Patents by Inventor Christopher W. Strock

Christopher W. Strock 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).

  • GAS TURBINE ENGINE COMPONENT COATING WITH SELF-HEALING BARRIER LAYER
    Publication number: 20200024749
    Abstract: A method of providing a self-healing coating includes providing substrate, applying a layer of an aluminum-containing MAX phase material and another material to the substrate. The method includes exposing the layer to a temperature greater than 2000° F. to form alpha aluminum.
    Type: Application
    Filed: April 29, 2019
    Publication date: January 23, 2020
    Inventors: Christopher W. Strock, Shahram Amini
  • TURBINE ABRASIVE BLADE TIPS WITH IMPROVED RESISTANCE TO OXIDATION
    Publication number: 20200024975
    Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 1750 degree Fahrenheit, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material and a thermal barrier coating material applied over said film of oxidant resistant coating.
    Type: Application
    Filed: July 19, 2018
    Publication date: January 23, 2020
    Applicant: United Technologies Corporation
    Inventors: Christopher W. Strock, Kevin Seymour
  • Abradable seal having nanolayer material
    Patent number: 10539036
    Abstract: A gas turbine engine includes a plurality of circumferentially-spaced blades. The blades have a polymeric coating thereon. An abradable seal circumscribes the blades and includes a polymeric matrix with a dispersion of a nanolayer material.
    Type: Grant
    Filed: January 8, 2015
    Date of Patent: January 21, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Shahram Amini, Christopher W. Strock
  • Gas turbine engine component with abrasive surface formed by electrical discharge machining
    Patent number: 10533439
    Abstract: A component for a gas turbine engine is described. The component may comprise a body portion formed from a metallic material. The component may further comprise an abrasive surface forming at least one surface of the body portion, and the abrasive surface may be configured to abrade an abradable material. The abrasive surface may be formed from electrical discharge machining of the metallic material.
    Type: Grant
    Filed: November 6, 2015
    Date of Patent: January 14, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Changsheng Guo, Christopher W. Strock
  • Corrosion-resistant aluminum-based abradable coatings
    Patent number: 10525529
    Abstract: A coated article comprising: a substrate; and a coating on the substrate comprising: a metallic matrix comprising, by weight: Al as a largest constituent; 3.0-6.0 Cr; 1.5-4.0 Mn; 0.1-3.5 Co; and 0.3-2.0 Zr; and a filler and optionally porosity.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: January 7, 2020
    Assignee: United Technologies Corporation
    Inventors: Pantcho P. Stoyanov, Christopher W. Strock, Thomas J. Watson
  • Abradable layer with glass microballoons
    Patent number: 10526908
    Abstract: A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.
    Type: Grant
    Filed: April 25, 2017
    Date of Patent: January 7, 2020
    Assignee: United Technologies Corporation
    Inventors: Kevin Seymour, Christopher W. Strock
  • FAN BLADES WITH ABRASIVE TIPS
    Publication number: 20200003225
    Abstract: A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing ling edge, a convex side, a concave side and a distal tip. The leading edge, trailing edge, convex side and concave side of the airfoil is at least partially coated with an erosion resistant coating. The distal tip of the airfoil is coated with a bonded abrasive coating. The bonded abrasive coating engages the abradable coating disposed on the fan liner and, because of its low thermal conductivity, reduces heat transfer to the distal tip of the fan blade. The reduction in heat transfer to the distal tip of the fan blade preserves the integrity of erosion resistant coatings that may be applied to the body or the airfoil of the fan blade.
    Type: Application
    Filed: September 9, 2019
    Publication date: January 2, 2020
    Inventors: Christopher W. Strock, Changsheng Guo
  • CHEMISTRY BASED METHODS OF MANUFACTURE FOR MAXMET COMPOSITE POWDERS
    Publication number: 20200003125
    Abstract: A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle.
    Type: Application
    Filed: August 13, 2019
    Publication date: January 2, 2020
    Applicant: United Technologies Corporation
    Inventors: Shahram Amini, Christopher W. Strock, Weina Li
  • Fusible bond for gas turbine engine coating system
    Patent number: 10513942
    Abstract: A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond strength greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine, and a method of forming a coating layer are also disclosed.
    Type: Grant
    Filed: November 4, 2014
    Date of Patent: December 24, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher W. Strock, Enzo DiBenedetto
  • TURBINE ENGINE COMPONENT WITH VIBRATION DAMPING
    Publication number: 20190383164
    Abstract: A vibration resistant fan guide vane for a gas turbine engine is provided. The fan guide vane comprises a vibration damping component made of a MAXMET composite. The damping component may be a cover that covers some or all of the fan guide vane body. Alternatively, portions of the fan guide vane body or the entire vane body may be made from MAXMET composites. The disclosure makes use of the ultrahigh, fully reversible, non-linear elastic hysteresis behavior that MAXMET composites exhibit during cyclic elastic deformation in order to damp vibration.
