Patents by Inventor Mark E. Addis

Mark E. Addis 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: 9943932
    Abstract: The present application discloses a method for repairing a damaged counterbore in a variable vane shroud. A layer of base material is removed from the vane shroud adjacent the counterbore such that a damaged portion of the counterbore is removed. A shrink-fit insert having a size slightly larger than that corresponding to the layer of base material removed from the shroud is placed into the area of removed material such that the counterbore is restored to pre-damaged dimensions upon installation of the shrink-fit insert.
    Type: Grant
    Filed: April 18, 2016
    Date of Patent: April 17, 2018
    Assignee: United Technologies Corporation
    Inventors: Mark E. Addis, George H. Reynolds
  • Patent number: 9643286
    Abstract: The inventive method involves the inspection of a turbine engine. A damaged component of the turbine engine is identified. Portions of the turbine engine component are removed from the damaged area to accommodate an overlay. The overlay is sized smaller than the turbine engine component. The overlay is then placed in a location previously occupied by the removed portion and attached to the turbine engine component.
    Type: Grant
    Filed: April 5, 2007
    Date of Patent: May 9, 2017
    Assignee: United Technologies Corporation
    Inventors: George H. Reynolds, Mark E. Addis
  • Publication number: 20160221130
    Abstract: The present application discloses a method for repairing a damaged counterbore in a variable vane shroud. A layer of base material is removed from the vane shroud adjacent the counterbore such that a damaged portion of the counterbore is removed. A shrink-fit insert having a size slightly larger than that corresponding to the layer of base material removed from the shroud is placed into the area of removed material such that the counterbore is restored to pre-damaged dimensions upon installation of the shrink-fit insert.
    Type: Application
    Filed: April 18, 2016
    Publication date: August 4, 2016
    Inventors: Mark E. Addis, George H. Reynolds
  • Patent number: 9404374
    Abstract: A vane shroud for a gas turbine engine has a cylindrical shaped body and a hole arranged at a circumference of the body. The hole is for receiving a trunnion from a variable vane. A counterbore is arranged concentrically around the hole on a radially inward facing surface of the body, and receives a trunnion hub from the variable vane. A shrink-fit insert is seated into the counterbore such that the trunnion hub is provided with a contact surface, and the shrink-fit insert is secured to the shroud through an interference fit.
    Type: Grant
    Filed: April 9, 2008
    Date of Patent: August 2, 2016
    Assignee: United Technologies Corporation
    Inventors: Mark E. Addis, George H. Reynolds
  • Patent number: 8727354
    Abstract: A brush seal assembly is disclosed that includes bristles arranged circumferentially about an axis to provide a bristle assembly. First and second plates are secured about the bristle assembly to provide a subassembly. A circumference of the subassembly is pressed into a retaining ring to provide the brush seal assembly. The circumference need not be machined. A perimeter weld is no longer needed to secure the first and second plates and bristle assembly to one another to provide the brush seal assembly.
    Type: Grant
    Filed: January 15, 2008
    Date of Patent: May 20, 2014
    Assignee: United Technologies Corporation
    Inventor: Mark E. Addis
  • Patent number: 8727353
    Abstract: A brush seal adapted to restrict a fluid flow through a gap between a first component and a second component, comprising: a body; a brush pack secured to the body; and a passage through the body for introducing a cooling flow to said gap. The passage has a first end that is exposed to the gap and a second end that is not exposed to the gap. The passage discharges a cooling flow to the brush seal, the cooling flow being discrete from the fluid flow.
    Type: Grant
    Filed: April 5, 2006
    Date of Patent: May 20, 2014
    Assignee: United Technologies Corporation
    Inventor: Mark E. Addis
  • Patent number: 8414254
    Abstract: A sealing assembly for a turbine engine has a brush configured to provide an air seal between an outer air seal segment and a blade. A support is provided for the brush and is configured for attachment to the outer air seal segment. The support is a flexible planar carrier having a first side and a second side. The brush extends from the first side while the second side is for attachment to the outer air seal segment. The flexible planar carrier has a stiffness less than a stiffness of the outer air seal segment.
