Patents by Inventor John Munson
John Munson 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: 20240009018Abstract: An abdominal wound support device is provided. The abdominal wound support device includes a frame. The frame includes a first end and a second end. A first pivotal member is placed on the first end of the frame. A second pivotal member is placed on the second end of the frame. A first handle is placed on the first pivotal member opposite the frame. A second handle is placed on the second pivotal member opposite the frame. A first roller is placed on the first pivotal member opposite the first handle. A second roller is placed on the second pivotal member opposite the second handle.Type: ApplicationFiled: July 6, 2022Publication date: January 11, 2024Inventor: John Munson
-
Patent number: 11326464Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.Type: GrantFiled: June 26, 2019Date of Patent: May 10, 2022Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Linnea Taketa, John Munson, Ted J. Freeman
-
Patent number: 11255436Abstract: A seal assembly is disclosed for sealing a high pressure fluid cavity from a low pressure fluid cavity. The cavities are at least partially disposed between a rotatable shaft and a sump housing. The seal assembly comprises a circumferential runner and a seal ring. The circumferential runner is carried by the shaft and has a radially outward facing seal surface extending axially along the shaft. The seal ring is sealing engaged with the sump housing and has a radially inward facing seal surface that sealingly engages the radially outward facing seal surface of the runner. The runner and the seal ring are formed from materials having coefficients of thermal expansion that are matched to effect sealing engagement between the runner and the seal ring over a predetermined range of operating temperatures.Type: GrantFiled: November 30, 2018Date of Patent: February 22, 2022Assignee: Rolls-Royce CorporationInventors: Daniel L. Fadgen, John Munson
-
Patent number: 11193594Abstract: An intershaft seal assembly comprises an annular seal ring disposed between a pair of annular runners connected to a hollow outer rotating shaft, and a surface of a co-axial inner rotating shaft. The centrifugal force resulting from rotation of the hollow outer rotating shaft effects engagement of the annular seal ring with the surface of the co-axial inner rotating shaft. The surface may be a radially-inward-facing surface of a retaining arm connected to the co-axial inner rotating shaft.Type: GrantFiled: July 22, 2019Date of Patent: December 7, 2021Assignee: Rolls-Royce CorporationInventor: John Munson
-
Publication number: 20200173557Abstract: A seal assembly is disclosed for sealing a high pressure fluid cavity from a low pressure fluid cavity. The cavities are at least partially disposed between a rotatable shaft and a sump housing. The seal assembly comprises a circumferential runner and a seal ring. The circumferential runner is carried by the shaft and has a radially outward facing seal surface extending axially along the shaft. The seal ring is sealing engaged with the sump housing and has a radially inward facing seal surface that sealingly engages the radially outward facing seal surface of the runner. The runner and the seal ring are formed from materials having coefficients of thermal expansion that are matched to effect sealing engagement between the runner and the seal ring over a predetermined range of operating temperatures.Type: ApplicationFiled: November 30, 2018Publication date: June 4, 2020Applicant: Rolls-Royce CorporationInventors: Daniel L. Fadgen, John Munson
-
Patent number: 10571028Abstract: A circumferential seal for a rotating machine having a ceramic runner and support system is provided. The circumferential seal may comprise a sealing runner having a radially inward facing surface and a mounting element. The mounting element may comprise a radial pilot, an axial flange, an isolating element, a spring element to provide an axially clamping force to the runner, and a support ring extending axially along a shaft a distance greater than the radially inward facing surface of the runner.Type: GrantFiled: February 7, 2017Date of Patent: February 25, 2020Assignee: ROLLS-ROYCE CORPORATIONInventors: Phillip Howard Burnside, John Munson
-
Patent number: 10520096Abstract: An intershaft seal assembly comprises an annular seal ring disposed between a pair of annular runners connected to a hollow outer rotating shaft, and a surface of a co-axial inner rotating shaft. The centrifugal force resulting from rotation of the hollow outer rotating shaft effects engagement of the annular seal ring with the surface of the co-axial inner rotating shaft. The surface may be a radially-inward-facing surface of a retaining arm connected to the co-axial inner rotating shaft.Type: GrantFiled: October 7, 2016Date of Patent: December 31, 2019Assignee: ROLLS-ROYCE CORPORATIONInventor: John Munson
-
Publication number: 20190346046Abstract: An intershaft seal assembly comprises an annular seal ring disposed between a pair of annular runners connected to a hollow outer rotating shaft, and a surface of a co-axial inner rotating shaft. The centrifugal force resulting from rotation of the hollow outer rotating shaft effects engagement of the annular seal ring with the surface of the co-axial inner rotating shaft. The surface may be a radially-inward-facing surface of a retaining arm connected to the co-axial inner rotating shaft.Type: ApplicationFiled: July 22, 2019Publication date: November 14, 2019Applicant: Rolls-Royce CorporationInventor: John Munson
-
Publication number: 20190330993Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.Type: ApplicationFiled: June 26, 2019Publication date: October 31, 2019Inventors: Linnea Taketa, John Munson, Ted J. Freeman
-
Patent number: 10415735Abstract: A flow splitter includes a stepped ring and a flow restriction. The stepped ring includes a first inner wall having a first diameter, a second inner wall having a second diameter less than the first diameter, a radial step that transitions from the first to the second inner wall, and a plurality of apertures circumferentially located along the first inner wall and partially through the radial step. The first flow restriction has at least a portion thereof at a position between the first diameter and the second diameter. Further, the first flow restriction directs a flow of at least one of a gas and a fluid towards the first inner wall, and is configured to split the flow into an exit flow and a secondary flow. The exit flow exits the stepped ring via the plurality of apertures and the secondary flow proceeds downstream directed by the second inner walls.Type: GrantFiled: June 10, 2016Date of Patent: September 17, 2019Assignee: Rolls-Royce CorporationInventors: John Munson, Phillip H. Burnside
