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).

  • Retention clip for a blade outer air seal
    Patent number: 10577963
    Abstract: One exemplary embodiment of this disclosure relates to a system having a static segment with a circumferentially extending slot. The system further includes a retention clip partially received in the slot, and partially contacting a circumferential end of the static segment.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: March 3, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Blade outer air seal with seal arc segment having secondary radial supports
    Patent number: 10563534
    Abstract: A blade outer air seal includes a seal arc segment that has radially inner and outer sides, first and second circumferential ends, and first and second axial sides. The seal arc segment includes first and second primary radial supports at which the seal arc segment can be carried in a primary radial position, and first and second secondary radial supports at which the seal arc segment can be carried in a secondary radial position upon release from the first and second primary radial supports.
    Type: Grant
    Filed: December 2, 2015
    Date of Patent: February 18, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Seal assembly for gas turbine engine
    Patent number: 10563531
    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: Grant
    Filed: March 16, 2016
    Date of Patent: February 18, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • SEAL ASSEMBLY FOR TURBINE ENGINE COMPONENT
    Publication number: 20200025007
    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a housing mountable to an engine static structure, a seal carrier secured to the housing and configured to be selectively biased from the housing, and a wedge seal secured to the seal carrier. The wedge seal abuts against sealing surfaces of adjacent blade outer air seals in response to movement of the seal carrier relative to the housing. The wedge seal is separate and distinct from the seal carrier. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
    Type: Application
    Filed: January 23, 2019
    Publication date: January 23, 2020
    Inventor: Michael G. McCaffrey
  • SEAL COATING
    Publication number: 20200025014
    Abstract: A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event.
    Type: Application
    Filed: April 18, 2019
    Publication date: January 23, 2020
    Inventors: John R. Farris, Michael G. McCaffrey
  • INTERCOOLED COOLING AIR WITH AUXILIARY COMPRESSOR CONTROL
    Publication number: 20200025105
    Abstract: A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.
    Type: Application
    Filed: April 4, 2019
    Publication date: January 23, 2020
    Inventors: Brian D. Merry, Gabriel L. Suciu, Michael G. McCaffrey
  • SEAL RING
    Publication number: 20200025293
    Abstract: A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.
    Type: Application
    Filed: January 9, 2019
    Publication date: January 23, 2020
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Ross Wilson, Edwin Otero, Alan W. Stoner
  • SUPPORT STRAPS AND METHOD OF ASSEMBLY FOR GAS TURBINE ENGINE
    Publication number: 20200018189
    Abstract: A method of assembling a portion of a gas turbine engine, includes assembling a plurality of static structure rings; attaching a plurality of support straps to an outer diameter of the plurality of static structure rings to form a cartridge; inserting the cartridge at least partially into an outer case assembly along an engine axis.
    Type: Application
    Filed: July 11, 2018
    Publication date: January 16, 2020
    Applicant: United Technologies Corporation
    Inventors: Michael G. McCaffrey, Scott D. Virkler
  • Boas enhanced heat transfer surface
    Patent number: 10513943
    Abstract: A seal assembly includes a seal arc segment that defines first and second seal supports and radially inner and outer sides with the radially outer side including 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. The seal assembly includes a carriage that 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. The radially inner surface has a higher surface roughness than the radially extending sidewalls.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: December 24, 2019
    Assignee: United Technologies Corporation
    Inventor: Michael G. McCaffrey
  • Ceramic core for component casting
    Patent number: 10507515
    Abstract: A casting ceramic core includes a ceramic structure having at least one through hole and a plurality of features extending from a main ceramic body. The ceramic body defines a negative space for a casting and a plurality of aligned fibers extending a substantial length of at least one casting feature.
