Patents by Inventor Michael A. Jacques

Michael A. Jacques 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: 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
  • 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
  • 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
  • Patent number: 10385705
    Abstract: A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.
    Type: Grant
    Filed: May 6, 2016
    Date of Patent: August 20, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter Balawajder, Benjamin F. Hagan, Jeffrey Michael Jacques
  • 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
  • Patent number: 10301951
    Abstract: A turbine vane for a gas turbine engine includes an outer platform including a first side spaced circumferentially apart from a second side, a forward end and an aft end. The first side includes a first gusset extending between the forward end and the aft end. The first gusset defines a first radius beginning at the forward end that transitions into an elliptical curve toward the aft end. An inner platform is also included. An airfoil extends between the outer platform and the inner platform. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: May 20, 2016
    Date of Patent: May 28, 2019
    Assignee: United Technologies Corporation
    Inventors: Russell J. Bergman, Jeffrey Michael Jacques, Daniel Belotto
  • Patent number: 10281245
    Abstract: A ballistic barrier formed of adjoining panels. The panels are made of a bullet resistant material capable of absorbing an impact from a firearm. Each of the panels include a top edge, a bottom edge opposite the top edge, a first side edge, a second side edge opposite the first side edge, a front surface, and a rear surface opposite the front surface. The plurality of panels may include at least a first panel and a second panel. At least one male hinge portion is coupled to the first panel at the first side edge and at least one female hinge portion is coupled to the second panel at the second side edge. The male hinge portion is releasably secured to the female hinge portion pivotably connecting the first panel to the second panel and forming the ballistic barrier.
    Type: Grant
    Filed: September 13, 2017
    Date of Patent: May 7, 2019
    Inventor: Michael Jacques DeKort
  • Patent number: 10247023
    Abstract: A seal damper system includes a plurality of circumferentially spaced blades that each include a platform and an airfoil that extends radially outwardly from the platform. A pocket is arranged circumferentially intermediate the blades and radially inwardly of the platform. A seal damper is arranged in the pocket. The seal damper includes a base section that extends along an axial dimension from a first axial end to an opposing second axial end. The base section joins a first arm that extends radially inwardly from the first axial end and a second arm that extends radially inwardly from the second axial end. The first arm includes a free end having a pair of spaced apart shoulders.
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: April 2, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jeffrey S. Beattie, Jeffrey Michael Jacques
  • Patent number: 10232325
    Abstract: The invention relates to a fluid premixer for mixing a first fluid and a second fluid by aspirating the second fluid into the first fluid by Venturi effect. The premixer comprises a pipe which has a first inlet for the first fluid at a first pressure and a second inlet for the second fluid to be mixed into the first fluid to form a mixture. The pipe also has an outlet for the mixture at a second pressure and a shutter movable between several positions where each position defines a distinct degree of shutting of the pipe. The premixer also includes a control element to control the position of the shutter as a function of the difference between the first pressure and the second pressure.
    Type: Grant
    Filed: December 24, 2014
    Date of Patent: March 19, 2019
    Assignee: GROUPE LEADER
    Inventors: Thierry Patrick Gérard Delerue, Michael Jacques Gérard Steen, Michel Lebey
  • Patent number: 10227875
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
    Type: Grant
    Filed: February 7, 2014
    Date of Patent: March 12, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Scott D. Lewis, Brandon M. Rapp, Jeffrey S. Beattie, Matthew Andrew Hough, Bret M. Teller, Jeffrey Michael Jacques, Max Asterlin
  • Patent number: 10180067
    Abstract: A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage.
    Type: Grant
    Filed: May 31, 2012
    Date of Patent: January 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Jeffrey S. Beattie, Scott D. Lewis, Mark F. Zelesky, Ricardo Trindade, Bret M. Teller, Jeffrey Michael Jacques, Brandon M. Rapp
  • Patent number: 10018062
    Abstract: What is described is a transfer tube for use with an airfoil of a gas turbine engine coupled to a platform. The transfer tube includes a main body having a first end defining an inlet configured to receive a flow of fluid and a second end defining an outlet for the flow of fluid, the main body having a curved section. The transfer tube also includes a first mating face coupled to the first end of the main body. The transfer tube also includes a second mating face coupled to the second end of the main body. At least one of the first mating face or the second mating face is configured to be coupled to a platform body of the outer diameter platform.
    Type: Grant
    Filed: July 2, 2015
    Date of Patent: July 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ryan Alan Waite, Jeffrey Michael Jacques, Benjamin F. Hagan
  • Patent number: 9963991
    Abstract: A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin.
