heat exchanger and a secondary heat exchanger. An air cycle machine is arranged in fluid communication with at least one of the primary and second heat exchanger. The air cycle machine includes a compressor and a plurality of turbines. Discharged cabin air is supplied to at least one of the plurality of turbines to operate the compressor.Type: GrantFiled: May 26, 2015Date of Patent: December 25, 2018Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Louis J. Bruno, Harold W. Hipsky, Donald E. Army, Jr., Erin G. Kline, Christina W. Millot, Paul M. D'Orlando
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Patent number: 10124452Abstract: A heat exchanger for an aircraft includes a hot fluid inlet, a hot fluid outlet, a cold fluid inlet, a cold fluid outlet, and a header connected to the hot fluid outlet. The header includes a housing defining a header volume and a baffle separating the header volume into a first volume and a second volume, wherein the first volume and the second volume are in fluid communication with each other.Type: GrantFiled: January 15, 2016Date of Patent: November 13, 2018Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Donald E. Army, Louis J. Bruno, Erin G. Kline, Anthony DeLugan
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Patent number: 10035602Abstract: An airplane is provided. The airplane includes a pressurized compartment and an environmental control system. The environmental control system includes a compressing device. The compressing device includes a compressor and a turbine. The airplane also includes a first flow of first medium configured to enter the pressurized compartment and a second flow of the first medium configured to enter the turbine.Type: GrantFiled: June 8, 2016Date of Patent: July 31, 2018Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Louis J. Bruno, Donald E. Army, Thomas M. Zywiak, Harold W. Hipsky, Erin G. Kline
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Patent number: 9994323Abstract: A replacement system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers. The replacement system employs a subsystem to treat the medium from the low-pressure location of the engine before it is received by the inerting system.Type: GrantFiled: March 4, 2015Date of Patent: June 12, 2018Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Louis J. Bruno, Thomas M. Zywiak, Erin G. Kline, Christina W. Millot, Harold W Hipsky, Jr., Donald E. Army, Jr., Paul M. D'Orlando
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Patent number: 9994322Abstract: A system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers.Type: GrantFiled: February 11, 2015Date of Patent: June 12, 2018Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Louis J. Bruno, Donald E. Army, Jr., Thomas M. Zywiak, Erin G. Kline, Christina W. Millot, Harold W. Hipsky, Paul M. D'Orlando
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Patent number: 9926080Abstract: A system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers. The compressing device is bypassed based on the preparing in parallel the medium for the chamber, which in turn enables the compressing device to windmill. Therefore, the system employs at least one mechanism to prevent components of the compressing device from windmilling.Type: GrantFiled: February 11, 2015Date of Patent: March 27, 2018Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Louis J. Bruno, Thomas M. Zywiak, Harold W. Hipsky, Christina W. Millot, Donald E. Army, Jr., Paul M. D'Orlando, Erin G. Kline
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Patent number: 9889938Abstract: A system includes an inlet line configured to receive a medium flowing from a low-pressure location of an engine to a chamber, a plurality of heat exchangers configured to receive the medium from the inlet line, and a valve located upstream from the plurality of heat exchangers. The valve is configured to divide in parallel the medium across at least a first heat exchanger and a second heat exchanger of the plurality of heat exchangers. A recirculation air system is configured to supply a recirculation.Type: GrantFiled: June 5, 2015Date of Patent: February 13, 2018Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Louis J. Bruno, Thomas M. Zywiak, Erin G. Kline, Christina W. Millot, Donald E. Army, Jr., Harold W. Hipsky