Patents by Inventor Mario Scaini
Mario Scaini 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: 9731834Abstract: A system is provided for inerting a fuel tank of an aircraft. The system includes a first compressor fluidly coupled to the fuel tank for removing an air and fuel vapor mixture from an ullage of the fuel tank. The system further includes a fuel processor fluidly coupled to the first compressor and configured to receive the air and fuel vapor mixture and to generate hydrogen from the air and fuel vapor mixture. The system further includes a fuel cell fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity. The system further includes a combustor fluidly coupled to the fuel cell and configured to combust the exhaust product to produce combustion gas, and a first heat exchanger fluidly coupled to the combustor and configured to cool the combustion gas into inerting gas for the fuel tank.Type: GrantFiled: February 16, 2017Date of Patent: August 15, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Bijan F. Hagh, Daguang Zheng, Russell W. Johnson, Mukund Acharya, Mario Scaini
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Publication number: 20170158343Abstract: A system is provided for inerting a fuel tank of an aircraft. The system includes a first compressor fluidly coupled to the fuel tank for removing an air and fuel vapor mixture from an ullage of the fuel tank. The system further includes a fuel processor fluidly coupled to the first compressor and configured to receive the air and fuel vapor mixture and to generate hydrogen from the air and fuel vapor mixture. The system further includes a fuel cell fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity. The system further includes a combustor fluidly coupled to the fuel cell and configured to combust the exhaust product to produce combustion gas, and a first heat exchanger fluidly coupled to the combustor and configured to cool the combustion gas into inerting gas for the fuel tank.Type: ApplicationFiled: February 16, 2017Publication date: June 8, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Bijan F. Hagh, Daguang Zheng, Russell W. Johnson, Mukund Acharya, Mario Scaini
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Patent number: 9604730Abstract: A system is provided for inerting a fuel tank of an aircraft. The system includes a first compressor fluidly coupled to the fuel tank for removing an air and fuel vapor mixture from an ullage of the fuel tank. The system further includes a fuel processor fluidly coupled to the first compressor and configured to receive the air and fuel vapor mixture and to generate hydrogen from the air and fuel vapor mixture. The system further includes a fuel cell fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity. The system further includes a combustor fluidly coupled to the fuel cell and configured to combust the exhaust product to produce combustion gas, and a first heat exchanger fluidly coupled to the combustor and configured to cool the combustion gas into inerting gas for the fuel tank.Type: GrantFiled: March 27, 2014Date of Patent: March 28, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Bijan F. Hagh, Daguang Zheng, Russell W. Johnson, Mukund Acharya, Mario Scaini
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Publication number: 20150353201Abstract: A system is provided for inerting a fuel tank of an aircraft. The system includes a first compressor fluidly coupled to the fuel tank for removing an air and fuel vapor mixture from an ullage of the fuel tank. The system further includes a fuel processor fluidly coupled to the first compressor and configured to receive the air and fuel vapor mixture and to generate hydrogen from the air and fuel vapor mixture. The system further includes a fuel cell fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity. The system further includes a combustor fluidly coupled to the fuel cell and configured to combust the exhaust product to produce combustion gas, and a first heat exchanger fluidly coupled to the combustor and configured to cool the combustion gas into inerting gas for the fuel tank.Type: ApplicationFiled: March 27, 2014Publication date: December 10, 2015Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Bijan F. Hagh, Daguang Zheng, Russell W. Johnson, Mukund Acharya, Mario Scaini
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Publication number: 20150266589Abstract: An aircraft system includes a main fuel tank configured to house primary fuel and a green fuel tank configured to house green fuel. The mixing apparatus is configured to mix the primary fuel and the green fuel to result in a predetermined ratio of mixed fuel. A controller selectively commands a first amount of primary fuel and a second amount of green fuel to result in the predetermined ratio of mixed fuel. The main aircraft engine is configured to operate, in a first main engine mode, with the primary fuel from the main fuel tank and to operate, in a second main engine mode, with the mixed fuel from the mixing apparatus based on commands from the controller. The auxiliary power source is configured to operate with at least a portion of the green fuel from the green fuel tank based on commands from the controller.Type: ApplicationFiled: March 24, 2014Publication date: September 24, 2015Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Eric Blumer, Mukund Acharya, Audie Mak, Mario Scaini, Bijan F. Hagh
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Patent number: 9080770Abstract: A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.Type: GrantFiled: June 6, 2011Date of Patent: July 14, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Veeraraghave Raju Hasti, Terrel Kuhn, Sunil James, Mario Scaini
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Publication number: 20120304647Abstract: A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.Type: ApplicationFiled: June 6, 2011Publication date: December 6, 2012Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Veeraraghava Raju Hasti, Terrel Kuhn, Sunil James, Mario Scaini
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Publication number: 20100319653Abstract: An axial vane rotary combustion engine includes various performance improving features. These features include fluid film bearings that enable the vane assemblies to react large loads, a dual vane assembly configuration that share vane loads over two cylindrical bearing supports, a vane actuation mechanism that provides positive actuation even with cam surface tolerance variations, and various features to reduce friction to thereby improve efficiency and reduce heat generation.Type: ApplicationFiled: June 19, 2009Publication date: December 23, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: George Jerzy Zalewski, Mario Scaini, Nathan Gibson, Patrick Flynn
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Patent number: 7036321Abstract: An auxiliary power unit (APU) includes a rotary fuel slinger, and a single-spool, two-stage turbine. The rotary fuel slinger receives a rotational drive force from the turbine, and a supply of fuel from a fuel source. The rotary fuel slinger injects the fuel into a combustor as a continuous “fuel sheet.” As a result, fuel mixing and atomization inside the combustor is improved, which reduces emissions and pattern factor, which in turn increases turbine life.Type: GrantFiled: April 30, 2004Date of Patent: May 2, 2006Assignee: Honeywell International, Inc.Inventors: Rodolphe Dudebout, David H. Edmonds, Frank J. Zupanc, Roger J. DeRudder, Mario Scaini, Victor M. Reyes
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Publication number: 20050076650Abstract: An auxiliary power unit (APU) includes a rotary fuel slinger, and a single-spool, two-stage turbine. The rotary fuel slinger receives a rotational drive force from the turbine, and a supply of fuel from a fuel source. The rotary fuel slinger injects the fuel into a combustor as a continuous “fuel sheet.” As a result, fuel mixing and atomization inside the combustor is improved, which reduces emissions and pattern factor, which in turn increases turbine life.Type: ApplicationFiled: April 30, 2004Publication date: April 14, 2005Inventors: Rodolphe Dudebout, David Edmonds, Frank Zupanc, Roger DeRudder, Mario Scaini, Victor Reyes