    Type: Grant
    Filed: February 18, 2008
    Date of Patent: April 9, 2013
    Assignee: United Technologies Corporation
    Inventor: Mark E. Addis
  • Patent number: 8366115
    Abstract: A brush seal includes a plurality of bristles aligned in parallel to form a brush pack having a first end and a second end, and a joint securing the brush pack together. The joint is located centrally between the first end and the second end such that both the first end and the second end of the brush pack can form a sealing surface.
    Type: Grant
    Filed: June 30, 2011
    Date of Patent: February 5, 2013
    Assignee: United Technologies Corporation
    Inventor: Mark E. Addis
  • Publication number: 20130001883
    Abstract: A brush seal includes a plurality of bristles aligned in parallel to form a brush pack having a first end and a second end, and a joint securing the brush pack together. The joint is located centrally between the first end and the second end such that both the first end and the second end of the brush pack can form a sealing surface.
    Type: Application
    Filed: June 30, 2011
    Publication date: January 3, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Mark E. Addis
  • Patent number: 8181965
    Abstract: The present invention relates to replaceable brush seal assemblies for use with turbines such as industrial gas turbines. In accordance with the present invention, a brush seal assembly comprises a flange, a brush seal mounted to the flange, and retainers preventing rotation of the brush seal relative to the flange. A method of repairing a brush seal having a back plate, side plate, and bristles is also disclosed. The method comprises the steps of removing the side plate and the bristles from the back plate, and securing a second brush seal to the back plate.
    Type: Grant
    Filed: June 27, 2002
    Date of Patent: May 22, 2012
    Assignee: United Technologies Corporation
    Inventor: Mark E. Addis
  • Publication number: 20110110783
    Abstract: A vane shroud for a gas turbine engine has a cylindrical shaped body and a hole arranged at a circumference of the body. The hole is for receiving a trunnion from a variable vane. A counterbore is arranged concentrically around the hole on a radially inward facing surface of the body, and receives a trunnion hub from the variable vane. A shrink-fit insert is seated into the counterbore such that the trunnion hub is provided with a contact surface, and the shrink-fit insert is secured to the shroud through an interference fit.
    Type: Application
    Filed: April 9, 2008
    Publication date: May 12, 2011
    Applicant: United Technologies Corporation
    Inventors: Mark E. Addis, George H. Reynolds
  • Patent number: 7931276
    Abstract: A brush seal, comprising: a bristle arrangement with a plurality of bristles; and a joint securing the bristles together; plates flanking the bristle arrangement; and a feature on the plates to receive the joint. A brush seal, comprising: a plurality of bristles, each having a first end and an opposed second end; and plates receiving the bristles therebetween, each having a first end and a second end. The first ends of the bristles extend past the first end of the plates and the second ends of the bristles reside between the first and second ends of the plates. A method of repairing a brush seal, comprising the steps of: providing a brush seal having a bristle arrangement secured between plates; removing the bristle arrangement from the plates; providing a replacement bristle arrangement; and placing said replacement bristle arrangement between the plates.
    Type: Grant
    Filed: March 20, 2002
    Date of Patent: April 26, 2011
    Assignee: United Technologies Corporation
    Inventors: John A. Szymbor, Mark E. Addis
  • Patent number: 7722318
    Abstract: A variable vane shroud for a gas turbine engine comprises a cylindrically shaped body, a hole arranged at a circumference of the body, and a counterbore arranged concentrically around the hole on a radially inward facing surface of the body. The hole is for receiving a trunnion from a variable vane and the counterbore is for receiving a hub from the variable vane. A liner is inserted into the hole and counterbore such that the trunnion and hub are provided with a contact surface. The invention also provides a method for repairing a damaged counterbore in a variable vane shroud. A liner having a shape corresponding to a layer of material removed from the shroud is inserted into the void left by removing damaged material such that the counterbore is restored to pre-damaged dimensions.
