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).

  • GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE
    Publication number: 20150315977
    Abstract: A gas turbine engine includes a core nacelle defined about an engine axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A gear train is defined along an engine axis. The gear train defines a gear reduction ratio of greater than or equal to about 2.3. A fan drive turbine along the engine axis which drives the gear train. The fan drive turbine includes three to six (3-6) stages. A fan is configured for rotation within the fan nacelle for operation at a fan pressure ratio less than about 1.45. A fan variable area nozzle is axially movable relative to said fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. A high bypass gas turbine engine is also disclosed.
    Type: Application
    Filed: June 30, 2015
    Publication date: November 5, 2015
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • TWO SPOOL GAS GENERATOR WITH IMPROVED PRESSURE SPLIT
    Publication number: 20150315974
    Abstract: A gas turbine engine has a first shaft including a first compressor rotor. A second shaft includes a second compressor rotor disposed upstream of the first compressor rotor. The second compressor rotor has a first overall pressure ratio. The first compressor rotor has a second overall pressure ratio, with a ratio of the first overall pressure ratio to the second overall pressure ratio being greater than or equal to about 3.0.
    Type: Application
    Filed: May 29, 2013
    Publication date: November 5, 2015
    Inventors: Gabriel L. Suciu, Brian D. Merry, Karl L. Hasel, Jessica Tsay
  • GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE
    Publication number: 20150300207
    Abstract: A gas turbine engine comprises a gear train defined along an engine axis. A spool along the engine axis drives the gear train, and includes a low stage count downstream turbine. A fan rotates at a fan speed about the engine axis and drives the downstream turbine through the gear train. The fan speed is less than a speed of the downstream turbine. A core is surrounded by a core housing defined about the engine axis. A fan nacelle is mounted around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10).
    Type: Application
    Filed: June 30, 2015
    Publication date: October 22, 2015
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • TWO SPOOL GAS GENERATOR TO CREATE FAMILY OF GAS TURBINE ENGINES
    Publication number: 20150300250
    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: Application
    Filed: May 29, 2013
    Publication date: October 22, 2015
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • Constant speed pump system for engine ECS loss elimination
    Patent number: 9163562
    Abstract: A gas turbine engine comprises a fan configured to produce propulsive thrust from a fan discharge air stream. A bypass duct is located between a cowl and an engine core, the bypass duct is fluidly coupled to the fan. An impeller pump has an intake manifold fluidly coupled to the bypass duct. The impeller pump has an outlet coupled to an outlet duct fluidly coupled to an environmental control system, wherein the impeller pump is configured to raise pressure of the fan discharge air stream and pump the fan discharge air into the environmental control system for cooling. An integrated drive pump is connected to the impeller pump for driving the impeller pump at a constant speed. The integrated drive pump is positioned on the engine core.
    Type: Grant
    Filed: March 14, 2012
    Date of Patent: October 20, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Jorn A. Glahn, Christopher M. Dye
  • Constant-speed pump system for engine thermal management system AOC reduction and environmental control system loss elimination
    Patent number: 9151224
    Abstract: A gas turbine engine has a spool, a towershaft connected to the spool and an impeller pump. An integrated drive pump is connected to the towershaft and to the impeller pump for driving the impeller pump at a constant speed. The integrated drive pump is positioned on an engine core. The gas turbine engine includes a fan and a bypass duct located between a cowl and the engine core. The gas turbine engine includes an intake manifold for the impeller pump, and the intake manifold receives air from the bypass duct.
    Type: Grant
    Filed: March 14, 2012
    Date of Patent: October 6, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Jorn A. Glahn, Brian D. Merry, Christopher M. Dye
  • INTEGRATED THERMAL SYSTEM FOR A GAS TURBINE ENGINE
    Publication number: 20150267617
    Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.
    Type: Application
    Filed: June 3, 2015
    Publication date: September 24, 2015
    Inventors: Gabriel L. Suciu, Allan R. Penda, Brian D. Merry, Christopher M. Dye, Nathan Snape
  • Pump system for TMS AOC reduction
    Patent number: 9121346
    Abstract: An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging air into a discharge manifold. The discharge manifold containing at least one heat exchanger which forms part of a thermal management system.
