Patents by Inventor Gregory L. Defrancesco

Gregory L. Defrancesco 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).

  • Publication number: 20190162428
    Abstract: A flow sensing ozone converter includes an inlet housing, an outlet housing, and an ozone converter core. The flow sensing ozone converter integrates flow sensing and oxygen removal components. The inlet housing is provided with an inlet housing flange. The outlet housing is provided with an outlet housing flange. The ozone converter core is at least partially received within the inlet housing. The ozone converter is provided with an ozone converter flange that abuts the inlet housing flange and the outlet housing flange.
    Type: Application
    Filed: November 28, 2017
    Publication date: May 30, 2019
    Inventors: Donald E. Army, Gregory L. DeFrancesco, Thomas M. Zywiak
  • Publication number: 20190093555
    Abstract: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.
    Type: Application
    Filed: November 26, 2018
    Publication date: March 28, 2019
    Inventors: Donald E. Army, John M. Maljanian, Gregory L. DeFrancesco
  • Publication number: 20190002109
    Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a plurality of heat exchangers positioned therein, the plurality of heat exchangers including a first heat exchanger, a second heat exchanger, and a third heat exchanger. The ram air circuit is configured and arranged so that a first medium received at the first heat exchanger passes through the first heat exchanger and then through the third heat exchanger and so that a second medium received at the second heat exchanger passes through the second heat exchanger. A compressing device is arranged in fluid communication with the ram air circuit.
    Type: Application
    Filed: February 5, 2018
    Publication date: January 3, 2019
    Inventors: Louis J. Bruno, Jeffrey Ernst, John M. Maljanian, Gregory L. DeFrancesco, Thomas M. Zywiak
  • Patent number: 10167778
    Abstract: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.
    Type: Grant
    Filed: April 28, 2017
    Date of Patent: January 1, 2019
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Donald E. Army, Gregory L. DeFrancesco, John M. Maljanian
  • Publication number: 20180281977
    Abstract: An airplane is provided. The airplane includes a motor-driven compressor assembly. The motor-driven compressor assembly includes a shaft, a motor, a compressor, and a turbine coupled to the compressor via the shaft. The motor provides a first power to the compressor via the shaft. The turbine receives and expands a second medium to provide a second power to the compressor via the shaft. The compressor receives and compresses a first medium in accordance with the first power provided by the turbine and the second power provided by the motor.
    Type: Application
    Filed: April 3, 2017
    Publication date: October 4, 2018
    Inventor: Gregory L. DeFrancesco
  • Publication number: 20180281976
    Abstract: An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, a turbine coupled to the compressor via the shaft; and a heat exchanger. The compressor receives and compresses a first medium in accordance with power provided by the turbine via the shaft. The turbine receives and expands a second medium to provide the power to the compressor via the shaft. The heat exchanger is configured to cool the first medium.
    Type: Application
    Filed: April 3, 2017
    Publication date: October 4, 2018
    Inventors: Thomas M. Zywiak, Gregory L. DeFrancesco, David E. Hall
  • Patent number: 10086946
    Abstract: An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, a turbine coupled to the compressor via the shaft; and a heat exchanger. The compressor receives and compresses a first medium in accordance with power provided by the turbine via the shaft. The turbine receives and expands a second medium to provide the power to the compressor via the shaft. The heat exchanger is configured to cool the first medium.
    Type: Grant
    Filed: April 3, 2017
    Date of Patent: October 2, 2018
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Thomas M. Zywiak, Gregory L. DeFrancesco, David E. Hall
  • Publication number: 20180215473
    Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and at least one compressing device is arranged in fluid communication with the ram air circuit and the dehumidification system. The at least one compressing device includes a turbine and a compressor operably coupled via a shaft. A fan is operably coupled to the ram air circuit. At least one compressing device is arranged non-linearly with the ram air circuit such that an axis of rotation of the fan is offset from the axis of the shaft.
    Type: Application
    Filed: April 11, 2017
    Publication date: August 2, 2018
    Inventors: Donald E. Army, Gregory L. DeFrancesco
  • Publication number: 20180215472
    Abstract: An environmental control system for providing conditioned air to a volume of an aircraft includes a ram air circuit including a ram air shell with at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and at least one compressing device is arranged in fluid communication with the ram air circuit and the dehumidification system. A plurality of mediums is receivable within the environmental control system. A first medium of the plurality of mediums is provided from the volume of the aircraft via at least one valve.
    Type: Application
    Filed: April 11, 2017
    Publication date: August 2, 2018
    Inventors: Gregory L. DeFrancesco, Donald E. Army
  • Publication number: 20180215474
    Abstract: An environmental control system of an aircraft includes a ram air circuit having a ram air shell with at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and a plurality of compressing devices is arranged in fluid communication with the ram air circuit and the dehumidification system.
    Type: Application
    Filed: April 11, 2017
    Publication date: August 2, 2018
    Inventors: Gregory L. DeFrancesco, Donald E. Army
  • Publication number: 20180215620
    Abstract: A flow sensing ozone converter includes an inlet housing, an outlet housing, and a central housing. The inlet housing defines a first pressure port. The outlet housing defines a second pressure port. The central housing extends between a second end of the inlet housing and a first end of the outlet housing.
