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).

  • Counter-rotating low pressure turbine with gear system mounted to turbine exhaust case
    Patent number: 9022725
    Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.
    Type: Grant
    Filed: February 29, 2012
    Date of Patent: May 5, 2015
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu
  • Pivoting Blocker Door
    Publication number: 20150113945
    Abstract: A gas turbine engine that has a fan case radially surrounding a fan hub, and plural fan exit guide vanes rotatably connected between the fan hub and the fan case. The fan section also has a thrust reverser opening within the case, axially upstream of the guide vanes. The gas turbine engine also has a core case containing a core engine.
    Type: Application
    Filed: October 13, 2014
    Publication date: April 30, 2015
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • Counter-rotating low pressure turbine with gear system mounted to turbine exhaust case
    Patent number: 9011076
    Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An inner rotor directly drives the shaft and includes an inner set of blades. An outer rotor has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system couples the outer rotor to the shaft and is configured to rotate the inner set of blades at a lower speed than the outer set of blades.
    Type: Grant
    Filed: February 29, 2012
    Date of Patent: April 21, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    Publication number: 20150089959
    Abstract: A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supporting the shaft relative to the inlet case. The second bearing is arranged radially outward from the shaft.
    Type: Application
    Filed: December 15, 2014
    Publication date: April 2, 2015
    Inventors: Brian D. Merry, Gabriel L. Suciu
  • Apparatus and method for operating a gas turbine engine during windmilling
    Patent number: 8978352
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a windmill pump driven by a spool. A first pump driven by said spool with an air-oil cooler is located downstream of the first pump. A second pump is also driven the spool with an air-air precooler located downstream of the second pump. A method of operating a gas turbine engine during a “windmilling” condition includes driving a windmill pump with a spool during a “windmilling ” condition. A lubricant is communicated to a geared architecture with the windmill pump. A first pump is driven by the spool and an air-oil cooler is located downstream of the first pump.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: March 17, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Michael E. McCune
  • Integrated thermal management system and environmental control system for a gas turbine engine
    Patent number: 8978351
    Abstract: A gas turbine engine includes a first and second pump driven by a spool. An Air-Oil Cooler downstream of the first pump. An air-air precooler is downstream of the second pump, the air-air precooler downstream of the Air-Oil Cooler.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: March 17, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Allan R. Penda, Brian D. Merry, Jorn A. Glahn, Christoper M. Dye, Nathan Snape
  • Accessory gearbox buffer cooling air pump system
    Patent number: 8967944
    Abstract: A buffer air pump provides pressurized cooling air for cooling components of the gas turbine engine. The buffer air pump is supported on and/or within an accessory gearbox and draws bypass air in through an inlet manifold. An impeller supported within a scroll housing pressurizes the incoming bypass air and directs the pressurized air through passages to a component requiring cooling. The buffer air pump draws in relatively cool air from the bypass flow, pressurizes the air with the impeller and sends the air through conduits and passages within the gas turbine engine to the component that requires cooling such as a bearing assembly.
    Type: Grant
    Filed: August 29, 2011
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jorn A. Glahn, Brian D. Merry, Christopher M. Dye
  • Constant speed transmission for gas turbine engine
    Patent number: 8966875
    Abstract: A gas turbine engine includes a constant speed transmission driven by a spool. The constant speed transmission drives a first pump and a second pump. In a further non-limiting example, the first pump is driven by a first drive shaft which is driven by the constant speed transmission and the second pump is driven by a second drive shaft which is driven by the first shaft through a gearbox to provide a constant speed ratio between the first shaft and the second shaft.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Allan R. Penda, Christopher M. Dye
  • Controllable speed windmill operation of a gas turbine engine through low spool power extraction
    Patent number: 8966876
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan, a geared architecture, a spool which drives the fan through the geared architecture, and at least one component geared to the spool and being operable to control a speed of the spool during a “windmilling” condition. A method of gas turbine engine operations during a “windmilling” condition is also disclosed.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Michael E. McCune
  • Secondary flow arrangement for slotted rotor
    Patent number: 8961132
    Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk and at least one spacer adjacent to the plurality of blades. A flow passage is defined between the rotor disk and the blades and spacer. A plurality of inlets are formed within the spacer to pump air into the flow passage.