    Type: Grant
    Filed: March 14, 2012
    Date of Patent: September 1, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Jorn A. Glahn
  • Gas turbine engine compressor arrangement
    Patent number: 9121367
    Abstract: A gas turbine engine has a fan section, a gear arrangement configured to drive the fan section, a compressor section, including both a low pressure compressor section and a high pressure compressor section. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.
    Type: Grant
    Filed: April 24, 2013
    Date of Patent: September 1, 2015
    Assignee: United Technologies Corporation
    Inventors: Hasel Karl, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • Distributed lubrication system
    Patent number: 9109464
    Abstract: A gas turbine engine includes a spool, a gearbox having gearing driven by the spool, and a lubrication system. The lubrication system includes a first heat exchanger positioned in a first air flow path, a second heat exchanger positioned in a second air flow path, and a lubrication pump fluidically connected to both the first heat exchanger and the second heat exchanger. A first air fan is driven by the gearbox for inducing air flow through the first air flow path. A second air fan is driven by an electric motor for inducing air flow through the second air flow path.
    Type: Grant
    Filed: August 31, 2011
    Date of Patent: August 18, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jorn A. Glahn, Brian D. Merry, Christopher M. Dye, Nathan Snape, Matthew J. Howlett, Matthew G. Dixon
  • Integrated actuator module for gas turbine engine
    Patent number: 9097137
    Abstract: An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing.
    Type: Grant
    Filed: December 15, 2011
    Date of Patent: August 4, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, James S. Elder
  • Integrated thermal system for a gas turbine engine
    Patent number: 9080511
    Abstract: An integrated thermal system for a gas turbine engine includes an Air-Oil Cooler and an Air-Air PreCooler within a housing, the Air-Air PreCooler downstream of the Air-Oil Cooler.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: July 14, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Allan R. Penda, Brian D. Merry, Christopher M. Dye, Nathan Snape
  • Counter-rotating low pressure turbine with gear system mounted to mid turbine frame
    Patent number: 9080512
    Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades. The gear system is mounted to a mid-turbine frame.
    Type: Grant
    Filed: February 29, 2012
    Date of Patent: July 14, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • Integrated inlet vane and strut
    Patent number: 9068460
    Abstract: A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length.
    Type: Grant
    Filed: March 30, 2012
    Date of Patent: June 30, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, Lisa I. Brilliant
  • Fan case thrust reverser
    Patent number: 9038367
    Abstract: A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis, a thrust reverser cascade section downstream of the blade containment section and a Fan Exit Guide Vane section downstream of the thrust reverser cascade section.
    Type: Grant
    Filed: September 16, 2011
    Date of Patent: May 26, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Allan R. Penda, Christopher M. Dye, Jay Bhatt
  • LPC flowpath shape with gas turbine engine shaft bearing configuration
    Patent number: 9038366
    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 flowpath. 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 in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. 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: October 30, 2013
    Date of Patent: May 26, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brian D. Merry, Gabriel L. Suciu, Lisa I. Brilliant, Becky E. Rose, Yuan Dong, Stanley J. Balamucki
  • Counter rotating low pressure turbine with splitter gear system
    Patent number: 9028200
    Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine 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 12, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Michael E. McCune, Shankar S. Magge
  • GAS TURBINE ENGINE VARIABLE PITCH FAN BLADE
    Publication number: 20150125259
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section.
    Type: Application
    Filed: February 24, 2014
    Publication date: May 7, 2015
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • CONJOINED REVERSE CORE FLOW ENGINE ARRANGEMENT
    Publication number: 20150121838
    Abstract: A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.
    Type: Application
    Filed: February 26, 2014
    Publication date: May 7, 2015
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • REVERSE CORE FLOW ENGINE MOUNTING ARRANGEMENT
    Publication number: 20150121896
    Abstract: A mounting arrangement for an aircraft engine includes a mounting structure attached to an aircraft body and not directly connected to an engine core of the aircraft engine, a propulsor mounted to the mounting structure, and a thrust reverser mounted directly to either the propulsor or mounting structure.
    Type: Application
    Filed: February 26, 2014
    Publication date: May 7, 2015
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Brian D. Merry