Patents by Inventor Mehdi Milani Baladi
Mehdi Milani Baladi 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: 11945573Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.Type: GrantFiled: November 18, 2021Date of Patent: April 2, 2024Assignees: General Electric Company, GE Avio S.r.l.Inventors: Mehdi Milani Baladi, Randy M Vondrell
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Patent number: 11814988Abstract: A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes a port at the flowpath and is configured to receive at least a portion of the fluid from the flowpath from the second compressor. The first compressor includes a vane positioned at the flowpath and the vane includes an opening at the flowpath configured to egress the portion of the fluid from the port into the flowpath.Type: GrantFiled: September 15, 2021Date of Patent: November 14, 2023Assignee: General Electric CompanyInventors: Rodrigo Rodriguez Erdmenger, Rudolph Selmeier, Mehdi Milani Baladi, Jacek Marian Elszkowski
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Publication number: 20230051515Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.Type: ApplicationFiled: November 18, 2021Publication date: February 16, 2023Inventors: Mehdi Milani Baladi, Randy M Vondrell
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Patent number: 11300368Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow 46 to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.Type: GrantFiled: August 6, 2019Date of Patent: April 12, 2022Assignee: General Electric CompanyInventors: Thomas Kupiszewski, Christopher Charles Glynn, Steven Douglas Johnson, John Andrew Kemme, Mehdi Milani Baladi, Michael Epstein
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Publication number: 20220090507Abstract: A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes a port at the flowpath and is configured to receive at least a portion of the fluid from the flowpath from the second compressor. The first compressor includes a vane positioned at the flowpath and the vane includes an opening at the flowpath configured to egress the portion of the fluid from the port into the flowpath.Type: ApplicationFiled: September 15, 2021Publication date: March 24, 2022Inventors: Rodrigo Rodriguez Erdmenger, Rudolph Selmeier, Mehdi Milani Baladi, Jacek Marian Elszkowski
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Patent number: 11199132Abstract: An air intake system includes an exterior housing for a vehicle, the exterior housing including an outer surface including a recessed portion defined therein. The recessed portion includes an angled bottom member having a first end and a second end that is coupled to the outer surface. The recessed portion further includes a first sidewall, a second sidewall opposing the first sidewall, and an inlet opening defined within the recessed portion. The inlet opening is bounded by the first sidewall, the second sidewall, and the second end, and the inlet opening is configured to receive a fluid stream therethrough. The air intake system further includes an actuation component coupled to the angled bottom member. The actuation component includes a shape memory alloy, and the actuation component is responsive to a change in a thermal condition and configured to move the second end, thereby regulating the inlet opening.Type: GrantFiled: August 8, 2017Date of Patent: December 14, 2021Assignee: General Electric CompanyInventors: Carlos Enrique Diaz, Alvaro Enrique Hernandez, Mehdi Milani Baladi, David William Kimball
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Publication number: 20200124360Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow 46 to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.Type: ApplicationFiled: August 6, 2019Publication date: April 23, 2020Inventors: Thomas Kupiszewski, Christopher Charles Glynn, Steven Douglas Johnson, John Andrew Kemme, Mehdi Milani Baladi, Michael Epstein
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Publication number: 20200080475Abstract: A propulsion system for a vehicle (10) includes a propulsor (102) for generating a thrust for the vehicle, a motor (104) operable with the propulsor for driving the propulsor, a motor mount (164) for mounting the motor in or to the vehicle, and a thrust measuring device (172). The thrust measuring device (172) includes a strain sensor (174) mounted to a structural component of at least one of the propulsor (102), the motor (104), or the motor (164) mount for directly measuring a strain on the structural component caused by the thrust generated by the propulsor during operation of the propulsion system.Type: ApplicationFiled: December 11, 2017Publication date: March 12, 2020Inventors: Mehdi Milani Baladi, Christopher Michael Chapman, Simone Castellani
