Patents by Inventor Peter M. Munsell

Peter M. Munsell 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: 20200263604
    Abstract: A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine. A method and a buffer system are also disclosed.
    Type: Application
    Filed: November 8, 2019
    Publication date: August 20, 2020
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 10731563
    Abstract: A method of designing a buffer system for a gas turbine engine according to an example of the present disclosure includes, among other things, configuring a heat exchanger to define a first inlet and a first outlet fluidly coupled to each other and a second inlet and a second outlet fluidly coupled to each other, configuring the first inlet to receive air from first and second air sources that are selectively fluidly coupled to the first inlet, configuring the second inlet to receive air from a third air source fluidly that is coupled to the second inlet, and configuring the first outlet to provide cooled pressurized air to multiple fluid-supplied areas that are located remotely from one another and that are fluidly coupled to the first outlet, the multiple fluid-supplied areas including a bearing compartment of a gas turbine engine.
    Type: Grant
    Filed: January 29, 2018
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 10724431
    Abstract: A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply and the second bleed air supply to communicate the buffer supply air to the portion of the gas turbine engine.
    Type: Grant
    Filed: January 31, 2012
    Date of Patent: July 28, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Publication number: 20200173302
    Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure is mounted to the front center body case structure to rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.
    Type: Application
    Filed: February 3, 2020
    Publication date: June 4, 2020
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Publication number: 20200141315
    Abstract: A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.
    Type: Application
    Filed: September 12, 2019
    Publication date: May 7, 2020
    Inventors: William K. Ackermann, Peter M. Munsell
  • Publication number: 20200102886
    Abstract: A gas turbine engine includes a compressor delivering air into a combustion section. The combustion section and the compressor are housed in a housing. An air supply system communicates through the housing to deliver air from a location between an upstream end of the compressor, and an upstream end of the combustor. A diffuser is positioned downstream of the compressor. An opening in the housing supplies air to the inlet end. The diffuser has an outer shroud and an inner shroud with intermediate vanes. The outer shroud ends at a location upstream of a downstream end of the inner shroud at locations circumferentially aligned with the inlet end. The outer shroud only ends at the upstream location at circumferential locations associated with the inlet end, but extends further downstream at other locations.
    Type: Application
    Filed: September 27, 2018
    Publication date: April 2, 2020
    Inventors: Cheng-Zhang Wang, Thomas G. Phillips, David F. Cloud, Peter M. Munsell
  • Patent number: 10550713
    Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.
    Type: Grant
    Filed: March 29, 2018
    Date of Patent: February 4, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 10550714
    Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and the front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.
    Type: Grant
    Filed: March 29, 2018
    Date of Patent: February 4, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 10487734
    Abstract: A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine. A method and a buffer system are also disclosed.
    Type: Grant
    Filed: April 7, 2014
    Date of Patent: November 26, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 10465549
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a low pressure compressor, and a high pressure compressor axially aft of the low pressure compressor. A first case structure defines a core flow path for core airflow into the low pressure compressor and has a forward end and an aft end. A second case structure defines a core flow path for core airflow into the high pressure compressor and is mounted to the aft end of the first case structure. A geared architecture is at least partially supported by the first case structure. A first bearing structure is mounted to the first case structure to rotationally support a fan shaft that connects with the geared architecture to drive the fan. A flex support provides a flexible attachment of the geared architecture within the first case structure. A fan drive turbine drives the geared architecture to drive the fan at a speed lower than a speed of the fan drive turbine.
    Type: Grant
    Filed: January 9, 2018
    Date of Patent: November 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 10415468
    Abstract: A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.
    Type: Grant
    Filed: February 6, 2012
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: William K. Ackermann, Peter M. Munsell
  • Patent number: 10119468
    Abstract: A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.
    Type: Grant
    Filed: February 6, 2012
    Date of Patent: November 6, 2018
    Assignee: United Technologies Corporation
    Inventors: Cheng-Zhang Wang, Thomas G. Phillips, David F. Cloud, Peter M. Munsell
  • Patent number: 10087782
    Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.
    Type: Grant
    Filed: March 12, 2014
    Date of Patent: October 2, 2018
    Assignee: United Technologies Corporation
    Inventors: Cheng-Zhang Wang, Jorn A. Glahn, David F. Cloud, Peter M. Munsell, Clifton J. Crawley, Jr., Robert Newman, Michelle Diana Stearns
  • Publication number: 20180216482
    Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.
    Type: Application
    Filed: March 29, 2018
    Publication date: August 2, 2018
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Publication number: 20180216483
    Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure and the front center body case structure rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.
    Type: Application
    Filed: March 29, 2018
    Publication date: August 2, 2018
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Publication number: 20180149035
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a low pressure compressor, and a high pressure compressor axially aft of the low pressure compressor. A first case structure defines a core flow path for core airflow into the low pressure compressor and has a forward end and an aft end. A second case structure defines a core flow path for core airflow into the high pressure compressor and is mounted to the aft end of the first case structure. A geared architecture is at least partially supported by the first case structure. A first bearing structure is mounted to the first case structure to rotationally support a fan shaft that connects with the geared architecture to drive the fan. A flex support provides a flexible attachment of the geared architecture within the first case structure. A fan drive turbine drives the geared architecture to drive the fan at a speed lower than a speed of the fan drive turbine.
    Type: Application
    Filed: January 9, 2018
    Publication date: May 31, 2018
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Publication number: 20180149088
    Abstract: A method of designing a buffer system for a gas turbine engine according to an example of the present disclosure includes, among other things, configuring a heat exchanger to define a first inlet and a first outlet fluidly coupled to each other and a second inlet and a second outlet fluidly coupled to each other, configuring the first inlet to receive air from first and second air sources that are selectively fluidly coupled to the first inlet, configuring the second inlet to receive air from a third air source fluidly that is coupled to the second inlet, and configuring the first outlet to provide cooled pressurized air to multiple fluid-supplied areas that are located remotely from one another and that are fluidly coupled to the first outlet, the multiple fluid-supplied areas including a bearing compartment of a gas turbine engine.
    Type: Application
    Filed: January 29, 2018
    Publication date: May 31, 2018
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 9885249
    Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure is mounted to the front center body case structure to rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.
    Type: Grant
    Filed: February 18, 2016
    Date of Patent: February 6, 2018
    Assignee: United Technologies Corporation
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 9879602
    Abstract: A gas turbine engine includes a fan, a compressor section fluidly connected to the fan, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor, and a buffer system. The buffer system includes a heat exchanger having a first inlet, a first outlet, a second inlet, and a second outlet. The first outlet is configured to provide a cooled pressurized fluid. The buffer system includes first and second air sources that are selectively fluidly coupled to the first inlet, and a third air source that are fluidly coupled to the second inlet. Multiple fluid-supplied areas are located remotely from one another and are fluidly coupled to the first outlet. The multiple fluid-supplied areas include a bearing compartment. A method and a buffer system are also disclosed.
    Type: Grant
    Filed: April 7, 2014
    Date of Patent: January 30, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 9416677
    Abstract: A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure is mounted to the front center body case structure to rotationally support a shaft driven by the geared architecture, the shaft drive a fan. A bearing compartment passage structure is in communication with the bearing structure through the front center body case structure. A method is also disclosed.
    Type: Grant
    Filed: June 22, 2015
    Date of Patent: August 16, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter M. Munsell, Philip S. Stripinis