    Type: Grant
    Filed: December 7, 2015
    Date of Patent: December 17, 2019
    Assignee: United Technologies Corporation
    Inventors: Jesse M. Carr, Michael G. McCaffrey
  • Rotor and gas turbine engine including same
    Patent number: 10502060
    Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk. One or more cooling features may be incorporated radially inboard from the rotor disk rim that operate to induce vortices adjacent to the disk rim and/or disk web. The vortices increase the local velocity in the secondary cooling air flow path and therefore increase the heat transfer rate from the rotor to the secondary cooling air flow path.
    Type: Grant
    Filed: June 17, 2015
    Date of Patent: December 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • SEAL SUPPORT STRUCTURE FOR A CIRCUMFERENTIAL SEAL OF A GAS TURBINE ENGINE
    Publication number: 20190331003
    Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.
    Type: Application
    Filed: June 27, 2019
    Publication date: October 31, 2019
    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
  • Bonded multi-piece gas turbine engine component
    Patent number: 10458249
    Abstract: An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.
    Type: Grant
    Filed: November 5, 2014
    Date of Patent: October 29, 2019
    Assignee: United Technologies Corporation
    Inventors: Michael G. McCaffrey, Ioannis Alvanos, Michael G. Abbott, Grant O. Cook, III
  • INTERCOOLED COOLING AIR FLEET MANAGEMENT SYSTEM
    Publication number: 20190323430
    Abstract: A method of modulating cooling of gas turbine engine components includes the steps of identifying an input indicative of a usage rate for at least a first gas turbine engine component of a plurality of gas turbine engine components. A cooling system is operated for at least the first gas turbine engine component. The cooling system is moved between a higher cooling potential mode and a lower cooling potential mode based on the identified rate. A gas turbine engine is also disclosed.
    Type: Application
    Filed: April 19, 2018
    Publication date: October 24, 2019
    Inventors: Frederick M. Schwarz, Michael G. McCaffrey
  • Blade outer air seal with centrally mounted seal arc segments
    Patent number: 10443616
    Abstract: A seal system includes a segmented annular seal support that has carriage arc segments arranged circumferentially in circumferential carriage joints, and a segmented annular seal that includes seal arc segments arranged end-to-end in circumferential seal joints. The circumferential seal joints are circumferentially offset from the circumferential carriage joints.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Turbine engine blade outer air seal with load-transmitting carriage
    Patent number: 10443424
    Abstract: A gas turbine engine includes a case disposed around a central axis, a vane structure disposed radially inwards of the case, a seal carriage mounted to the case, and a seal arc segment mounted to the seal carriage. The vane structure exerts an axial load on the seal carriage. The seal carriage defines a load path that radially transmits the axial load to the case.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Turbomachine blade assemblies
    Patent number: 10443421
    Abstract: A turbomachine blade can include a blade root defining a plurality of feather seal slots on a lateral portion thereof. The plurality of seal slots includes two leg slots, each leg slot extending radially, and a cross member slot extending axially. An airfoil portion extends radially from the blade root.
    Type: Grant
    Filed: July 20, 2015
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Seal support structure for a circumferential seal of a gas turbine engine
    Patent number: 10443450
    Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.
    Type: Grant
    Filed: October 23, 2015
    Date of Patent: October 15, 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
  • Gas turbine engine blade outer air seal assembly
    Patent number: 10443423
    Abstract: A gas turbine engine includes a rotating stage of blades. A circumferential array of blade outer air seal segments are arranged radially outward of the blades. Adjacent blade outer air seal segments provide a circumferential gap. Facing ends of the adjacent blade outer air seal segments include surfaces. A gap seal engages the surfaces and obstructs the circumferential gap. A biasing member is configured to urge the gap seal radially inward toward the surfaces.
    Type: Grant
    Filed: August 25, 2015
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Intercooled cooling air with auxiliary compressor control
    Patent number: 10443508
    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor, and at least one more upstream compressor. A turbine section has a high pressure turbine. A tap line taps air from at least one of the more upstream compressors in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions. An intercooling system is also disclosed.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: October 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, Michael G. McCaffrey