-
Patent number: 10370995Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.Type: GrantFiled: November 28, 2017Date of Patent: August 6, 2019Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Linnea Taketa, John Munson, Ted J. Freeman
-
Publication number: 20190211700Abstract: A seal assembly for sealing a high pressure fluid cavity from a low pressure fluid cavity, the cavities at least partially disposed between a hollow rotating shaft and a co-axial rotating shaft at least partially disposed within the hollow rotating shaft, is provided. The seal assembly comprises a pair of annular axially-spaced runners and an annular seal ring positioned axially between the runners. The annular seal ring has an axial dimension, a radial dimension, and a radially-outward facing surface frictionally engaged with a surface rotating with the hollow rotating shaft. The cross-sectional area at any point along the circumference of the annular seal ring is less than the product of the axial dimension multiplied by the radial dimension of the annular seal ring at that point along the circumference.Type: ApplicationFiled: January 9, 2018Publication date: July 11, 2019Applicant: Rolls-Royce CorporationInventor: John Munson
-
Publication number: 20180291815Abstract: An intershaft seal assembly comprises an annular seal ring disposed between a pair of annular runners connected to a co-axial inner rotating shaft and a surface of a hollow outer rotating shaft. The centrifugal force resulting from rotation of the co-axial inner rotating shaft effects engagement of the annular seal ring with the surface of the hollow outer rotating shaft. The surface may be a radially-inward-facing surface of a retaining arm connected to the hollow outer rotating shaft. A lubricious coating is applied to one or more of the interfaces between the seal ring and adjacent components such as the runners and the retaining arm. The lubricious coating may maintain the coefficient of friction between the interfaces between the seal ring and adjacent components below 0.4 at the maximum rotational speed of the seal ring.Type: ApplicationFiled: April 10, 2017Publication date: October 11, 2018Applicant: Rolls-Royce CorporationInventors: John Munson, Joseph Black
-
Publication number: 20180180185Abstract: An intershaft seal assembly comprises an annular seal ring disposed between a pair of annular runners connected to a hollow outer rotating shaft, and a surface of a co-axial inner rotating shaft. The centrifugal force resulting from rotation of the hollow outer rotating shaft effects engagement of the annular seal ring with the surface of the co-axial inner rotating shaft. The surface may be a radially-inward-facing surface of a retaining arm connected to the co-axial inner rotating shaft.Type: ApplicationFiled: October 7, 2016Publication date: June 28, 2018Applicant: Rolls-Royce CorporationInventor: John Munson
-
Publication number: 20180156052Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.Type: ApplicationFiled: November 28, 2017Publication date: June 7, 2018Inventors: Linnea Taketa, John Munson, Ted J. Freeman
-
Patent number: 9938845Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.Type: GrantFiled: December 18, 2013Date of Patent: April 10, 2018Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Linnea Taketa, John Munson, Ted J. Freeman
-
Publication number: 20170234432Abstract: A circumferential seal for a rotating machine having a ceramic runner and support system is provided. The circumferential seal may comprise a sealing runner having a radially inward facing surface and a mounting element. The mounting element may comprise a radial pilot, an axial flange, an isolating element, a spring element to provide an axially clamping force to the runner, and a support ring extending axially along a shaft a distance greater than the radially inward facing surface of the runner.Type: ApplicationFiled: February 7, 2017Publication date: August 17, 2017Applicant: Rolls-Royce CorporationInventors: Phillip Howard Burnside, John Munson
-
Publication number: 20160369925Abstract: A flow splitter includes a stepped ring and a flow restriction. The stepped ring includes a first inner wall having a first diameter, a second inner wall having a second diameter less than the first diameter, a radial step that transitions from the first to the second inner wall, and a plurality of apertures circumferentially located along the first inner wall and partially through the radial step. The first flow restriction has at least a portion thereof at a position between the first diameter and the second diameter. Further, the first flow restriction directs a flow of at least one of a gas and a fluid towards the first inner wall, and is configured to split the flow into an exit flow and a secondary flow. The exit flow exits the stepped ring via the plurality of apertures and the secondary flow proceeds downstream directed by the second inner walls.Type: ApplicationFiled: June 10, 2016Publication date: December 22, 2016Applicant: Rolls-Royce CorporationInventors: John Munson, Phillip H. Burnside
-
Publication number: 20150003963Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be a variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.Type: ApplicationFiled: December 18, 2013Publication date: January 1, 2015Inventors: Linnea Taketa, John Munson, Ted J. Freeman
-
Patent number: 8657573Abstract: A circumferential sealing arrangement is disclosed herein. The circumferential sealing arrangement includes a seal runner operable to be fixed to a structure for concurrent rotation with the structure about an axis. The circumferential sealing arrangement also includes a housing that encircles the seal runner or is encircled by the seal runner. The circumferential sealing arrangement also includes a primary seal element at least partially disposed in the housing. The primary seal element includes a first surface cooperating with a second surface of the seal runner to form a circumferential seal between the primary seal element and the seal runner. The circumferential sealing arrangement also includes a secondary seal element positioned between the housing and the primary seal element on a first side of the primary seal element along the axis of rotation. A second side of the primary seal element along the axis of rotation opposite the first side seals against the housing.Type: GrantFiled: April 13, 2010Date of Patent: February 25, 2014Assignee: Rolls-Royce CorporationInventor: John Munson