    Type: Application
    Filed: December 31, 2018
    Publication date: December 19, 2019
    Inventors: Shahram Amini, Christopher W. Strock, Sergei F. Burlatsky, Dmitri Novikov
  • Blade rub material
    Patent number: 10480330
    Abstract: A rub material (124) comprises a polymeric matrix (128) and polymeric micro-balloons (130) in the matrix.
    Type: Grant
    Filed: May 9, 2019
    Date of Patent: November 19, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher W. Strock, Changsheng Guo
  • Abrasive tip blade manufacture methods
    Patent number: 10472729
    Abstract: A method is provided for manufacturing a blade. The blade comprises an airfoil (100) having: a root end and a tip (106); a metallic substrate (102) along at least a portion of the airfoil; and an anodized layer (154). The method comprises roughening the tip to form protrusions (158?; 402?) and anodizing to form the anodized layer so that the protrusions form an abrasive (156; 400).
    Type: Grant
    Filed: May 24, 2018
    Date of Patent: November 12, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher W. Strock, James O. Hansen
  • Edge treatment for gas turbine engine component
    Patent number: 10472981
    Abstract: A gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, a body having a first outer face meeting a second outer face at an intersection, the body having a plurality of apertures extending from an opening in the first outer face to an opening on the second outer face; and a coating filling at least a portion of the plurality of apertures.
    Type: Grant
    Filed: January 30, 2014
    Date of Patent: November 12, 2019
    Assignee: United Technologies Corporation
    Inventors: John R. Farris, Christopher W. Strock, Paul M. Lutjen
  • Thermal-sprayed bonding of a ceramic structure to a substrate
    Patent number: 10458256
    Abstract: A thermal barrier system includes a protective coating on a substrate, and a ceramic feature layer attached to the protective coating via an adhesive spray coat.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: October 29, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher W Strock, Paul M Lutjen
  • THERMAL-SPRAYED BONDING OF A CERAMIC STRUCTURE TO A SUBSTRATE
    Publication number: 20190323365
    Abstract: A thermal barrier system includes a protective coating on a substrate, and a ceramic feature layer attached to the protective coating via an adhesive spray coat.
    Type: Application
    Filed: June 28, 2019
    Publication date: October 24, 2019
    Applicant: United Technologies Corporation
    Inventors: Christopher W. Strock, Paul M. Lutjen
  • Abrasive tip blade manufacture methods
    Patent number: 10450876
    Abstract: A blade comprises an airfoil having a root end and a tip. A metallic substrate is along at least a portion of the airfoil. An abrasive tip coating comprises an abrasive and an aluminum-based matrix. An aluminum-based base layer is between the tip coating and the substrate.
    Type: Grant
    Filed: April 15, 2015
    Date of Patent: October 22, 2019
    Assignee: United Technologies Corporation
    Inventor: Christopher W. Strock
  • Cost effective manufacturing method for GSAC incorporating a stamped preform
    Patent number: 10443444
    Abstract: A process for manufacturing a preformed sheet having geometric surface features for a geometrically segmented abradable ceramic thermal barrier coating on a turbine engine component, the process comprising the steps of providing a preformed sheet material. The process includes forming a partially of geometric surface features in the sheet material. The process includes joining the sheet material to a substrate of the turbine engine component. The process includes disposing a thermally insulating topcoat over the geometric surface features and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the geometric surface features.
    Type: Grant
    Filed: May 19, 2015
    Date of Patent: October 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher W Strock, Paul M Lutjen
  • CALCIUM-MAGNESIUM ALUMINO-SILICATE (CMAS) RESISTANT THERMAL BARRIER COATINGS, SYSTEMS, AND METHODS OF PRODUCTION THEREOF
    Publication number: 20190308910
    Abstract: The thermal barrier coating includes reactive gadolinia in its microstructures and the embedded gadolinia effectively reacts with CMAS contaminant reducing the damage from CMAS. Moreover, a method to produce a CMAS resistant thermal barrier coating can include a post-treatment to the thermal barrier coating with the reactive gadolinia suspension in sol-gel state.
    Type: Application
    Filed: June 17, 2019
    Publication date: October 10, 2019
    Inventor: Christopher W. Strock
  • Fire containment coating system for titanium
    Patent number: 10435776
    Abstract: A blade outer air seal (BOAS) or segment thereof comprises: a metallic substrate having an inner diameter (ID) surface; and a coating system along the inner diameter surface comprises: a bondcoat atop the substrate; and a ceramic barrier coat atop the bondcoat. The bondcoat has a combined content of one or more of molybdenum, chromium, and vanadium of at least 50 percent by weight.
    Type: Grant
    Filed: November 3, 2017
    Date of Patent: October 8, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher W. Strock, Matthew E. Bintz
  • Abrasive blade tips with additive resistant to clogging by organic matrix abradable
    Patent number: 10422242
    Abstract: A method of applying an additive to an abrasive coated blade tip comprises applying the additive to the abrasive coated blade tip and wicking the additive into the abrasive coated blade tip, wherein the additive is configured to prevent adhesion of an organic component of an abradable seal onto the abrasive coated blade tip.
    Type: Grant
    Filed: April 29, 2016
    Date of Patent: September 24, 2019
    Assignee: United Technologies Corporation
    Inventor: Christopher W Strock