Patents by Inventor M Rifat Ullah
M Rifat Ullah 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: 11499442Abstract: A bearing compartment seal for a gas turbine engine includes at least one seal ring defining an axis and having a radially inward facing sealing surface and a seal runner having a support constructed of a first material and an interface portion constructed of a second material. The interface portion includes a radially outward facing surface. A first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.Type: GrantFiled: April 12, 2019Date of Patent: November 15, 2022Assignee: Raytheon Technologies CorporationInventors: Jonathan Logan Miller, M. Rifat Ullah
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Patent number: 11299997Abstract: A seal includes a seal runner, at least one seal ring, and a seal housing. The runner extends in an axial direction to a runner end face that faces a bearing. The ring is fixed to a static structure and has an inner surface engaging the seal runner and a first face that faces the bearing. The seal housing is fixed to the static structure and includes a first portion extending in an axial direction from the first face of the seal ring to a housing face that faces the bearing. The first portion has a first length extending from the first face of the seal ring to the housing face. The seal runner has a first runner portion with a second length that extends from the first face of the seal ring to the runner end face. The second length is at least 35% longer than the first length.Type: GrantFiled: August 21, 2019Date of Patent: April 12, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Jonathan Logan Miller, M Rifat Ullah
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Publication number: 20210054755Abstract: A seal includes a seal runner, at least one seal ring, and a seal housing. The runner extends in an axial direction to a runner end face that faces a bearing. The ring is fixed to a static structure and has an inner surface engaging the seal runner and a first face that faces the bearing. The seal housing is fixed to the static structure and includes a first portion extending in an axial direction from the first face of the seal ring to a housing face that faces the bearing. The first portion has a first length extending from the first face of the seal ring to the housing face. The seal runner has a first runner portion with a second length that extends from the first face of the seal ring to the runner end face. The second length is at least 35% longer than the first length.Type: ApplicationFiled: August 21, 2019Publication date: February 25, 2021Inventors: Jonathan Logan Miller, M Rifat Ullah
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Publication number: 20200325788Abstract: A bearing compartment seal for a gas turbine engine includes at least one seal ring defining an axis and having a radially inward facing sealing surface and a seal runner having a support constructed of a first material and an interface portion constructed of a second material. The interface portion includes a radially outward facing surface. A first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.Type: ApplicationFiled: April 12, 2019Publication date: October 15, 2020Inventors: Jonathan Logan Miller, M. Rifat Ullah
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Patent number: 10502094Abstract: The present disclosure relates to sealing systems for bearing compartments. In one embodiment, a sealing system includes a runner configured to extend circumferentially around a rotating component, the runner is formed of a material with low radial thermal growth and is configured to fit to the rotating component to remove heat away from the runner. The runner can include an outer surface configured to provide passive cooling for the runner in the bearing compartment. The sealing system can also include a seal configured to operate with the runner, wherein the seal includes a clearance seal on an air side of the runner. The runner can be configured to operate without direct oil cooling.Type: GrantFiled: July 20, 2015Date of Patent: December 10, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Nasr A. Shuaib, Jonathan L. Miller, M. Rifat Ullah
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Patent number: 10443443Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.Type: GrantFiled: March 10, 2017Date of Patent: October 15, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: M. Rifat Ullah, Robert E. Peters
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Patent number: 10352195Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.Type: GrantFiled: January 10, 2017Date of Patent: July 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: M. Rifat Ullah, Robert E. Peters
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Publication number: 20180223690Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.Type: ApplicationFiled: March 10, 2017Publication date: August 9, 2018Inventors: M. Rifat Ullah, Robert E. Peters
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Patent number: 9915175Abstract: A system is provided associated with an engine of an aircraft. The system includes a ring, a runner and at least one radially-oriented hole associated with the runner that is configured to supply oil to an interface between the runner and the ring. The at least one hole is contained within an axial projection of the ring.Type: GrantFiled: July 15, 2015Date of Patent: March 13, 2018Assignee: United Technologies CorporationInventors: Jonathan L. Miller, M Rifat Ullah
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Publication number: 20170122127Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.Type: ApplicationFiled: January 10, 2017Publication date: May 4, 2017Inventors: M. Rifat Ullah, Robert E. Peters
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Patent number: 9574459Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.Type: GrantFiled: April 2, 2014Date of Patent: February 21, 2017Assignee: United Technologies CorporationInventors: M. Rifat Ullah, Robert E. Peters