    Type: Application
    Filed: January 27, 2017
    Publication date: August 2, 2018
    Inventors: Gregory L. DeFrancesco, Donald E. Army
  • Patent number: 9796477
    Abstract: An air compressing system is provided that includes a compressor configured to compressor air. An engine is operatively connected to the compressor. Further, an infinitely variable transmission is operatively connected between the engine and the compressor. A first shaft operatively connects the engine to the infinitely variable transmission and is configured to rotate at a first speed and a second shaft operatively connects the infinitely variable transmission to the compressor and is configured to rotate at a second speed.
    Type: Grant
    Filed: November 20, 2014
    Date of Patent: October 24, 2017
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Harold W. Hipsky, Gregory L. DeFrancesco
  • Publication number: 20170226926
    Abstract: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.
    Type: Application
    Filed: April 28, 2017
    Publication date: August 10, 2017
    Inventors: Donald E. Army, Gregory L . DeFrancesco, John M. Maljanian
  • Patent number: 9670842
    Abstract: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.
    Type: Grant
    Filed: January 14, 2011
    Date of Patent: June 6, 2017
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Donald E. Army, Gregory L. DeFrancesco, John M. Malijanian
  • Patent number: 9650967
    Abstract: A method for decreasing a throttle setting at which a gas turbine-powered aircraft must switch from low-pressure bleed air to a high-pressure bleed air. The method includes flowing low-pressure bleed air from a compressor at a first pressure. A first portion of the low-pressure bleed air is directed to an air-to-air heat exchanger and cooled in the air-to-air heat exchanger. The first portion of the low-pressure bleed air is flowed from the air-to air heat exchanger into a cooled bleed air line. A second portion of the low-pressure bleed air is directed to a low-pressure bypass line. The second portion of the low-pressure bleed air is flowed from the low-pressure bypass line into the cooled bleed air line upstream of an environmental control system.
    Type: Grant
    Filed: May 15, 2015
    Date of Patent: May 16, 2017
    Assignee: Hamiilton Sundstrand Corporation
    Inventor: Gregory L. DeFrancesco
  • Publication number: 20160167790
    Abstract: An air compressing system is provided that includes a compressor configured to compressor air. An engine is operatively connected to the compressor. Further, an infinitely variable transmission is operatively connected between the engine and the compressor. A first shaft operatively connects the engine to the infinitely variable transmission and is configured to rotate at a first speed and a second shaft operatively connects the infinitely variable transmission to the compressor and is configured to rotate at a second speed.
    Type: Application
    Filed: November 20, 2014
    Publication date: June 16, 2016
    Inventors: Harold W. Hipsky, Gregory L. DeFrancesco
  • Publication number: 20160090917
    Abstract: An engine bleed air system having one or more taps in the compressor section of an aircraft engine, for example a low pressure tap and a high pressure tap. The low pressure tap is fluidly connected to the compressor of a turbo-compressor and the high pressure tap is fluidly connected to the turbine of the turbo-compressor. A bypass line connects the high pressure air to the outlet of the compressor, with a heat exchanger used to remove excess heat from the bypass line. An additional heat exchanger is used to remove any excess heat from the compressed air, dumping the heat to a fan stream or to the expanded air exiting the turbine. The system is controlled to minimize the amount of high pressure air extracted from the engine.
    Type: Application
    Filed: September 30, 2014
    Publication date: March 31, 2016
    Inventors: Louis J. Bruno, Gregory L. DeFrancesco, Thomas M. Zywiak, Diane G. Drew, Harold W. Hipsky, Daniel L. Hughes
  • Publication number: 20150247463
    Abstract: A method for decreasing a throttle setting at which a gas turbine-powered aircraft must switch from low-pressure bleed air to a high-pressure bleed air. The method includes flowing low-pressure bleed air from a compressor at a first pressure. A first portion of the low-pressure bleed air is directed to an air-to-air heat exchanger and cooled in the air-to-air heat exchanger. The first portion of the low-pressure bleed air is flowed from the air-to air heat exchanger into a cooled bleed air line. A second portion of the low-pressure bleed air is directed to a low-pressure bypass line. The second portion of the low-pressure bleed air is flowed from the low-pressure bypass line into the cooled bleed air line upstream of an environmental control system.
    Type: Application
    Filed: May 15, 2015
    Publication date: September 3, 2015
    Inventor: Gregory L. DeFrancesco
  • Patent number: 9062604
    Abstract: A bleed air conditioning system within an aircraft including a low-pressure bleed air line and a high-pressure bleed air line. The system includes an air-to-air heat exchanger and an un-cooled bleed air line to connect the air-to-air heat exchanger to the low-pressure bleed air line and the high-pressure bleed air line. The un-cooled bleed air line carries a flow of un-cooled bleed air from at least one of the low-pressure bleed air line and the high-pressure bleed air line to the air-to-air heat exchanger. The system also includes a cooled bleed air line connected to the air-to-air heat exchanger for carrying cooled bleed air from the air-to-air heat exchanger and a low-pressure bypass line connecting the low-pressure bleed air line to the cooled bleed air line, bypassing un-cooled bleed air from the low-pressure line around the air-to-air heat exchanger to the cooled bleed air line.
    Type: Grant
    Filed: January 14, 2011
    Date of Patent: June 23, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Gregory L. DeFrancesco
  • Patent number: 8662445
    Abstract: A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft.
    Type: Grant
    Filed: July 29, 2013
    Date of Patent: March 4, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Louis J. Bruno, Anthony C. Jones, Todd A. Spierling, Gregory L. DeFrancesco