    Type: Grant
    Filed: February 13, 2007
    Date of Patent: May 25, 2010
    Assignee: United Technologies Corporation
    Inventor: Mark E. Addis
  • Patent number: 7717671
    Abstract: A seal for restricting leakage of a fluid through a gap disposed between rotating and stationary components concentrically aligned within a gas turbine engine comprises a sealing member and a land. The sealing member is positioned on either the rotating or stationary component of the gas turbine engine and closes a gap between the rotating member and the stationary member. The land is positioned opposite the sealing member on either the rotating or stationary component of the gas turbine engine such that a clearance height is provided between the sealing member and the land. In one embodiment, the land is geometrically shaped according to expected changes in the gap and relative axial position of the sealing member and land during operation of the gas turbine engine. The sealing member and the land are positioned with respect to each other so that the clearance height is maintained approximately constant during operation of the gas turbine engine.
    Type: Grant
    Filed: October 16, 2006
    Date of Patent: May 18, 2010
    Assignee: United Technologies Corporation
    Inventor: Mark E. Addis
  • Publication number: 20090208330
    Abstract: A sealing assembly for a turbine engine has a brush configured to provide an air seal between an outer air seal segment and a blade. A support is provided for the brush and is configured for attachment to the outer air seal segment. The support is a flexible planar carrier having a first side and a second side. The brush extends from the first side while the second side is for attachment to the outer air seal segment. The flexible planar carrier has a stiffness less than a stiffness of the outer air seal segment.
    Type: Application
    Filed: February 18, 2008
    Publication date: August 20, 2009
    Inventor: Mark E. Addis
  • Patent number: 7572099
    Abstract: A turbine engine includes a first turbine structure that supports a seal. The seal is movable within a recess of the first turbine structure. The seal is arranged in close proximity to a seal land of a second turbine structure for preventing a fluid from leaking past the seal and seal land. A thermal expansion member interconnects the first turbine structure and the seal. The thermal expansion member expands in response to an increase in temperature to move the seal toward the seal land preventing the typical enlarged gap between the seal and seal land resulting from thermal growth. In one example, the thermal expansion member, which is arranged at each opposing end of a seal segment, is a bimetallic coil spring supported on the first turbine structure by a cage. A free end of the coil spring is secured to the seal at the opposing end portions.
    Type: Grant
    Filed: July 6, 2006
    Date of Patent: August 11, 2009
    Assignee: United Technologies Corporation
    Inventor: Mark E. Addis
  • Publication number: 20090179384
    Abstract: A brush seal assembly is disclosed that includes bristles arranged circumferentially about an axis to provide a bristle assembly. First and second plates are secured about the bristle assembly to provide a subassembly. A circumference of the subassembly is pressed into a retaining ring to provide the brush seal assembly. The circumference need not be machined. A perimeter weld is no longer needed to secure the first and second plates and bristle assembly to one another to provide the brush seal assembly.
    Type: Application
    Filed: January 15, 2008
    Publication date: July 16, 2009
    Inventor: Mark E. Addis
  • Publication number: 20090064500
    Abstract: The inventive method involves the inspection of a turbine engine. A damaged component of the turbine engine is identified. Portions of the turbine engine component are removed from the damaged area to accommodate an overlay. The overlay is sized smaller than the turbine engine component. The overlay is then placed in a location previously occupied by the removed portion and attached to the turbine engine component.
    Type: Application
    Filed: April 5, 2007
    Publication date: March 12, 2009
    Inventors: George H. Reynolds, Mark E. Addis
  • Publication number: 20090035477
    Abstract: Masks and related methods for repairing a gas turbine engine components are provided. A representative method includes using a self-coiling strip of material as a mask during application of a coating to a surface of the component.
    Type: Application
    Filed: July 30, 2007
    Publication date: February 5, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Mark E. Addis
  • Publication number: 20090000101
    Abstract: Methods for repairing gas turbines are provided. A representative method includes: identifying an affected area of a surface of a component of the gas turbine, the surface of the component defining a portion of a gas flow path through the gas turbine; applying an epoxy-based filler to the affected area; curing the epoxy-based filler; and blending the epoxy-based filler with the surface of the component.
    Type: Application
    Filed: June 29, 2007
    Publication date: January 1, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: George H Reynolds, Mark E Addis