Patents by Inventor Jorn Axel Glahn
Jorn Axel Glahn 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).
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Patent number: 11519285Abstract: A hydrostatic seal configured to be disposed between relatively rotatable components. The hydrostatic seal includes a seal carrier. The hydrostatic seal also includes a beam extending axially from a forward end to an aft end, the beam cantilevered to the seal carrier at one of the forward end and the aft end, the beam free at the other end. The hydrostatic seal further includes a bellows seal operatively coupled to the seal carrier and in contact with the beam.Type: GrantFiled: May 13, 2019Date of Patent: December 6, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Jorn Axel Glahn, Brian F. Hilbert
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Patent number: 11441448Abstract: A rotating seal rotatable about a rotational axis is provided. The rotating seal includes a body having a first surface disposable to face the rotational axis and a second surface disposable to contact with a stationary element. The body defines a cooling channel including one or more entrance channels respectively extending from the first surface, one or more exit channels and a plenum. The plenum extends circumferentially through the body and has a hot side adjacent to the second surface. The plenum is fluidly interposed between the one or more entrance channels and the one or more exit channels whereby fluid exiting the one or more entrance channels and entering the plenum impinges against the hot side.Type: GrantFiled: February 13, 2020Date of Patent: September 13, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Sin Chien Siw, Timothy Castaldo, Charles Joseph Banas, Jorn Axel Glahn
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Publication number: 20220162993Abstract: A gas turbine engine includes at least one shaft that interconnects a compressor section and a turbine section. A starter turbine provides torque to the at least one shaft during an engine start event. The starter turbine includes an air inlet and an outlet. A buffer air system is in fluid communication with the starter turbine and is configured to receive air associated with the outlet to supplement sealing of a bearing compartment sealing system.Type: ApplicationFiled: November 23, 2020Publication date: May 26, 2022Inventors: Nigel David Sawyers-Abbott, Jorn Axel Glahn
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Publication number: 20210340911Abstract: A gas turbine engine includes a fan rotor, a compressor section, a combustor section, and a turbine section. The turbine section is positioned downstream of the combustor section. A fan drive turbine in the turbine section, and a shaft connects the fan drive turbine to the fan rotor. An inlet duct is connected to a cooling air source and connected to a cooling compressor downstream of the fan drive turbine. The cooling compressor is connected to an air source, and connected to a turning duct for passing compressed air in an upstream direction through the shaft. A method is also disclosed.Type: ApplicationFiled: July 15, 2021Publication date: November 4, 2021Inventors: Gary D. Roberge, Jorn Axel Glahn
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Publication number: 20210254502Abstract: A rotating seal rotatable about a rotational axis is provided. The rotating seal includes a body having a first surface disposable to face the rotational axis and a second surface disposable to contact with a stationary element. The body defines a cooling channel including one or more entrance channels respectively extending from the first surface, one or more exit channels and a plenum. The plenum extends circumferentially through the body and has a hot side adjacent to the second surface. The plenum is fluidly interposed between the one or more entrance channels and the one or more exit channels whereby fluid exiting the one or more entrance channels and entering the plenum impinges against the hot side.Type: ApplicationFiled: February 13, 2020Publication date: August 19, 2021Inventors: Sin Chien Siw, Timothy Castaldo, Charles Joseph Banas, Jorn Axel Glahn
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Patent number: 11078843Abstract: A gas turbine engine includes a fan rotor, a compressor section, a combustor section, and a turbine section. The turbine section is positioned downstream of the combustor section. A fan drive turbine in the turbine section, and a shaft connects the fan drive turbine to the fan rotor. An inlet duct is connected to a cooling air source and connected to a cooling compressor downstream of the fan drive turbine. The cooling compressor is connected to an air source, and connected to a turning duct for passing compressed air in an upstream direction through the shaft. A method is also disclosed.Type: GrantFiled: May 31, 2018Date of Patent: August 3, 2021Assignee: Raytheon Technologies CorporationInventors: Gary D. Roberge, Jorn Axel Glahn
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Publication number: 20200362716Abstract: A hydrostatic seal configured to be disposed between relatively rotatable components. The hydrostatic seal includes a seal carrier. The hydrostatic seal also includes a beam extending axially from a forward end to an aft end, the beam cantilevered to the seal carrier at one of the forward end and the aft end, the beam free at the other end. The hydrostatic seal further includes a bellows seal operatively coupled to the seal carrier and in contact with the beam.Type: ApplicationFiled: May 13, 2019Publication date: November 19, 2020Inventors: Jorn Axel Glahn, Brian F. Hilbert
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Patent number: 10837318Abstract: This disclosure relates to a buffer system for a gas turbine engine. An exemplary gas turbine engine includes, among other features, a buffer manifold in an intershaft region. The buffer manifold is configured to direct a flow of air between a first air seal and a first oil seal, and to direct another flow of air between a second air seal and a second oil seal.Type: GrantFiled: January 8, 2019Date of Patent: November 17, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Jorn Axel Glahn, Taryn Narrow, Anthony Spagnoletti, Francis Parnin, Justin W. Heiss
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Patent number: 10815889Abstract: A gas turbine engine includes a first tap connected to a compressor section to deliver air at a first pressure. A heat exchanger is downstream of the first tap. A cooling air valve selectively blocks flow of cooling air across the heat exchanger. A cooling compressor is downstream of the heat exchanger and pressurizes the air from the first tap to a greater second pressure. A shut off valve selectively stops flow of the air between the heat exchanger and the cooling compressor. A controller controls the cooling air valve, the shut off valve, and the cooling compressor such that the flow of the air is stopped between the heat exchanger and the cooling compressor only after the controller has stopped the cooling compressor. A monitoring system communicates with the controller and includes a pressure sensor and a temperature sensor downstream of the cooling compressor.Type: GrantFiled: July 5, 2018Date of Patent: October 27, 2020Assignee: United Technologies CorporationInventors: Frederick M. Schwarz, Jorn Axel Glahn
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Patent number: 10774684Abstract: A gas turbine engine according to an example of the present disclosure includes a shaft rotatable about an axis, a bearing disposed about the shaft and within a bearing compartment, and a seal assembly positioned to seal the bearing compartment. The seal assembly includes a fixed seal and a seal runner rotatable with the shaft. The first axial face and a second axial face axially opposite the first axial face with respect to the axis. The first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion. A second surface is angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface. An oil source is positioned to provide oil into the trough portion.Type: GrantFiled: October 24, 2018Date of Patent: September 15, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Jorn Axel Glahn, Denman H. James, Anthony Sr. Demitraszek
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Patent number: 10767510Abstract: A seal seat includes an annular body and an extension. The annular body is disposed about a centerline axis. The extension is connected to and extends radially outward from the annular body. The extension includes first, second, and third portions. The first portion is connected to the annular body and is defined by axially opposed upstream and downstream wall faces. The first portion includes a fin connected to the upstream wall face. The second portion is connected to the first portion and extends substantially parallel to the annular body. The third portion is connected to the second portion and extends substantially parallel to the second portion.Type: GrantFiled: February 6, 2019Date of Patent: September 8, 2020Assignee: United Technologies CorporationInventors: Armando Amador, Todd A. Davis, Jorn Axel Glahn
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Publication number: 20200248585Abstract: A seal seat includes an annular body and an extension. The annular body is disposed about a centerline axis. The extension is connected to and extends radially outward from the annular body. The extension includes first, second, and third portions. The first portion is connected to the annular body and is defined by axially opposed upstream and downstream wall faces. The first portion includes a fin connected to the upstream wall face. The second portion is connected to the first portion and extends substantially parallel to the annular body. The third portion is connected to the second portion and extends substantially parallel to the second portion.Type: ApplicationFiled: February 6, 2019Publication date: August 6, 2020Inventors: Armando Amador, Todd A. Davis, Jorn Axel Glahn
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Publication number: 20200217220Abstract: This disclosure relates to a buffer system for a gas turbine engine. An exemplary gas turbine engine includes, among other features, a buffer manifold in an intershaft region. The buffer manifold is configured to direct a flow of air between a first air seal and a first oil seal, and to direct another flow of air between a second air seal and a second oil seal.Type: ApplicationFiled: January 8, 2019Publication date: July 9, 2020Inventors: Jorn Axel Glahn, Taryn Narrow, Anthony Spagnoletti, Francis Parnin, Justin W. Heiss
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Publication number: 20200131935Abstract: A gas turbine engine according to an example of the present disclosure includes a shaft rotatable about an axis, a bearing disposed about the shaft and within a bearing compartment, and a seal assembly positioned to seal the bearing compartment. The seal assembly includes a fixed seal and a seal runner rotatable with the shaft. The first axial face and a second axial face axially opposite the first axial face with respect to the axis. The first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion. A second surface is angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface. An oil source is positioned to provide oil into the trough portion.Type: ApplicationFiled: October 24, 2018Publication date: April 30, 2020Inventors: Jorn Axel Glahn, Denman H. James, Anthony Sr. Demitraszek
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Publication number: 20200011247Abstract: A gas turbine engine includes a first tap connected to a compressor section to deliver air at a first pressure. A heat exchanger is downstream of the first tap. A cooling air valve selectively blocks flow of cooling air across the heat exchanger. A cooling compressor is downstream of the heat exchanger and pressurizes the air from the first tap to a greater second pressure. A shut off valve selectively stops flow of the air between the heat exchanger and the cooling compressor. A controller controls the cooling air valve, the shut off valve, and the cooling compressor such that the flow of the air is stopped between the heat exchanger and the cooling compressor only after the controller has stopped the cooling compressor. A monitoring system communicates with the controller and includes a pressure sensor and a temperature sensor downstream of the cooling compressor.Type: ApplicationFiled: July 5, 2018Publication date: January 9, 2020Inventors: Frederick M. Schwarz, Jorn Axel Glahn
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Publication number: 20190368419Abstract: A gas turbine engine includes a fan rotor, a compressor section, a combustor section, and a turbine section. The turbine section is positioned downstream of the combustor section. A fan drive turbine in the turbine section, and a shaft connects the fan drive turbine to the fan rotor. An inlet duct is connected to a cooling air source and connected to a cooling compressor downstream of the fan drive turbine. The cooling compressor is connected to an air source, and connected to a turning duct for passing compressed air in an upstream direction through the shaft. A method is also disclosed.Type: ApplicationFiled: May 31, 2018Publication date: December 5, 2019Inventors: Gary D. Roberge, Jorn Axel Glahn