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Publication number: 20170016350Abstract: A system is provided associated with an engine of an aircraft. The system includes a ring, a runner and at least one radially-oriented hole associated with the runner that is configured to supply oil to an interface between the runner and the ring. The at least one hole is contained within an axial projection of the ring.Type: ApplicationFiled: July 15, 2015Publication date: January 19, 2017Inventors: Jonathan L. Miller, M. Rifat Ullah
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Patent number: 9482158Abstract: A turbomachine seal includes, among other things, a sealing member configured to be influenced by both hydrostatic and hydrodynamic forces when providing a seal.Type: GrantFiled: December 19, 2012Date of Patent: November 1, 2016Assignee: United Technologies CorporationInventor: M. Rifat Ullah
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Patent number: 9359912Abstract: A runner assembly for a circumferential seal assembly includes a runner defined about an axis. The runner has an inwardly extending runner mounting flange. A radially flexible clamp is engaged with the inwardly extending mounting flange. An axial spring is trapped between an axial retainer and the runner. The runner, the radially flexible clamp, the axial spring, and the axial retainer are co-rotatable about the axis. The axial retainer is radially inline with the runner and spaced from a radially inner surface of the runner such that there is a radial gap between the axial retainer and the radially inner surface of the runner permitting radial movement of the runner.Type: GrantFiled: January 10, 2011Date of Patent: June 7, 2016Assignee: United Technologies CorporationInventors: M. Rifat Ullah, Jonathan Logan Miller, Leslie Charles Kurz
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Publication number: 20160032765Abstract: The present disclosure relates to sealing systems for bearing compartments. In one embodiment, a sealing system includes a runner configured to extend circumferentially around a rotating component, the runner is formed of a material with low radial thermal growth and is configured to tit to the rotating component to remove heat away from the runner. The runner can include an outer surface configured to provide passive cooling for the runner in the bearing compartment. The sealing system can also include a seal configured to operate with the runner, wherein the seal includes a clearance seal on an air side of the runner. The runner can be configured to operate without direct oil cooling.Type: ApplicationFiled: July 20, 2015Publication date: February 4, 2016Applicant: United Technologies CorporationInventors: Nasr A. SHUAIB, Jonathan L. MILLER, M. Rifat ULLAH
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Publication number: 20140255156Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.Type: ApplicationFiled: April 2, 2014Publication date: September 11, 2014Applicant: United Technologies CorporationInventors: M. Rifat Ullah, Robert E. Peters
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Patent number: 8770918Abstract: A rotating element is associated with at least one bearing compartment that includes a bearing to support the rotating element. A seal resists leakage of lubricant outwardly of the bearing compartment and allows air to flow from a chamber across the seal and into the bearing compartment. The seal has a seal face facing a rotating face rotating with the rotating element. The seal is a non-contact seal. A gas turbine engine is also disclosed.Type: GrantFiled: October 15, 2013Date of Patent: July 8, 2014Assignee: United Technologies CorporationInventors: M. Rifat Ullah, Robert E. Peters
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Patent number: 8641366Abstract: A rotating element is associated with at least one bearing compartment that includes a bearing to support the rotating element. A seal resists leakage of lubricant outwardly of the bearing compartment and allows air to flow from a chamber across the seal and into the bearing compartment. The seal has a seal face facing a rotating face rotating with the rotating element. The seal is a non-contact seal. A gas turbine engine is also disclosed.Type: GrantFiled: March 7, 2013Date of Patent: February 4, 2014Assignee: United Technologies CorporationInventors: M. Rifat Ullah, Robert E. Peters
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Publication number: 20120177486Abstract: A runner assembly for a circumferential seal assembly includes a runner having an inwardly extending runner mounting flange, a flexible mounting structure and a retainer assembly therefore.Type: ApplicationFiled: January 10, 2011Publication date: July 12, 2012Inventors: M. Rifat Ullah, Jonathan Logan Miller, Leslie Charles Kurz
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Patent number: 8167314Abstract: According to the present invention, an annular face seal arrangement for a gas turbine engine is provided that includes a mounting ring, a mounting member, a rotor, and a stator. The mounting ring has a width extending between a first axial end and a second axial end. The mounting member has a clamp portion and a biasing portion. The clamp portion extends axially between a first clamping surface and a second clamping surface. The biasing portion includes a first segment and a second segment. The second segment has a width and a rotor contact surface. The rotor has a rotor seal surface and a clamp portion having a width. The stator has a stator seal surface that is aligned with the rotor seal surface. The mounting ring is disposed radially inside of the rotor and radially inside of at least part of the biasing portion, and is disposed in contact with the second clamping surface of the clamp portion. The rotor contact surface of the biasing portion is disposed in contact with the rotor.Type: GrantFiled: March 31, 2009Date of Patent: May 1, 2012Assignee: United Technologies CorporationInventor: M. Rifat Ullah