Patents by Inventor Brian D. Merry

Brian D. Merry 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).

  • SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES
    Publication number: 20180187605
    Abstract: A turbofan engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a shaft configured to be driven by the turbine section and coupled to the compressor section through a first torque load path, and a speed reduction mechanism configured to be driven by the shaft through a second torque load path separate from the first load path for rotating the fan.
    Type: Application
    Filed: February 28, 2018
    Publication date: July 5, 2018
    Inventors: Michael E. McCune, Brian D. Merry, Gabriel L. Suciu
  • Intercooled cooling air with heat exchanger packaging
    Patent number: 10006370
    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations 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 core housing has an outer peripheral surface and a fan housing defining an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is received within the at least one bifurcation duct.
    Type: Grant
    Filed: June 22, 2015
    Date of Patent: June 26, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Brian D. Merry, Nathan Snape
  • Gas turbine rotors
    Patent number: 10006364
    Abstract: A rotor for a gas turbine engine includes a cold shell, a hot shell, and a spoke. The spoke is connected to and extends radially outward from the cold shell. The hot shell is connected to the cold shell by the spoke and includes an axially extending outboard segment and an axially extending inboard segment. The outboard segment is connected to the inboard segment and the inboard segment is disposed radially inboard of the outboard segment for sealably engaging a stator blade shroud.
    Type: Grant
    Filed: July 30, 2015
    Date of Patent: June 26, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, James D. Hill
  • Cooling system for gas turbine engines
    Patent number: 10001061
    Abstract: A cooling system for gas turbine engines includes a turbine rotor compartment defining a cooling air plenum. A plurality of turbine discs are rotatably housed within the rotor compartment. A cooling air inlet is in fluid communication with the plenum. Each turbine disc includes a cooling outlet in fluid communication with the plenum for cooling the rotor compartment.
    Type: Grant
    Filed: June 5, 2015
    Date of Patent: June 19, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L Suciu, Brian D Merry, James D Hill
  • Gas turbine engine thermal management system
    Patent number: 9988986
    Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: June 5, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nathan Snape, Gabriel L. Suciu, Brian D. Merry, James D. Hill, William Ackermann
  • Engine mounting system
    Patent number: 9970322
    Abstract: A mounting system for a gas turbine engine includes a low pressure turbine section, a first bearing, a mid-turbine frame, and a rear mount. The first bearing supports at least a portion of the low pressure turbine section. The mid-turbine frame supports the first bearing. The rear mount is connected to the mid-turbine frame and is configured to react loads from the gas turbine engine.
    Type: Grant
    Filed: March 11, 2014
    Date of Patent: May 15, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • Mixing plenum for spoked rotors
    Patent number: 9963972
    Abstract: A gas turbine engine may comprise a first rotor with a primary flowpath along an outer diameter of the first rotor. A secondary flowpath may be radially inward from the primary flowpath. The secondary flowpath may pass through an opening through the first rotor. A blade may be disposed on a distal end of the first rotor. The blade may extend into the primary flowpath. A bleed tube may be in a wall of the primary flowpath and forward of the blade. The bleed tube may extend radially inward from the primary flowpath. The bleed tube may fluidly connect to the opening through the first rotor. A plenum may be aft of the blade and radially inward from the primary flowpath. The plenum may be fluidly connected to the opening through the first rotor. A second rotor may be aft of the plenum.
    Type: Grant
    Filed: July 13, 2015
    Date of Patent: May 8, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, James D. Hill
  • Gas turbine engine front architecture
    Patent number: 9957918
    Abstract: A turbine engine is disclosed that includes a fan case surrounding a fan. A core is supported relative to the fan case by support structure, such as flow exit guide vanes, which are arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage. In one example, the example turbine engine includes a gear train arranged between the fan and a spool. The gear train is axially aligned and supported by the inlet case. An intermediate case is arranged axially adjacent to the compressor case. The support structure is arranged axially forward of the intermediate case. In one example, the support structure is axially aligned with the compressor case.
    Type: Grant
    Filed: August 28, 2007
    Date of Patent: May 1, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye
  • Geared turbofan bearing arrangement
    Patent number: 9938898
    Abstract: A geared turbofan gas turbine engine includes a fan section and a core section. The core section includes a compressor section, a combustor section and a turbine section. The fan section includes a gearbox and a fan. A low spool includes a low turbine within the turbine section and a forward connection to a gearbox for driving the fan. The low spool is supported for rotation about the axis at a forward most position by a forward roller bearing and at an aft position by a thrust bearing.
