Patents by Inventor Jose R Paulino

Jose R Paulino 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).

  • Publication number: 20210172527
    Abstract: A seal joint assembly is provided that includes a stationary seal carrier, a stationary seal land and a brush seal. The stationary seal land includes a seal land surface. The brush seal is mounted to the stationary seal carrier. The brush seal includes a first set of bristles and a second set of bristles. The first set of bristles includes a first bristle that contacts the seal land surface. The second set of bristles includes a second bristle that contacts the seal land surface. The second bristle crosses the first bristle.
    Type: Application
    Filed: December 6, 2019
    Publication date: June 10, 2021
    Inventors: Jose R. Paulino, Neil L. Tatman, Paul J. Burgess
  • Publication number: 20210102474
    Abstract: A replaceable rotor blade tip clearance measurement device for a gas turbine engine, includes a threaded section along an axis and an integral abradable tip with an internal lattice geometry that extends from the threaded section along the axis.
    Type: Application
    Filed: October 3, 2019
    Publication date: April 8, 2021
    Applicant: United Technologies Corporation
    Inventors: Jose R. Paulino, Veronika Reynolds, Jason David Liles
  • Patent number: 10920601
    Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets. A sacrificial structure for forming internal cooling passages within a blade outer air seal and a method of cooling an interface between a blade outer air seal and a rotating blade array is also disclosed.
    Type: Grant
    Filed: July 24, 2019
    Date of Patent: February 16, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Dmitriy A. Romanov, Jose R. Paulino, Ken F. Blaney
  • Patent number: 10801353
    Abstract: A component for a gas turbine engine includes a surface adjacent a flow of hot gases. A plurality of cavities is in a portion of the surface. The plurality of cavities have a first group of cavities with a first cross-section and a second group of cavities with a second cross-section different from the first cross-section. The first and second groups of cavities are arranged such that there is no straight line across the portion of the surface that does not intersect one of the plurality of cavities. A thermal barrier coating is over the surface and fills each of the plurality of cavities.
    Type: Grant
    Filed: February 8, 2019
    Date of Patent: October 13, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul M. Lutjen, Christopher W. Strock, Jose R. Paulino
  • Patent number: 10746049
    Abstract: An example case for a gas turbine engine includes a bearing compartment, a radially outer ring, and a radially inner ring. The radially outer ring and radially inner ring are connected by a plurality of circumferentially spaced apart struts and define an annular flow path therebetween. The radially inner ring includes a first flange that extends radially outward from the bearing compartment. The first flange includes an undulation that extends axially away from the plurality of struts, and defines a load path between the bearing compartment and the radially outer ring.
    Type: Grant
    Filed: March 30, 2018
    Date of Patent: August 18, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jonathan Jeffery Eastwood, Adam Lee Hart, Brian Levy, Luis Miguel Ayalde, Brian Craig, Jose R. Paulino, Esref Yaylagan
  • Patent number: 10746033
    Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform includes a radially outer surface that is attached to the radially inner end of the airfoil. A radially inner side of the platform includes a forward surface and an aft surface. A pocket is recessed into at least one of the forward surface and the aft surface. A cover plate covers the pocket and a seal is attached to the cover plate.
    Type: Grant
    Filed: May 17, 2018
    Date of Patent: August 18, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Jose R. Paulino
  • Publication number: 20200256206
    Abstract: A component for a gas turbine engine includes a surface adjacent a flow of hot gases. A plurality of cavities is in a portion of the surface. The plurality of cavities have a first group of cavities with a first cross-section and a second group of cavities with a second cross-section different from the first cross-section. The first and second groups of cavities are arranged such that there is no straight line across the portion of the surface that does not intersect one of the plurality of cavities. A thermal barrier coating is over the surface and fills each of the plurality of cavities.
    Type: Application
    Filed: February 8, 2019
    Publication date: August 13, 2020
    Inventors: Paul M. Lutjen, Christopher W. Strock, Jose R. Paulino
  • Publication number: 20200232390
    Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.
    Type: Application
    Filed: January 18, 2019
    Publication date: July 23, 2020
    Inventors: Ramons A. Reba, Bruce L. Morin, Daniel L. Gysling, Carson A. Roy Thill, Jose R. Paulino, JinQuan Xu, Stephen A. Morford
  • Patent number: 10641129
    Abstract: A component for a gas turbine engine is disclosed. The component includes a platform and a rail having an outer radial surface and an inner radial surface, with the inner radial surface connected to the platform. The rail includes a plurality of apertures spaced circumferentially between the outer radial surface and the inner radial surface, the apertures disposed to form a truss-like structure.
    Type: Grant
    Filed: November 8, 2017
    Date of Patent: May 5, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Jose R. Paulino, Craig R. McGarrah, Edward R. Bareiss, Edwin Otero
  • Publication number: 20200102848
    Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets. A sacrificial structure for forming internal cooling passages within a blade outer air seal and a method of cooling an interface between a blade outer air seal and a rotating blade array is also disclosed.
    Type: Application
    Filed: July 24, 2019
    Publication date: April 2, 2020
    Inventors: Dmitriy A. Romanov, Jose R. Paulino, Ken F. Blaney
  • Patent number: 10550708
    Abstract: Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, and at least three beams, each beam having a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, and at least three beams, where each beam has a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure.
