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).

  • Patent number: 10502094
    Abstract: 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: Grant
    Filed: July 20, 2015
    Date of Patent: December 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nasr A. Shuaib, Jonathan L. Miller, M. Rifat Ullah
  • Patent number: 10443443
    Abstract: 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: Grant
    Filed: March 10, 2017
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Patent number: 10352195
    Abstract: 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: Grant
    Filed: January 10, 2017
    Date of Patent: July 16, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Publication number: 20180223690
    Abstract: 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: Application
    Filed: March 10, 2017
    Publication date: August 9, 2018
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Patent number: 9915175
    Abstract: 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: Grant
    Filed: July 15, 2015
    Date of Patent: March 13, 2018
    Assignee: United Technologies Corporation
    Inventors: Jonathan L. Miller, M Rifat Ullah
  • Publication number: 20170122127
    Abstract: 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: Application
    Filed: January 10, 2017
    Publication date: May 4, 2017
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Patent number: 9574459
    Abstract: 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: Grant
    Filed: April 2, 2014
    Date of Patent: February 21, 2017
    Assignee: United Technologies Corporation
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Publication number: 20170016350
    Abstract: 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: Application
    Filed: July 15, 2015
    Publication date: January 19, 2017
    Inventors: Jonathan L. Miller, M. Rifat Ullah
  • Patent number: 9482158
    Abstract: 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: Grant
    Filed: December 19, 2012
    Date of Patent: November 1, 2016
    Assignee: United Technologies Corporation
    Inventor: M. Rifat Ullah
  • Patent number: 9359912
    Abstract: 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: Grant
    Filed: January 10, 2011
    Date of Patent: June 7, 2016
    Assignee: United Technologies Corporation
    Inventors: M. Rifat Ullah, Jonathan Logan Miller, Leslie Charles Kurz
  • Publication number: 20160032765
    Abstract: 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: Application
    Filed: July 20, 2015
    Publication date: February 4, 2016
    Applicant: United Technologies Corporation
    Inventors: Nasr A. SHUAIB, Jonathan L. MILLER, M. Rifat ULLAH
  • Publication number: 20140255156
    Abstract: 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: Application
    Filed: April 2, 2014
    Publication date: September 11, 2014
    Applicant: United Technologies Corporation
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Patent number: 8770918
    Abstract: 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: Grant
    Filed: October 15, 2013
    Date of Patent: July 8, 2014
    Assignee: United Technologies Corporation
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Patent number: 8641366
    Abstract: 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: Grant
    Filed: March 7, 2013
    Date of Patent: February 4, 2014
    Assignee: United Technologies Corporation
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Publication number: 20120177486
    Abstract: 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: Application
    Filed: January 10, 2011
    Publication date: July 12, 2012
    Inventors: M. Rifat Ullah, Jonathan Logan Miller, Leslie Charles Kurz
  • Patent number: 8167314
    Abstract: 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: Grant
    Filed: March 31, 2009
    Date of Patent: May 1, 2012
    Assignee: United Technologies Corporation
    Inventor: M. Rifat Ullah
  • Publication number: 20100244385
    Abstract: 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: Application
    Filed: March 31, 2009
    Publication date: September 30, 2010
    Applicant: United Technologies Corporation
    Inventor: M. Rifat Ullah
  • Patent number: 6655695
    Abstract: A composite face seal having an annular seal rotor with a metal base portion and a radially extending flange. The flange having first and second axially facing surfaces. A first ceramic ring is mounted to the first surface of the flange by a first braze joint and a second ceramic ring is mounted to the second surface of the flange by a second braze joint. The composite face seal assembly further includes an annular stator having an axially facing surface that sealingly engages an axially facing surface of one of the ceramic rings. Each of the braze joints may comprise a molybdenum ring disposed between two braze rings or, for thicker seal assemblies, molybdenum and nickel rings disposed between braze rings.
    Type: Grant
    Filed: February 13, 2001
    Date of Patent: December 2, 2003
    Assignee: Honeywell International Inc.
    Inventors: Steven E. Sund, Charles J. Gasdaska, James V. Guiheen, Lennox Bruce, M. Rifat Ullah, William L. Giesler
  • Patent number: 6322081
    Abstract: A circumferential seal for sealing between a rotating shaft and a stationary housing circumscribing the shaft. The seal comprises a stator mounted to said housing and having a radially inward facing carbon portion and a rotor with a ceramic sealing member having a radially outward facing surface in rubbing contact with said carbon portion. The rotor also includes a metal clamping means for mounting the ceramic sealing member to the shaft. The clamping means includes an axial flexible clamping member, and a radial flexible clamping member that together clamp onto a mounting flange of the ceramic sealing member when exposed to the compressive force of a lockup assembly.
    Type: Grant
    Filed: July 11, 1997
    Date of Patent: November 27, 2001
    Assignee: Ceramic Engineering Consulting, Inc.
    Inventors: M Rifat Ullah, Michael F. O'Brien, Fred Fuller, Gary Boyd
  • Patent number: 5639096
    Abstract: Disclosed is an oil film cooled face seal that is comprised of an annular stator having a flat surface in rubbing contact with the flat sealing surface of a rotor. The rotor has a flange portion extending radially from a base portion. The base portion has a plurality of holes extending radially therethrough in fluid communication with a source of cooling oil. One side of the flange portion comprises the flat sealing surface. The opposite side, or backface, has a plurality of external radially spaced apart annular grooves criss-crossing a plurality of external circumferentially spaced apart substantially radial grooves. Each of the radial grooves is aligned with and in fluid communication with a corresponding hole in the base portion, and extends fully across the backface.
    Type: Grant
    Filed: July 11, 1996
    Date of Patent: June 17, 1997
    Assignee: AlliedSignal Inc.
    Inventor: M. Rifat Ullah