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Patent number: 10415897Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.Type: GrantFiled: November 17, 2014Date of Patent: September 17, 2019Assignee: General Electric CompanyInventors: Thomas Kupiszewski, Mehdi Milani Baladi, John Andrew Kemme, Christopher Charles Glynn, Steven Douglas Johnson, Michael Jay Epstein
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Publication number: 20190195128Abstract: An air intake system includes an exterior housing for a vehicle, the exterior housing including an outer surface including a recessed portion defined therein. The recessed portion includes an angled bottom member having a first end and a second end that is coupled to the outer surface. The recessed portion further includes a first sidewall, a second sidewall opposing the first sidewall, and an inlet opening defined within the recessed portion. The inlet opening is bounded by the first sidewall, the second sidewall, and the second end, and the inlet opening is configured to receive a fluid stream therethrough. The air intake system further includes an actuation component coupled to the angled bottom member. The actuation component includes a shape memory alloy, and the actuation component is responsive to a change in a thermal condition and configured to move the second end, thereby regulating the inlet opening.Type: ApplicationFiled: August 8, 2017Publication date: June 27, 2019Inventors: Carlos Enrique Diaz, Alvaro Enrique Hernandez, Mehdi Milani Baladi, David William Kimball
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Patent number: 10316696Abstract: A system includes a turbine with an expansion section configured to expand an exhaust flow in a downstream direction, such that the expansion section includes a plurality of stages and a diffuser section coupled downstream of the expansion section. The diffuser section receives the exhaust flow along an exhaust path and an energizing flow along a wall, and the diffuser section includes the wall comprising an inner surface, so the wall is disposed about the exhaust path, and an energizing port disposed in the wall at or downstream of a last stage of the plurality of stages of the expansion section. The energizing port is configured to direct the energizing flow along the inner surface of the wall to energize a boundary layer along the wall, and a first pressure of the energizing flow is greater than a second pressure of the exhaust flow at the energizing port.Type: GrantFiled: May 8, 2015Date of Patent: June 11, 2019Assignee: General Electric CompanyInventors: Mehdi Milani Baladi, Abdus Shamim, Joseph Anthony Cotroneo
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Publication number: 20180340474Abstract: An aircraft can comprise an engine, an environmental control system, an engine controller, and a plurality of sensors detecting engine or aircraft parameters. Engine or aircraft operation can be updated in real time based on input from the sensors, including airflow management or operation parameters.Type: ApplicationFiled: May 12, 2018Publication date: November 29, 2018Inventors: Mehdi Milani BALADI, Robert Jon MCQUISTON, Aniello ESPOSITO, Joseph DONOFRIO, Nicholas William SIMONE, Simone CASTELLANI
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Publication number: 20180209337Abstract: The gas turbine system comprises an aeroderivative gas turbine engine and a load having a shaft line drivingly coupled to the gas turbine engine. The gas turbine engine comprises a high-pressure turbine section and a high-pressure compressor section, drivingly coupled to one another by a first turbine shaft. The gas turbine engine further comprises an intermediate-pressure turbine section and a low-pressure compressor section, drivingly coupled to one another by a second turbine shaft, coaxial to the first turbine shaft (91). Furthermore, a combustor section is provided, fluidly coupled to the high-pressure compressor section and to the high-pressure turbine section. A free power turbine, supported by a third turbine shaft which is mechanically uncoupled from the first turbine shaft and the second turbine shaft, and is directly coupled to the shaft line, such that the shaft line and the third turbine shaft rotate at the same rotational speed.Type: ApplicationFiled: January 26, 2018Publication date: July 26, 2018Inventors: Alessandro RUSSO, Alessandro DEL BONO, Luciano MEI, Maurizio CIOFINI, Abdus SHAMIM, Mehdi Milani BALADI, Alessio POSTACCHINI, Bernard W. DUMM, Jason HAYDEN, Gabriele CARTOCCI, Francesco CARATELLI