    Type: Grant
    Filed: July 29, 2011
    Date of Patent: April 10, 2018
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu
  • Spoked rotor for a gas turbine engine
    Patent number: 9938831
    Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: April 10, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Stephen P. Muron, Ioannis Alvanos, Christopher M. Dye, Brian D. Merry, Arthur M. Salve, James W. Norris
  • Ceramic matrix composite turbine exhaust case for a gas turbine engine
    Patent number: 9938900
    Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: April 10, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Ioannis Alvanos, Brian D. Merry
  • Gas turbine engine having section with thermally isolated area
    Patent number: 9920652
    Abstract: A section of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a thermally isolated area, and a first rotor disk and a second rotor disk. Each of the first and second rotor disks are provided within the thermally isolated area.
    Type: Grant
    Filed: February 9, 2015
    Date of Patent: March 20, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, William K. Ackermann, James D. Hill, Brian D. Merry
  • Ceramic matrix composite airfoil structures for a gas turbine engine
    Patent number: 9915154
    Abstract: A Ceramic Matrix Composite (CMC) airfoil segment for a gas turbine engine includes a box-shape fiber geometry which defines a rectilinear pressure side bond line and a rectilinear suction side bond line.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: March 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Douglas M. Berczik, Gabriel L. Suciu, Brian D. Merry, Alvanos Ioannis, Christopher M. Dye
  • Systems and methods for distributing cooling air in gas turbine engines
    Patent number: 9915204
    Abstract: Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section.
    Type: Grant
    Filed: April 1, 2015
    Date of Patent: March 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, James D. Hill
  • INTERCOOLED COOLING AIR WITH DUAL PASS HEAT EXCHANGER
    Publication number: 20180066587
    Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.
    Type: Application
    Filed: November 9, 2017
    Publication date: March 8, 2018
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Joseph Brent Staubach, Brian D. Merry, Wesley K. Lord
  • Combined stability and customer bleed with dirt, water and ice rejection
    Patent number: 9909497
    Abstract: A compressor section of a gas turbine engine includes a bleed port having a flow splitter therein so as to define a downstream bleed channel having a downstream inlet and an upstream bleed channel having an upstream inlet that is positioned radially outward from the downstream inlet.
    Type: Grant
    Filed: May 7, 2015
    Date of Patent: March 6, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew R. Feulner, Brian D. Merry, Jesse M. Chandler, Gabriel L. Suciu, Joseph B. Staubach
  • Rear mounted reverse core engine thrust reverser
    Patent number: 9897040
    Abstract: In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.
    Type: Grant
    Filed: February 26, 2014
    Date of Patent: February 20, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Brian D. Merry
  • TWIN CENTRIFUGAL SINGLE SPOOL ENGINE
    Publication number: 20180023576
    Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.
    Type: Application
    Filed: July 25, 2016
    Publication date: January 25, 2018
    Applicant: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Arthur W. Utay, Tania Bhatia Kashyap, Thomas N. Slavens, Kevin L. Rugg, Mark F. Zelesky, Brian D. Merry, Gabriel L. Suciu
  • THRUST REVERSER STRUCTURE MOUNTED TO FAN CASE
    Publication number: 20180023509
    Abstract: A gas turbine engine has a core engine and a fan. A pivoting D-door structure includes a pivoting inner D-door portion and an outer D-door portion, which is axially moveable relative to the inner D-door portion between a stowed and thrust reverse position. A fan case surrounds the fan. Cascades are axially moveable along with the outer D-door portion between a stowed and a thrust reverse position. Structure supporting the cascades is mounted on the fan case.
    Type: Application
    Filed: July 25, 2016
    Publication date: January 25, 2018
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Brian D. Merry
  • Two spool gas generator to create family of gas turbine engines
    Patent number: 9869248
    Abstract: A method of configuring a plurality of gas turbine engines includes the steps of configuring each of the engines with respective ones of a plurality of propulsors. Each propulsor includes a propulsor turbine and one of a fan and a propeller. Each of the engines is configured with respective ones of a plurality of substantially mutually alike gas generators, with the respective propulsor turbine driven by products of combustion downstream of the gas generator.
    Type: Grant
    Filed: May 29, 2013
    Date of Patent: January 16, 2018
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry