Patents by Inventor Luis Miguel Ayalde

Luis Miguel Ayalde 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).

  • Blade outer air seal cooling fin
    Patent number: 11268402
    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: Grant
    Filed: April 11, 2018
    Date of Patent: March 8, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Adam Lee Hart, Brian Levy, Luis Miguel Ayalde, Jose R. Paulino, Patrick Scheelk, Nicolas Bueno
  • Gas turbine engine exhaust component
    Patent number: 10774685
    Abstract: A heat shield for a gas turbine engine includes a radial heat shield flange that extends in a circumferential direction and forms a ring. A plurality of bosses extend from a first axial side of the radial heat shield flange. There is a plurality of guide pins. One of the plurality of guide pins extends from a corresponding one of the plurality of bosses.
    Type: Grant
    Filed: April 30, 2018
    Date of Patent: September 15, 2020
    Assignee: RATHEON TECHNOLOGIES CORPORATION
    Inventors: Jonathan Jeffery Eastwood, Adam Lee Hart, Brian Craig, Luis Miguel Ayalde, Brian Levy
  • Gas turbine engine case including bearing compartment
    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
  • GAS TURBINE ENGINE EXHAUST COMPONENT
    Publication number: 20190331002
    Abstract: A heat shield for a gas turbine engine includes a radial heat shield flange that extends in a circumferential direction and forms a ring. A plurality of bosses extend from a first axial side of the radial heat shield flange. There is a plurality of guide pins. One of the plurality of guide pins extends from a corresponding one of the plurality of bosses.
    Type: Application
    Filed: April 30, 2018
    Publication date: October 31, 2019
    Inventors: Jonathan Jeffery Eastwood, Adam Lee Hart, Brian Craig, Luis Miguel Ayalde, Brian Levy
  • BLADE OUTER AIR SEAL COOLING FIN
    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
  • GAS TURBINE ENGINE CASE INCLUDING BEARING COMPARTMENT
    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