Patents by Inventor Ken F. Blaney

Ken F. Blaney 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: 20200094447
    Abstract: A mandrel for a molding process that includes a first portion that has a first portion outer surface, a first portion inner surface, a first portion first end, and a first portion second end. A thickness of the first portion first end is greater than the first portion second end. A second portion has a second portion outer surface, a second portion inner surface, a second portion first end, and a second portion second end. A thickness of the second portion first end is smaller than the second portion second end. The first portion inner surface engages the second portion inner surface to form a mandrel that has a constant cross-section.
    Type: Application
    Filed: September 24, 2018
    Publication date: March 26, 2020
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Publication number: 20200072067
    Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. A flow guide has a plurality of flow guide segments arranged between the blade outer air seal and the support structure. An intersegment seal is at a circumferential end of at least one of the flow guide segments.
    Type: Application
    Filed: September 5, 2018
    Publication date: March 5, 2020
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Publication number: 20200072071
    Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The blade outer air seal has a lip at an axial end engaged with the support structure. A seal structure has a seal portion and a wear liner portion joined by a radially extending portion. The seal portion is radially outward of the lip and the wear liner is radially inward of the lip.
    Type: Application
    Filed: September 5, 2018
    Publication date: March 5, 2020
    Inventors: Ken F. Blaney, Paul M. Lutjen, Thomas E. Clark
  • Publication number: 20200072127
    Abstract: A turbine section for a gas turbine engine includes a turbine blade that extends radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is mounted in a support structure and is arranged radially outward of the outer tip. A flow guide is arranged between the support structure and the blade outer air seal and defines a passage between the flow guide and the blade outer air seal. The passage is configured to communicate air in a generally axial direction.
    Type: Application
    Filed: September 5, 2018
    Publication date: March 5, 2020
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Publication number: 20200072084
    Abstract: A blade outer air seal assembly contains a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The support structure has a first support member that engages a first axial side of the blade outer air seal. A second support member engages a second axial side of the blade outer air seal. A retaining clip secures the blade outer air seal to the support structure. The retaining clip has a first leg and a second leg that extends in a generally radial direction. The first leg abuts the first axial side and the second leg abuts the first support member.
    Type: Application
    Filed: September 5, 2018
    Publication date: March 5, 2020
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Publication number: 20200072070
    Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section has at least one turbine rotor that has a radially extending turbine blade and is rotatable about an axis of rotation and at least one turbine vane. A blade outer air seal is positioned radially outwardly of a radially outer tip of the turbine blade. A structure mounts the blade outer air seal and provides a platform of at least one turbine vane.
    Type: Application
    Filed: September 5, 2018
    Publication date: March 5, 2020
    Inventors: Ken F. Blaney, Paul M. Lutjen, Thomas E. Clark
  • Patent number: 10557368
    Abstract: An active clearance control system of a gas turbine engine includes a radially adjustable blade outer air seal system movable between a radially contracted Blade Outer Air Seal (BOAS) position that defines a first air volume and a radially expanded Blade Outer Air Seal (BOAS) position that defines a second air volume, the second air volume different than the first air volume. An accumulator system accommodate a difference in air volume between the first air volume and the second air volume.
    Type: Grant
    Filed: February 6, 2014
    Date of Patent: February 11, 2020
    Assignee: United Technologies Corporation
    Inventors: Ken F. Blaney, Todd M. LaPierre
  • Patent number: 10557367
    Abstract: An example active clearance control system for a gas turbine engine includes an actuator, and a case wall portion defining an aperture configured to receive the actuator. The actuator is configured to move an air seal segment, and the actuator is insertable to an installed position within the aperture through a radially outer side of the case wall portion.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: February 11, 2020
    Assignee: United Technologies Corporation
    Inventors: Ken F. Blaney, Richard K. Hayford, Christopher M. Jarochym
  • Publication number: 20200025029
    Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a chamber within the attachment block, and communicates to circumferential edges of the attachment block to direct cooling air along the central web of the blade outer air seal. A blade outer air seal assembly is also disclosed.
    Type: Application
    Filed: July 23, 2018
    Publication date: January 23, 2020
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Publication number: 20200025028
    Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a central chamber within the attachment block, and communicates with cooling holes through a radially inner face of the attachment block to direct cooling air at the central web of the blade outer air seal. A blade outer air seal is also disclosed.
