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).
-
Patent number: 11560839Abstract: A gas turbine engine includes, among other things, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, an inner shaft that interconnects the low pressure compressor and the low pressure turbine, an outer shaft that interconnects the high pressure compressor and the high pressure turbine, a bearing structure that supports at least one of the inner and outer shafts, and a buffer system. The buffer system prepares buffer air, communicates the buffer air to the bearing structure to pressurize a bearing compartment, and then from the bearing structure along at least one of the shafts.Type: GrantFiled: September 8, 2021Date of Patent: January 24, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: William K. Ackermann, Peter M. Munsell
-
Patent number: 11549387Abstract: A gas turbine engine includes a propulsor section, a compressor section including a first compressor, a front center body case structure that defines a first core flow path for core airflow into the first compressor, an intermediate case structure, a geared architecture, a propulsor shaft, a first bearing structure mounted to the front center body case structure, a bearing compartment passage structure in communication with the first bearing structure through the front center body case structure, and a turbine section.Type: GrantFiled: March 8, 2022Date of Patent: January 10, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis
-
Patent number: 11499476Abstract: 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: GrantFiled: July 27, 2020Date of Patent: November 15, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis
-
Publication number: 20220341341Abstract: A gas turbine engine includes a propulsor section, a compressor section including a first compressor, a front center body case structure that defines a first core flow path for core airflow into the first compressor, an intermediate case structure, a geared architecture, a propulsor shaft, a first bearing structure mounted to the front center body case structure, a bearing compartment passage structure in communication with the first bearing structure through the front center body case structure, and a turbine section.Type: ApplicationFiled: March 8, 2022Publication date: October 27, 2022Inventors: Peter M. Munsell, Philip S. Stripinis
-
Patent number: 11293299Abstract: A turbofan 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 rotationally support a fan shaft. A fan rotor bearing support structure extends radially inward from the front center body and at least partially supports the bearing structure. The fan rotor bearing support structure includes a passage that communicates buffer supply air from a hollow strut to the bearing structure.Type: GrantFiled: February 2, 2021Date of Patent: April 5, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis
-
Patent number: 11286852Abstract: 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: GrantFiled: September 12, 2019Date of Patent: March 29, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: William K. Ackermann, Peter M. Munsell
-
Publication number: 20210396177Abstract: A gas turbine engine includes, among other things, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, an inner shaft that interconnects the low pressure compressor and the low pressure turbine, an outer shaft that interconnects the high pressure compressor and the high pressure turbine, a bearing structure that supports at least one of the inner and outer shafts, and a buffer system. The buffer system prepares buffer air, communicates the buffer air to the bearing structure to pressurize a bearing compartment, and then from the bearing structure along at least one of the shafts.Type: ApplicationFiled: September 8, 2021Publication date: December 23, 2021Inventors: William K. Ackermann, Peter M. Munsell
-
Publication number: 20210310366Abstract: A turbofan 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 rotationally support a fan shaft. A fan rotor bearing support structure extends radially inward from the front center body and at least partially supports the bearing structure. The fan rotor bearing support structure includes a passage that communicates buffer supply air from a hollow strut to the bearing structure.Type: ApplicationFiled: February 2, 2021Publication date: October 7, 2021Inventors: Peter M. Munsell, Philip S. Stripinis
-
Patent number: 11098644Abstract: 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: GrantFiled: November 8, 2019Date of Patent: August 24, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis
-
Publication number: 20210071576Abstract: 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: ApplicationFiled: July 27, 2020Publication date: March 11, 2021Inventors: Peter M. Munsell, Philip S. Stripinis
-
Patent number: 10920603Abstract: 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: GrantFiled: February 3, 2020Date of Patent: February 16, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis
-
Publication number: 20200263604Abstract: 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: ApplicationFiled: November 8, 2019Publication date: August 20, 2020Inventors: Peter M. Munsell, Philip S. Stripinis
-
Patent number: 10731563Abstract: 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: GrantFiled: January 29, 2018Date of Patent: August 4, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis
-
Patent number: 10724431Abstract: 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: GrantFiled: January 31, 2012Date of Patent: July 28, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis
-
Publication number: 20200173302Abstract: 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: ApplicationFiled: February 3, 2020Publication date: June 4, 2020Inventors: Peter M. Munsell, Philip S. Stripinis
-
Publication number: 20200141315Abstract: 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: ApplicationFiled: September 12, 2019Publication date: May 7, 2020Inventors: William K. Ackermann, Peter M. Munsell
-
Publication number: 20200102886Abstract: 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: ApplicationFiled: September 27, 2018Publication date: April 2, 2020Inventors: Cheng-Zhang Wang, Thomas G. Phillips, David F. Cloud, Peter M. Munsell
-
Patent number: 10550713Abstract: 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: GrantFiled: March 29, 2018Date of Patent: February 4, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis
-
Patent number: 10550714Abstract: 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: GrantFiled: March 29, 2018Date of Patent: February 4, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis
-
Patent number: 10487734Abstract: 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: GrantFiled: April 7, 2014Date of Patent: November 26, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Peter M. Munsell, Philip S. Stripinis