    Type: Grant
    Filed: August 31, 2016
    Date of Patent: February 4, 2020
    Assignee: United Technologies Corporation
    Inventors: Jose R. Paulino, Conway Chuong, Joey Wong, Christopher J. Peters, Ross Wilson
  • Patent number: 10487678
    Abstract: A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal.
    Type: Grant
    Filed: May 23, 2016
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Terence P. Tyler, Jr., Timothy M. Davis, Jeremy Drake, Jose R. Paulino, Jaimie Schweitzer
  • Patent number: 10487943
    Abstract: A multi-ply seal ring includes an inner seal ring and an outer seal ring. The inner seal ring includes a plurality of discrete inner ring segments disposed circumferentially about an axis in an annular array. The inner ring segments are arranged end-to-end within the annular array. The inner seal ring is engaged with and nested within the outer seal ring. In addition or alternatively, the outer seal ring may include a plurality of discrete outer ring segments disposed circumferentially about the axis in an annular array.
    Type: Grant
    Filed: July 12, 2016
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Timothy M. Davis, Jeffrey M. Wittman, Jose R. Paulino
  • Publication number: 20190316485
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion; and a multitude of cooling fins disposed around the radially outer face of the seal body, at least one of the multitude of cooling fins having at least one aperture.
    Type: Application
    Filed: April 11, 2018
    Publication date: October 17, 2019
    Applicant: United Technologies Corporation
    Inventors: Adam Lee Hart, Brian Levy, Luis Miguel Ayalde, Jose R. Paulino, Patrick Scheelk, Nicolas Bueno
  • Patent number: 10443425
    Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dmitriy A. Romanov, Jose R. Paulino, Ken F. Blaney
  • Publication number: 20190309856
    Abstract: A brush seal is provided that includes a top plate, a back plate, and a bristle pack. The bristle pack is secured at a joint between the top plate and the back plate. The bristle pack includes a first bristle set extending from the joint, a second bristle set extending from the joint, and a sliding backing plate. The sliding backing plate includes a sliding portion and a support portion. The sliding portion is disposed contiguous with the second bristle set. The support portion has an inner face and a support face. The inner face is in contact with a distal end of the second bristle set. The support face is configured to support at least a portion of the first bristle set. The sliding backing plate is configured to slide relative to the second bristle set.
    Type: Application
    Filed: April 5, 2018
    Publication date: October 10, 2019
    Inventors: Jeremy Drake, Timothy M. Davis, Mark J. Rogers, Jose R. Paulino
  • Publication number: 20190301302
    Abstract: An example case for a gas turbine engine includes a bearing compartment, a radially outer ring, and a radially inner ring. The radially outer ring and radially inner ring are connected by a plurality of circumferentially spaced apart struts and define an annular flow path therebetween. The radially inner ring includes a first flange that extends radially outward from the bearing compartment. The first flange includes an undulation that extends axially away from the plurality of struts, and defines a load path between the bearing compartment and the radially outer ring.
    Type: Application
    Filed: March 30, 2018
    Publication date: October 3, 2019
    Inventors: Jonathan Jeffery Eastwood, Adam Lee Hart, Brian Levy, Luis Miguel Ayalde, Brian Craig, Jose R. Paulino, Esref Yaylagan
  • Patent number: 10428953
    Abstract: Aspects of the disclosure are directed to a brush seal assembly, comprising a compressible core, at least one wire wound around the core, and a backing plate that is substantially ‘c’ shaped or ‘u’ shaped that at least partially encases the at least one wire. Aspects of the disclosure are directed to a method comprising separating compressible cores with a spacer, winding wires around the cores and the spacer, and forming substantially ‘c’ shaped or ‘u’ shaped backings about the wires to obtain a package of brush seal assemblies.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: October 1, 2019
    Assignee: United Technologies Corporation
    Inventors: Paul M. Lutjen, Jose R. Paulino
  • Patent number: 10415411
    Abstract: Aspects of the disclosure are directed to a system for maintaining a seal about an engine centerline, comprising: a first component, a second component, and a dog-bone seal coupled to the first component and the second component, wherein the first component is configured with at least one spline that is configured to engage a slot in the dog-bone seal to radially center the dog-bone seal relative to the first component and the second component.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: September 17, 2019
    Assignee: United Technologies Corporation
    Inventors: Timothy M. Davis, Jose R. Paulino
  • Patent number: 10393270
    Abstract: A brush seal includes a bristle pack disposed between a top plate and a back plate. A sliding backing plate is disposed between the bristle pack and the back plate. The bristle pack includes a first bristle set that extends across a seal gap between a first engine component and a second engine component to prevent leakage across the seal gap and a second bristle set that exerts a force on the sliding backing plate. The sliding backing plate supports at least a portion of the first bristles and extends across the seal cavity to contact the second component. The force exerted on the sliding backing plate drives the sliding backing plate into contact with the second component.
    Type: Grant
    Filed: July 31, 2017
    Date of Patent: August 27, 2019
    Assignee: United Technologies Corporation
    Inventors: Timothy M Davis, Jose R. Paulino, Mark J. Rogers