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).

  • LPC FLOWPATH SHAPE WITH GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    Publication number: 20140248129
    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: Application
    Filed: October 30, 2013
    Publication date: September 4, 2014
    Applicant: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, Lisa I. Brilliant, Becky E. Rose, Yuan Dong, Stanley J. Balamucki
  • GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    Publication number: 20140230403
    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 first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.
    Type: Application
    Filed: August 28, 2013
    Publication date: August 21, 2014
    Applicant: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, Todd A. Davis, Gregory E. Reinhardt, Enzo DiBenedetto
  • Gas turbine engine compressor arrangement
    Patent number: 8807477
    Abstract: A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: August 19, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • Gas turbine engine with low stage count low pressure turbine
    Patent number: 8800914
    Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: August 12, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    Publication number: 20140205439
    Abstract: A gas turbine engine includes a housing including 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. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.
    Type: Application
    Filed: March 19, 2014
    Publication date: July 24, 2014
    Applicant: United Technologies Corporaiton
    Inventors: Brian D. Merry, Gabriel L. Suciu, Karl L. Hasel
  • Asymmetrically slotted rotor for a gas turbine engine
    Patent number: 8784062
    Abstract: A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: July 22, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Stephen P. Muron, Christopher M. Dye, Ioannis Alvanos, Brian D. Merry
  • GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    Publication number: 20140186158
    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: Application
    Filed: August 28, 2013
    Publication date: July 3, 2014
    Applicant: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, Karl L. Hasel
  • GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE
    Publication number: 20140174056
    Abstract: A gas turbine engine comprises a gear train defined along an axis. A spool along the axis drives the gear train and includes a low stage count low pressure turbine. A fan i s rotatable at a fan speed about the axis and driven by the low pressure turbine through the gear train. The fan speed is less than a speed of the low pressure turbine. A core is surrounded by a core nacelle defined about the axis. A fan nacelle i s mounted at least partially 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: February 26, 2014
    Publication date: June 26, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven M. Johnson, Frederick M. Schwarz
  • GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    Publication number: 20140165534
    Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than or equal to about 8.
    Type: Application
    Filed: February 13, 2014
    Publication date: June 19, 2014
    Applicant: United Technologies Corporation
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • FAN WITH INTEGRAL SHROUD
    Publication number: 20140169972
    Abstract: An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.
    Type: Application
    Filed: December 17, 2012
    Publication date: June 19, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Brian D. Merry
  • TURBO COMPRESSOR FOR BLEED AIR
    Publication number: 20140165588
    Abstract: A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.
    Type: Application
    Filed: December 14, 2012
    Publication date: June 19, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nathan Snape, Brian D. Merry, Allan R. Penda, Gabriel L. Suciu
  • GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    Publication number: 20140157756
    Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, the geared arrangement defining a gear reduction ratio greater than or equal to about 2.6. A compressor section includes both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor.
    Type: Application
    Filed: February 13, 2014
    Publication date: June 12, 2014
    Applicant: United Technologies Corporation
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    Publication number: 20140157757
    Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. The turbine section includes a fan drive turbine configured to drive the fan section, a pressure ratio across the fan drive turbine being greater than or equal to about 5. An overall pressure ratio is provided by the combination of the first compressor and the second compressor.
    Type: Application
    Filed: February 13, 2014
    Publication date: June 12, 2014
    Applicant: United Technologies Corporation
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    Publication number: 20140157752
    Abstract: A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. The pressure ratio across the first compressor is greater than or equal to about 7.
    Type: Application
    Filed: February 13, 2014
    Publication date: June 12, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    Publication number: 20140157754
    Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. A pressure ratio across the fan section is less than or equal to about 1.50. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.
    Type: Application
    Filed: February 13, 2014
    Publication date: June 12, 2014
    Applicant: United Technologies Corporation
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    Publication number: 20140157755
    Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section is greater than or equal to about 8.
    Type: Application
    Filed: February 13, 2014
    Publication date: June 12, 2014
    Applicant: United Technologies Corporation
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    Publication number: 20140157753
    Abstract: A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. An overall pressure ratio, being provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor, is greater than or equal to about 35. The pressure ratio across the first compressor is greater than or equal to about 7.
    Type: Application
    Filed: February 13, 2014
    Publication date: June 12, 2014
    Applicant: United Technologies Corporation
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • Gas turbine engine with low stage count low pressure turbine
    Patent number: 8695920
    Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: April 15, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES
    Publication number: 20140096508
    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: December 11, 2013
    Publication date: April 10, 2014
    Applicant: United Technologies Corporation
    Inventors: Michael E. McCune, Brian D. Merry, Gabriel L. Suciu
  • Gas turbine engine compressor arrangement
    Patent number: 8684303
    Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four (4) stages.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: April 1, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson