Patents by Inventor Robert Russell Mayer
Robert Russell Mayer 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: 11939924Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.Type: GrantFiled: October 3, 2022Date of Patent: March 26, 2024Assignee: RTX CORPORATIONInventors: Nicholas W. Kantany, Edward Boucher, Kristine Marie Carnavos, Robert Russell Mayer, Donald W. Peters
-
Publication number: 20230029935Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.Type: ApplicationFiled: October 3, 2022Publication date: February 2, 2023Applicant: Raytheon Technologies CorporationInventors: Nicholas W. Kantany, Edward Boucher, Kristine Marie Carnavos, Robert Russell Mayer, Donald W. Peters
-
Patent number: 11492977Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.Type: GrantFiled: June 5, 2019Date of Patent: November 8, 2022Assignee: Raytheon Technologies CorporationInventors: Nicholas W. Kantany, Edward Boucher, Kristine Marie Carnavos, Robert Russell Mayer, Donald W. Peters
-
Patent number: 10927687Abstract: A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.Type: GrantFiled: December 3, 2018Date of Patent: February 23, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Chris Vargas, Robert Russell Mayer
-
Patent number: 10753279Abstract: A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.Type: GrantFiled: August 5, 2015Date of Patent: August 25, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Robert Russell Mayer, George J. Kramer, Paul W. Palmer
-
Publication number: 20190323435Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.Type: ApplicationFiled: June 5, 2019Publication date: October 24, 2019Applicant: United Technologies CorporationInventors: Nicholas W. Kantany, Edward Boucher, Kristine Marie Carnavos, Robert Russell Mayer, Donald W. Peters
-
Patent number: 10352248Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.Type: GrantFiled: July 29, 2015Date of Patent: July 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Nicholas W. Kantany, Edward Boucher, Kristine Marie Carnavos, Robert Russell Mayer, Donald W. Peters
-
Publication number: 20190106996Abstract: A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.Type: ApplicationFiled: December 3, 2018Publication date: April 11, 2019Inventors: Chris Vargas, Robert Russell Mayer
-
Patent number: 10167727Abstract: A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.Type: GrantFiled: July 8, 2015Date of Patent: January 1, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Chris Vargas, Robert Russell Mayer
-
Patent number: 9995171Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.Type: GrantFiled: January 16, 2015Date of Patent: June 12, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Andrew D. Burdick, Anthony P. Cherolis, Christopher Treat, Jonathan Lemoine, Robert Russell Mayer, Jorge I. Farah, John H. Mosley
-
Publication number: 20160341075Abstract: A gas turbine engine includes a core assembly with a core case having a containment section for containing liberated compressor and turbine blades and blade fragments. The containment section includes first and second containment layers and the containment section is configured to have a non-linear rate of energy dissipation across the first and second containment layers, thereby to improve containment of blades and blade fragments.Type: ApplicationFiled: August 15, 2014Publication date: November 24, 2016Inventors: Shu Liu, Robert Russell Mayer, Paul W. Palmer, Peter Balawajder, Igor S. Garcia, David C. Pimenta, Stephanie Ernst, Fernando K. Grant, Eric Baker, Andrew S. Miller
-
Publication number: 20160341070Abstract: A gas turbine engine includes a containment ring to contain liberated compressor and turbine blades and blade fragments within a core assembly. The combination of a containment gap between the core case and the containment ring and a containment layer disposed in the gap helps dissipate the energy generated by loose body impacts on the core assembly. The containment layer deforms, deflects, and/or redirects the impact energy acting in a radial direction, thereby to improve containment.Type: ApplicationFiled: August 14, 2014Publication date: November 24, 2016Applicant: United Technologies CorporationInventors: Igor S. Garcia, Shu Liu, Robert Russell Mayer, Eric Baker, Stephanie Ernst, Fernando K. Grant, Andrew S. Miller, Peter Balawajder, Paul W. Palmer
-
Publication number: 20160208644Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.Type: ApplicationFiled: January 16, 2015Publication date: July 21, 2016Inventors: Andrew D. Burdick, Anthony P. Cherolis, Christopher Treat, Jonathan Lemoine, Robert Russell Mayer, Jorge I. Farah, John H. Mosley
-
Publication number: 20160097327Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.Type: ApplicationFiled: July 29, 2015Publication date: April 7, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Nicholas W. Kantany, Edward Boucher, Kristine Marie Carnavos, Robert Russell Mayer, Donald W. Peters
-
Publication number: 20160047255Abstract: A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.Type: ApplicationFiled: July 8, 2015Publication date: February 18, 2016Inventors: Chris Vargas, Robert Russell Mayer
-
Patent number: 9255487Abstract: A gas turbine engine includes a seal assembly that is supported by a member at a joint. The seal assembly includes a seal support having a radial flange secured to the joint. A first bend adjoins the radial flange to a first leg, which is oriented generally in an axial direction. A second bend adjoins the first leg to a second leg, which is conical in shape. A seal is supported by the second leg.Type: GrantFiled: January 31, 2012Date of Patent: February 9, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Robert Russell Mayer, Paul W. Palmer, Jonathan Lemoine
-
Publication number: 20150337732Abstract: A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.Type: ApplicationFiled: August 5, 2015Publication date: November 26, 2015Inventors: Robert Russell Mayer, George J. Kramer, Paul W. Palmer
-
Patent number: 9140137Abstract: A gas turbine engine includes high and low pressure turbines. A mid turbine frame is arranged axially between the high and low pressure turbines. A bearing is operatively supported by a support structure. An inner case is secured to the support structure and includes a first conical member and a bearing support to which the bearing is mounted. The bearing support includes a second conical member that is secured to the first conical member at a joint. The first and second conical members are arranged radially inward of the joint.Type: GrantFiled: January 31, 2012Date of Patent: September 22, 2015Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Robert Russell Mayer, George J. Kramer, Paul W. Palmer
-
Publication number: 20130192260Abstract: A gas turbine engine includes a seal assembly that is supported by a member at a joint. The seal assembly includes a seal support having a radial flange secured to the joint. A first bend adjoins the radial flange to a first leg, which is oriented generally in an axial direction. A second bend adjoins the first leg to a second leg, which is conical in shape. A seal is supported by the second leg.Type: ApplicationFiled: January 31, 2012Publication date: August 1, 2013Inventors: Robert Russell Mayer, Paul W. Palmer, Jonathan Lemoine
-
Publication number: 20130192261Abstract: A gas turbine engine includes high and low pressure turbines. A mid turbine frame is arranged axially between the high and low pressure turbines. A bearing is operatively supported by a support structure. An inner case is secured to the support structure and includes a first conical member and a bearing support to which the bearing is mounted. The bearing support includes a second conical member that is secured to the first conical member at a joint. The first and second conical members are arranged radially inward of the joint.Type: ApplicationFiled: January 31, 2012Publication date: August 1, 2013Inventors: Robert Russell Mayer, George J. Kramer, Paul W. Palmer