Patents by Inventor Brendan T. McAuliffe

Brendan T. McAuliffe 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).

  • Work recovery system for a gas turbine engine utilizing an overexpanded, recuperated supercritical CO2 bottoming cycle
    Patent number: 11230948
    Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger is disposed in the primary flowpath downstream of the turbine section. The heat exchanger includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) bottoming cycle and a second outlet connected to the sCO2 bottoming cycle. The sCO2 bottoming cycle is an overexpanded, recuperated Brayton cycle.
    Type: Grant
    Filed: January 16, 2019
    Date of Patent: January 25, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Brendan T. McAuliffe, Joseph B. Staubach, Nagendra Somanath
  • WORK RECOVERY SYSTEM FOR A GAS TURBINE ENGINE UTILIZING AN OVEREXPANDED, RECUPERATED SUPERCRITICAL CO2 BOTTOMING CYCLE
    Publication number: 20200224589
    Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger is disposed in the primary flowpath downstream of the turbine section. The heat exchanger includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) bottoming cycle and a second outlet connected to the sCO2 bottoming cycle. The sCO2 bottoming cycle is an overexpanded, recuperated Brayton cycle.
    Type: Application
    Filed: January 16, 2019
    Publication date: July 16, 2020
    Inventors: Brendan T. McAuliffe, Joseph B. Staubach, Nagendra Somanath
  • WORK RECOVERY SYSTEM FOR A GAS TURBINE ENGINE UTILIZING AN OVEREXPANDED, RECUPERATED SUPERCRITICAL CO2 CYCLE DRIVEN BY COOLED COOLING AIR WASTE HEAT
    Publication number: 20200224557
    Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) work recovery cycle and a second outlet connected to the sCO2 work recovery cycle. The sCO2 work recovery cycle is an overexpanded, recuperated work recovery cycle.
    Type: Application
    Filed: January 16, 2019
    Publication date: July 16, 2020
    Inventors: Brendan T. McAuliffe, Joseph B. Staubach, Nagendra Somanath
  • WORK RECOVERY SYSTEM FOR A GAS TURBINE ENGINE UTILIZING A RECUPERATED SUPERCRITICAL CO2 CYCLE DRIVEN BY COOLED COOLING AIR WASTE HEAT
    Publication number: 20200224590
    Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) coolant circuit and a second outlet connected to the sCO2 work recovery cycle.
    Type: Application
    Filed: January 16, 2019
    Publication date: July 16, 2020
    Inventors: Brendan T. McAuliffe, Joseph B. Staubach, Nagendra Somanath
  • WORK RECOVERY SYSTEM FOR A GAS TURBINE ENGINE UTILIZING A RECUPERATED SUPERCRITICAL CO2 BOTTOMING CYCLE
    Publication number: 20200224588
    Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger is disposed in the primary flowpath downstream of the turbine section. The heat exchanger includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger further includes a second inlet fluidly connected to a supercritical CO2 (sCO2) bottoming cycle and a second outlet connected to the sCO2 coolant circuit. The sCO2 bottoming cycle is a recuperated Brayton cycle.
    Type: Application
    Filed: January 16, 2019
    Publication date: July 16, 2020
    Inventors: Nagendra Somanath, Brendan T. McAuliffe, Joseph B. Staubach