    Type: Grant
    Filed: September 14, 2015
    Date of Patent: May 8, 2018
    Assignee: United Technologies Corporation
    Inventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John W. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Edwin Otero, Alan W. Stoner
  • Publication number: 20180073841
    Abstract: A ballistic barrier formed of adjoining panels. The panels are made of a bullet resistant material capable of absorbing an impact from a firearm. Each of the panels include a top edge, a bottom edge opposite the top edge, a first side edge, a second side edge opposite the first side edge, a front surface, and a rear surface opposite the front surface. The plurality of panels may include at least a first panel and a second panel. At least one male hinge portion is coupled to the first panel at the first side edge and at least one female hinge portion is coupled to the second panel at the second side edge. The male hinge portion is releasably secured to the female hinge portion pivotably connecting the first panel to the second panel and forming the ballistic barrier.
    Type: Application
    Filed: September 13, 2017
    Publication date: March 15, 2018
    Inventor: Michael Jacques DeKort
  • Publication number: 20170335698
    Abstract: A turbine vane for a gas turbine engine includes an outer platform including a first side spaced circumferentially apart from a second side, a forward end and an aft end. The first side includes a first gusset extending between the forward end and the aft end. The first gusset defines a first radius beginning at the forward end that transitions into an elliptical curve toward the aft end. An inner platform is also included. An airfoil extends between the outer platform and the inner platform. A gas turbine engine is also disclosed.
    Type: Application
    Filed: May 20, 2016
    Publication date: November 23, 2017
    Inventors: Russell J. Bergman, Jeffrey Michael Jacques, Daniel Belotto
  • Publication number: 20170321560
    Abstract: A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.
    Type: Application
    Filed: May 6, 2016
    Publication date: November 9, 2017
    Inventors: Peter Balawajder, Benjamin F. Hagan, Jeffrey Michael Jacques
  • Patent number: 9587495
    Abstract: A method of assembling a blade array includes the step of inserting a blade having a platform into a rotor. The blade includes a pocket radially beneath the platform that includes an interference feature. The blade corresponds to one of first and second blades that are scaled versions of one another. The method includes the step of selecting a damper seal, and inserting the damper seal into the pocket. The damper seal corresponds to one of first and second damper seals. The first damper seal cooperates with the interference feature thereby permitting the first damper seal to fully seat within the pocket. The second damper seal is obstructed by the interference feature thereby preventing the second damper seal from fully seating within the pocket.
    Type: Grant
    Filed: June 29, 2012
    Date of Patent: March 7, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jeffrey S. Beattie, Jeffrey Michael Jacques
  • Patent number: 9546556
    Abstract: A turbine blade for a gas turbine engine includes an airfoil that extends in a first radial direction from a platform. A root extends from the platform in a second radial direction and has opposing lateral sides that provide a firtree-shaped contour. The contour includes first, second and third lobes on each of the lateral sides and that tapers relative to the radial direction away from the platform. The first, second and third lobes each provide contact surfaces arranged at about 45° relative to the radial direction. A contact plane on each lateral side at an angle of about 11° relative to the radial direction defining a contact point on each of the contact surfaces. The first, second and third lobes each include first, second and third grooves that are substantially aligned with one another along an offset plane spaced a uniform offset distance from the contact plane.
    Type: Grant
    Filed: September 26, 2012
    Date of Patent: January 17, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jeffrey S. Beattie, Jeffrey Michael Jacques
  • Publication number: 20170002671
    Abstract: What is described is a transfer tube for use with an airfoil of a gas turbine engine coupled to a platform. The transfer tube includes a main body having a first end defining an inlet configured to receive a flow of fluid and a second end defining an outlet for the flow of fluid, the main body having a curved section. The transfer tube also includes a first mating face coupled to the first end of the main body. The transfer tube also includes a second mating face coupled to the second end of the main body. At least one of the first mating face or the second mating face is configured to be coupled to a platform body of the outer diameter platform.
    Type: Application
    Filed: July 2, 2015
    Publication date: January 5, 2017
    Inventors: RYAN ALAN WAITE, Jeffrey Michael Jacques, Benjamin F. Hagan
  • Publication number: 20160325245
    Abstract: The invention relates to a fluid premixer for mixing a first fluid and a second fluid by aspirating the second fluid into the first fluid by Venturi effect, the premixer comprising a pipe (12) including: a first inlet (16) for the first fluid at a first pressure, a second inlet (18) for the second fluid to be mixed into the first fluid to form a mixture, an outlet (22) for the mixture at a second pressure, and a shutter (24) of the pipe (12) movable between several positions each defining a distinct degree of shutting of the pipe (12), the premixer further including a control element (34) able to control the position of the shutter (24) as a function of the difference between the first pressure and the second pressure.
    Type: Application
    Filed: December 24, 2014
    Publication date: November 10, 2016
    Inventors: Thierry Patrick Gérard Delerue, Michael Jacques Gérard Steen, Michel Lebey