Patents by Inventor Michael G. McCaffrey

Michael G. McCaffrey 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).

  • Seal anti-rotation feature
    Patent number: 10436053
    Abstract: A seal assembly includes a seal arc segment defining first and second seal supports. A carriage defines first and second support members with the first support member supporting the seal arc segment in a first ramped interface and the second support member supporting the seal arc segment in a second ramped interface such that the seal arc segment is circumferentially moveable with respect to the carriage. The seal assembly includes an anti-rotation interface in which the seal arc segment and the carriage are engaged. The anti-rotation interface restricts circumferential movement of the seal arc segment.
    Type: Grant
    Filed: September 27, 2018
    Date of Patent: October 8, 2019
    Assignee: United Technologies Corporation
    Inventor: Michael G. McCaffrey
  • Blade outer air seal having angled retention hook
    Patent number: 10436070
    Abstract: A blade outer air seal (BOAS) according to an exemplary aspect of the present disclosure includes, among other things, a ceramic body having a radially inner face and a radially outer face and a retention feature that extends from the radially outer face. The retention feature includes at least one angled hook that extends at a transverse angle relative to the radially outer face.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: October 8, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Seal support structure
    Patent number: 10436051
    Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.
    Type: Grant
    Filed: October 23, 2015
    Date of Patent: October 8, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Alan W. Stoner, Edwin Otero
  • Turbine engine blade outer air seal with load-transmitting cover plate
    Patent number: 10422240
    Abstract: A seal assembly includes a seal arc segment that defines radially inner and outer sides and first and second axial arc segment sides, a carriage that carries the seal arc segment, and a cover that defines first and second axial cover sides. The second axial cover side is adjacent the first axial arc segment side.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: September 24, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Blade outer air seal support for a gas turbine engine
    Patent number: 10422241
    Abstract: A blade outer air seal support includes, at least one arc body having a first portion and a second portion, a blade outer air seal mounting region defined at least partially between the first portion and the second portion, and an interface feature interfacing the first portion and the second portion. The interface feature is configured such that axially aligned forces are communicated between the first and second portions through the interface feature, bypassing the blade outer air seal mounting region.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: September 24, 2019
    Assignee: United Technologies Corporation
    Inventors: Michael G. McCaffrey, Peter Balawajder, David Richard Griffin, Benjamin F. Hagan
  • SEAL ASSEMBLY FOR GAS TURBINE ENGINE
    Publication number: 20190285002
    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal including a sealing portion and an engagement portion. A support includes an interface portion and a mounting portion. The interface portion defines a retention slot spaced apart from opposing mate faces. The mounting portion is configured to be fixedly attached to an engine static structure. The engagement portion is dimensioned to be slideably received within the retention slot.
    Type: Application
    Filed: March 16, 2016
    Publication date: September 19, 2019
    Inventor: Michael G. McCaffrey
  • System for modulating turbine blade tip clearance
    Patent number: 10415419
    Abstract: A system for modulating turbine blade tip clearance is provided. The system may comprise an actuation control system having at least one actuator configured to modulate turbine blade tip clearance between a turbine blade tip and a blade outer air seal (BOAS). Each actuator may be coupled to the BOAS. Each actuator may comprise a solid-state motion amplification device such as a flextensional actuator. The actuators may be configured to move the BOAS in a radial direction from a first position to a second position to control tip clearance.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: September 17, 2019
    Assignee: United Technologies Corporation
    Inventors: Fanping Sun, Zaffir A. Chaudhry, Lee A. Hoffman, Hailing Wu, Seung Bum Kim, Michael G. McCaffrey, Joel H. Wagner
  • Seal arc segment with anti-rotation feature
    Patent number: 10415414
    Abstract: A seal arc segment includes a body including a radially inner surface and a radially outer surface. The radially inner surface and the radially outer surface are located between a first circumferential end and a second circumferential end. A recessed portion defines a cavity in the radially outer surface. A notch is located in an edge of the recessed portion adjacent the first circumferential end.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher Corcoran, Michael G. McCaffrey, Benjamin F. Hagan
  • System for modulating turbine blade tip clearance
    Patent number: 10415418
    Abstract: A system for modulating turbine blade tip clearance is provided. The system may comprise an actuation control system having at least one actuator configured to modulate turbine blade tip clearance. Each actuator may comprise a solid-state motion amplification device such as a flextensional actuator. Each actuator may be in operable communication with a blade outer air seal (BOAS) segment or a BOAS mounting block. The actuators may be configured to move the BOAS segment and/or the BOAS mounting block in a radial direction from a first position to a second position to control tip clearance.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: September 17, 2019
    Assignee: United Technologies Corporation
    Inventors: Michael G. McCaffrey, Zaffir A. Chaudhry, Fanping Sun
  • Gas turbine engine active clearance control system
    Patent number: 10415417
    Abstract: A gas turbine engine includes a blade having a tip, a blade outer air seal operatively connected to a case assembly, and an active clearance control system disposed on the case assembly. The active control system includes an actuator assembly. The actuator assembly includes a motor assembly and a shaft. The shaft has a shaft body that extends between a first end that is operatively connected to the motor assembly and a second end that is operatively connected to the blade outer air seal.
    Type: Grant
    Filed: July 27, 2016
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Gas turbine engine and seal assembly therefore
    Patent number: 10370991
    Abstract: The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams.
    Type: Grant
    Filed: August 19, 2015
    Date of Patent: August 6, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, Michael G McCaffrey, John R Farris, Theodore W Hall, John J Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, Edwin Otero, John E Paul
  • Meter plate for blade outer air seal
    Patent number: 10364706
    Abstract: One exemplary embodiment according to this disclosure relates to a system includes a blade outer air seal (BOAS), and a meter plate. A portion of the meter plate is provided radially outward of a radially outermost surface of the BOAS.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: July 30, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Composite airfoil
    Patent number: 10358929
    Abstract: An airfoil includes a core with a first Young's Modulus; and an outer section at least partially surrounding the core with a second Young's Modulus, wherein the first Young's Modulus is higher than the second Young's Modulus.
    Type: Grant
    Filed: July 1, 2014
    Date of Patent: July 23, 2019
    Assignee: United Technologies Corporation
    Inventors: Michael G. McCaffrey, Greg C. Ojard, Kevin L. Rugg
  • High temperature seal and method
    Patent number: 10352183
    Abstract: An embodiment of a turbine assembly includes, among other possible things, a first component including a first component surface, a second component including a second component surface spaced apart from the first component surface, and a brush seal disposed between the first component and the second component. The brush seal includes, among other things, a first bristled region extending in a first direction from a backing plate, and sealingly engaging one of the first component surface and the second component surface. At least one of the backing plate and the first bristled region includes a nickel-based superalloy material having at least 40% of a Ni3(Al,X) precipitate phase, X being a metallic or refractory element other than Al.
    Type: Grant
    Filed: April 25, 2016
    Date of Patent: July 16, 2019
    Assignee: United Technologies Corporation
    Inventors: Dilip M. Shah, Katelyn Kwoka, Alan D. Cetel, Venkatarama K. Seetharaman, Michael G. McCaffrey
  • Compact advanced passive tip clearance control
    Patent number: 10344612
    Abstract: A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. The section also includes a control ring being annular, positioned radially inward from the case and designed to move radially relative to the case. The section also includes a segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and designed to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: July 9, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Eric A. Hudson, Michael G. McCaffrey, Stanley J. Funk, Scott D. Virkler
  • Blade outer air seal with flow guide manifold
    Patent number: 10337346
    Abstract: A blades outer air seal includes a seal arc segment that defines radially inner and outer sides. The radially outer side includes radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A manifold is disposed at least partially in the pocket. The manifold subdivides the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface. The manifold includes at least one inlet and a plurality of outlets.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: July 2, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael G. McCaffrey, Benjamin F. Hagan, David Richard Griffin
  • LIGHTWEIGHT TIEROD
    Publication number: 20190195087
    Abstract: The present disclosure provides an assembly for a gas turbine engine. The assembly may comprise a tierod, a bearing mounting ring, and a joint coupling the tierod to the bearing mounting ring. The joint may be configured to increase a volume of a bearing compartment on an inner surface of the bearing mounting ring. A coefficient of thermal expansion of the bearing mounting ring may be substantially the same as the coefficient of thermal expansion of the tierod.
    Type: Application
    Filed: December 21, 2017
    Publication date: June 27, 2019
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael G. McCaffrey, Scott D. Virkler, Tuan David Vo
  • Blade outer air seal with cooling features
    Patent number: 10323534
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, 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. At least one cooling fin is disposed on the radially outer face between the leading edge portion and the trailing edge portion.
    Type: Grant
    Filed: January 9, 2017
    Date of Patent: June 18, 2019
    Assignee: United Technologies Corporation
    Inventor: Michael G. McCaffrey
  • Staged high temperature heat exchanger
    Patent number: 10317150
    Abstract: A staged high temperature heat exchanger (HEX) may comprise a first stage made from a first material and a second stage made from a second material. The first stage may comprise an inlet manifold configured to receive a flow of fluid. The second stage may comprise an outlet manifold whereby the flow of fluid exits the HEX. The first stage is configured to withstand the temperature of the flow of fluid entering the inlet manifold and configured to reduce the temperature of the flow of fluid to an intermediate temperature before the flow of fluid reaches the second stage. In various embodiments, the first material may comprise a nickel-based superalloy having at least 40% of a Ni3(Al,X) precipitate phase, X being a metallic or refractory element other than Al.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: June 11, 2019
    Assignee: United Technologies Corporation
    Inventors: Michael G McCaffrey, Matthew A Devore
  • HIGH TEMPERATURE PLATE FIN HEAT EXCHANGER
    Publication number: 20190170445
    Abstract: A heat exchanger includes at least one plate including a first end portion. A second end portion is spaced apart from the first end portion. A cavity is disposed between the first end portion and the second end portion. The cavity defines a first flow path. An outer surface portion defines a second flow path. The at least one plate includes a single unitary part without a joint between any two portions. A first end cap defines an inlet disposed at the first end portion. A second end cap defines an outlet at the second end portion. A plate for a heat exchanger and a method are also disclosed.
    Type: Application
    Filed: November 9, 2018
    Publication date: June 6, 2019
    Inventor: Michael G. McCaffrey