    Type: Grant
    Filed: April 30, 2012
    Date of Patent: February 24, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Christopher M. Dye, William K. Ackermann, Stephen P. Muron, Ioannis Alvanos, Brian D. Merry, Arthur M. Salve, James W. Norris
  • Gas turbine engine generator switchable drive
    Patent number: 8943839
    Abstract: A gas turbine engine includes a first spool, a first gear system connected to and driven by the first spool, a second spool, and a second gear system connected to and driven by the second spool. A first starter-generator has a first shaft with a switchable coupling connected to the first shaft. The switchable coupling selectively couples the first starter-generator to the first gear system when the switchable coupling is in a first position and selectively couples the first starter-generator to the second gear system when the switchable coupling is in a second position.
    Type: Grant
    Filed: August 26, 2011
    Date of Patent: February 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu
  • Integrated ceramic matrix composite rotor disk hub geometry for a gas turbine engine
    Patent number: 8944770
    Abstract: A rotor disk for a gas turbine engine includes a CMC hub and a rail integrated with the CMC hub opposite the multiple of CMC airfoils, the rail defines a rail platform section that tapers to a rail inner bore.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: February 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Ioannis Alvanos, Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye
  • Ceramic matrix composite vane structures for a gas turbine engine turbine
    Patent number: 8905711
    Abstract: A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: December 9, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Ioannis Alvanos, Brian D. Merry, Christopher M. Dye
  • Gas turbine engine shaft bearing configuration
    Patent number: 8863491
    Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
    Type: Grant
    Filed: August 28, 2013
    Date of Patent: October 21, 2014
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, Karl L. Hasel
  • ASYMMETRICALLY SLOTTED ROTOR FOR A GAS TURBINE ENGINE
    Publication number: 20140294589
    Abstract: A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.
    Type: Application
    Filed: June 12, 2014
    Publication date: October 2, 2014
    Inventors: Gabriel L. Suciu, Stephen P. Muron, Christopher M. Dye, Ioannis Alvanos, Brian D. Merry
  • REAR MOUNTED REVERSE CORE ENGINE THRUST REVERSER
    Publication number: 20140250863
    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: Application
    Filed: February 26, 2014
    Publication date: September 11, 2014
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Brian D. Merry
  • REVERSE FLOW GAS TURBINE ENGINE AIRFLOW BYPASS
    Publication number: 20140250862
    Abstract: A gas turbine engine has a propulsor including a fan and a power turbine, an engine core aerodynamically connected to the propulsor by a transition duct, and a bypass valve in the transition duct that allows for air from the engine core to bypass the power turbine.
    Type: Application
    Filed: February 26, 2014
    Publication date: September 11, 2014
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • REVERSE FLOW GAS TURBINE ENGINE REMOVABLE CORE
    Publication number: 20140252160
    Abstract: An engine mounting arrangement includes a propulsor mounted to an aircraft wing, and an engine core aerodynamically connected to the propulsor and positioned rearward of the propulsor.
    Type: Application
    Filed: February 26, 2014
    Publication date: September 11, 2014
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • REVERSE CORE ENGINE THRUST REVERSER FOR UNDER WING
    Publication number: 20140252167
    Abstract: A gas turbine engine for mounting under a wing of an aircraft 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 horizontal deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.
    Type: Application
    Filed: February 26, 2014
    Publication date: September 11, 2014
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Brian D. Merry
  • Thermal management system integrated pylon
    Patent number: 8826641
    Abstract: A thermal management system includes at least one heat exchanger in communication with a bypass flow of a gas turbine engine. The placement of the heat exchanger(s) minimizes weight and aerodynamic losses and contributes to overall performance increase over traditional ducted heat exchanger placement schemes.
    Type: Grant
    Filed: January 28, 2008
    Date of Patent: September 9, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye