Patents by Inventor Fuhua Ma

Fuhua Ma 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: 20230026997
    Abstract: A gas turbine engine includes a fan section that includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. A high spool includes a high pressure turbine that drives a high pressure compressor. The high pressure compressor includes a pressure ratio of greater than 6.5 and less than 11.5. A ratio of a product of a pressure ratio of the fan with a pressure ratio of the low pressure compressor pressure to the pressure ratio of the high pressure compressor is greater than 0.35 and less than 0.90. An exhaust gas exit temperature is greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off.
    Type: Application
    Filed: July 19, 2021
    Publication date: January 26, 2023
    Inventors: Stephen G. Pixton, Ronald S. Walther, Matthew R. Feulner, Fuhua Ma, Ozhan Turgut
  • Patent number: 8978387
    Abstract: The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted.
    Type: Grant
    Filed: December 21, 2010
    Date of Patent: March 17, 2015
    Assignee: General Electric Company
    Inventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi, Adam Rasheed, Brian Gene Brzek, Douglas Carl Hofer, Thomas Michael Lavertu, Fuhua Ma
  • Publication number: 20120192546
    Abstract: The present application provides a pulse detonation turbine engine. The pulse detonation turbine engine may include one or more pulse detonation combustors to produce a flow of combustion gases, a turbine positioned downstream of the pulse detonation combustors such that the flow of combustion gases drives the turbine, and a catalytic converter positioned downstream of the pulse detonation combustors such that the flow of combustion gases passes therethrough.
    Type: Application
    Filed: January 28, 2011
    Publication date: August 2, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Venkat Eswarlu Tangirala, Narendra Joshi, Danielle Kalitan, Fuhua Ma, Thomas Lavertu
  • Publication number: 20120151896
    Abstract: The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted.
    Type: Application
    Filed: December 21, 2010
    Publication date: June 21, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: VENKAT ESWARLU TANGIRALA, NARENDRA DIGAMBER JOSHI, ADAM RASHEED, Brian Gene Brzek, Douglas Carl Hofer, Thomas Michael Lavertu, Fuhua MA
  • Publication number: 20120151895
    Abstract: The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass includes a pump that raises the pressure of the bypass flow sufficient to deliver it to downstream stations of the engine that contain combustion products that are at a higher pressure than the compressor exit.
    Type: Application
    Filed: December 21, 2010
    Publication date: June 21, 2012
    Applicant: General Electric Company
    Inventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi, Adam Rasheed, Brian Gene Brzek, Douglas Carl Hofer, Thomas Michael Lavertu, Fuhua Ma