    Type: Application
    Filed: July 23, 2018
    Publication date: January 23, 2020
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Publication number: 20200003422
    Abstract: A self-pumping fuel injector includes a pump and a motor for, in-part, delivering fuel to a combustor at higher fuel pressures during start-up and ramping-up conditions. Each pump may include a stationary flow interuptor that intermittently and variably supplies fuel to a rotating spindle that, in-turn, expels the fuel into a nozzle of the injector for improve fuel spray distributions.
    Type: Application
    Filed: September 10, 2019
    Publication date: January 2, 2020
    Inventors: Ken F. Blaney, Stephen K. Kramer
  • Publication number: 20200003077
    Abstract: An attachment body for a blade outer air seal includes a leading edge connected to a trialing edge by a radially inner wall and a radially outer wall. At least one forward hook extends from the radially outer wall. At least one aft hook extends from the radially outer wall. At least one post extends from the radially outer surface and has a blade outer air seal (BOAS) guide surface.
    Type: Application
    Filed: June 27, 2018
    Publication date: January 2, 2020
    Inventors: Thomas E. Clark, Ken F. Blaney
  • Patent number: 10519872
    Abstract: A planetary gear system for a turbomachine includes a forward planetary gear assembly including a plurality of forward planet gears meshed to a forward sun gear disposed on a power shaft and a forward ring gear meshed to the forward planet gears and an aft planetary gear assembly aft of the forward planetary assembly including a plurality of aft planet gears meshed to an aft sun gear disposed on the power shaft and an aft ring gear meshed to the aft planet gears. The system also includes a gear housing disposed between the forward planetary gear assembly and the aft planetary gear assembly. The gear housing includes a stationary carrier, wherein the forward and aft planet gears are rotatably mounted to the stationary carrier, and a mount extending radially from the stationary carrier that is connectable to a stationary portion of the turbomachine.
    Type: Grant
    Filed: August 28, 2017
    Date of Patent: December 31, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ken F. Blaney, Todd M. LaPierre, Richard K. Hayford
  • Patent number: 10443851
    Abstract: A self-pumping fuel injector includes a pump and a motor for, in-part, delivering fuel to a combustor at higher fuel pressures during start-up and ramping-up conditions. Each pump may include a stationary flow interuptor that intermittently and variably supplies fuel to a rotating spindle that, in-turn, expels the fuel into a nozzle of the injector for improve fuel spray distributions.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: October 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Ken F. Blaney, Stephen K. Kramer
  • 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
  • Patent number: 10370999
    Abstract: An active clearance control system of a gas turbine engine includes an air seal segment with a bridge hook having a lugged aperture.
    Type: Grant
    Filed: February 6, 2014
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Ken F. Blaney, Paul M. Lutjen, Brian R. Pelletier
  • Patent number: 10352184
    Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.
    Type: Grant
    Filed: October 31, 2016
    Date of Patent: July 16, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jose R. Paulino, Ken F. Blaney, Terence P. Tyler, Jr., Daniel S. Rogers, Anthony B. Swift, Thomas E. Clark
  • Patent number: 10329934
    Abstract: A casting core for a Blade Outer Air Seal includes a heat exchange cavity core section in communication with a first plenum section and a second plenum section, the first plenum and the second plenum section are of a thickness greater than the heat exchange cavity section.
    Type: Grant
    Filed: October 12, 2015
    Date of Patent: June 25, 2019
    Assignee: United Technologies Corporation
    Inventors: Ken F Blaney, Anthony B Swift, Neil L Tatman, Paul M Lutjen, Christopher M Jarochym
  • Patent number: 10309253
    Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: January 13, 2016
    Date of Patent: June 4, 2019
    Assignee: United Technologies Corporation
    Inventors: Kevin J. Ryan, Terence P. Tyler, Jr., Ken F. Blaney
  • Patent number: 10247028
    Abstract: A clearance control system for a gas turbine engine is provided. The system includes an inner axial wall that extends between a forward wall and an aft wall. The system also includes an outer axial wall that extends parallel to the inner axial wall to pivotally receive a full hoop thermal control ring.
    Type: Grant
    Filed: August 5, 2014
    Date of Patent: April 2, 2019
    Assignee: United Technologies Corporation
    Inventors: Ken F. Blaney, Paul M. Lutjen