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Patent number: 9957900Abstract: One embodiment of the present discloses includes a system. The system includes a turbine and a fluid supply system. The turbine includes a main flow path, a plurality of turbine blades disposed along the main flow path, at least one flow control area disposed along the main flow path, and at least one fluid injection port fluidly coupled to the main flow path. The fluid supply system is fluidly coupled to the at least one fluid injection port, wherein the fluid supply system is configured to supply a fluid to the at least one fluid injection port to adjust an effective area of the at least one flow control area.Type: GrantFiled: May 11, 2015Date of Patent: May 1, 2018Assignee: General Electric CompanyInventors: Mehdi Milani Baladi, Edward Michael Yanosik, Jr., Richard Bradford Hook, Jr., Scott Edward Farley, Gordon Jeffery Follin
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Patent number: 9932124Abstract: A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine.Type: GrantFiled: November 26, 2013Date of Patent: April 3, 2018Assignee: General Electric CompanyInventors: Deepak Manohar Kamath, Todd James Buchholz, Mehdi Milani Baladi, Michael Jay Epstein
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Patent number: 9863279Abstract: A system includes a gas turbine engine and a multipurpose gas turbine engine support frame couple to the gas turbine engine. The multipurpose gas turbine support frame is configured to support the gas turbine engine during both operation and transport of the gas turbine engine.Type: GrantFiled: July 11, 2012Date of Patent: January 9, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Donald Gordon Laing, Jose Francisco Estrada, Gerardo Plata Contreras, Mehdi Milani Baladi
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Patent number: 9656762Abstract: A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels. The system includes a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tank fluidly coupled to the engine, with the second fuel being different from the first fuel and having a different temperature than the first fuel, a fuel distribution unit (FDU) fluidly coupled to the first fuel tank of the first fuel system, and a fuel-to-fuel cooler (FFC) configured to transfer heat between the first fuel in the first fuel system and the second fuel in the second fuel system.Type: GrantFiled: November 26, 2013Date of Patent: May 23, 2017Assignee: General Electric CompanyInventors: Deepak Manohar Kamath, Mehdi Milani Baladi, Sergei A. Jerebets, Robert Lawrence Mayer, Scott Chandler Morton, Alejandro Yatzail Perez Valadez
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Patent number: 9644496Abstract: The present application provides a radial diffuser exhaust system for use with a gas turbine engine. The radial diffuser exhaust system may include a radial diffuser positioned within an asymmetric exhaust collector. The asymmetric exhaust collector may include a closed end chamber and an exhaust end chamber. The closed end chamber may have a first size, the exhaust end chamber may have a second size, and the first size may be smaller than the second size.Type: GrantFiled: March 13, 2013Date of Patent: May 9, 2017Assignee: General Electric CompanyInventors: Fernando Lopez-Parra, Balakrishnan Ponnuraj, Przemyslaw Drezek, Mehdi Milani Baladi, Ravinder Yerram, Donald Gordon Laing
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Publication number: 20160333794Abstract: One embodiment of the present discloses includes a system. The system includes a turbine and a fluid supply system. The turbine includes a main flow path, a plurality of turbine blades disposed along the main flow path, at least one flow control area disposed along the main flow path, and at least one fluid injection port fluidly coupled to the main flow path. The fluid supply system is fluidly coupled to the at least one fluid injection port, wherein the fluid supply system is configured to supply a fluid to the at least one fluid injection port to adjust an effective area of the at least one flow control area.Type: ApplicationFiled: May 11, 2015Publication date: November 17, 2016Inventors: Mehdi Milani Baladi, Edward Michael Yanosik, JR., Richard Bradford Hook, JR., Scott Edward Farley, Gordon Jeffery Follin
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Publication number: 20160326915Abstract: A system includes a turbine configured to expand a gas flow. The turbine includes a turbine rotor, such that the heated gas flow rotates the turbine rotor about an axis and a turbine casing is disposed around the turbine rotor. A cooling manifold directs a low pressure cooling fluid toward the turbine casing such that the low pressure cooling fluid cools the turbine casing.Type: ApplicationFiled: May 8, 2015Publication date: November 10, 2016Inventor: Mehdi Milani Baladi