Patents by Inventor Daniel Bernard Kupratis

Daniel Bernard Kupratis 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 stream diverter
    Patent number: 10787996
    Abstract: In accordance with one aspect of the disclosure, a stream diverter for a gas turbine engine is disclosed. The stream diverter may include a first air duct, a second air duct, a third air duct, and a door operatively associated with the second and third air ducts of the gas turbine engine. The door may have at least an open position allowing air from the second air duct to flow into the third air duct and a closed position preventing air from flowing between the ducts.
    Type: Grant
    Filed: December 19, 2016
    Date of Patent: September 29, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Francis R. Moon
  • VARIABLE REACTION FREE WHEEL FOR A TURBINE SECTION OF A GAS TURBINE ENGINE
    Publication number: 20200291784
    Abstract: A turbine section for a gas turbine engine includes a variable reaction free wheel downstream of the first static vane structure and a turbine rotor downstream of the variable reaction free wheel. A method of generating thrust for a gas turbine engine, includes rotating a variable reaction free wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.
    Type: Application
    Filed: March 12, 2019
    Publication date: September 17, 2020
    Applicant: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Jacob Shubinski
  • Turbofan with motorized rotating inlet guide vane
    Patent number: 10738694
    Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a fan including a plurality of fan blades rotatable about an axis, a plurality of inlet guide vanes mounted forward of the plurality of fan blades, the plurality of inlet guide vanes selectively rotatable about the axis independent of the plurality of fan blades; and a motor for controlling rotation of the plurality of inlet guide vanes about the axis.
    Type: Grant
    Filed: August 23, 2018
    Date of Patent: August 11, 2020
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Dmitriy B. Sidelkovskiy, Neil Terwilliger, William G. Sheridan
  • ELECTRIC ENHANCED TRANSMISSION FOR MULTI-SPOOL LOAD-SHARING TURBOFAN ENGINE
    Publication number: 20200240331
    Abstract: A turbofan engine includes a first spool including a first turbine, and a first tower shaft engaged to the first spool. A second spool includes a second turbine, and a second tower shaft is engaged to the second spool. A superposition gearbox includes a sun gear, a plurality of intermediate gears engaged to the sun gear, and is supported in a carrier and a ring gear circumscribing the intermediate gears. The first tower shaft or the second tower shaft drives one of the intermediate gears. A drive motor is engaged to drive the sun gear, an inner electric motor, a stator disposed radially outside of the inner electric motor, and an outer electric motor disposed radially outside the stator. A first load on the first spool and a second load on the second spool is adjusted by operation of at least one of the inner electric motor and the outer electric motor.
    Type: Application
    Filed: January 30, 2019
    Publication date: July 30, 2020
    Inventors: Daniel Bernard Kupratis, Coy Bruce Wood
  • Turbofan with motorized rotating inlet guide vane
    Patent number: 10724395
    Abstract: A gas turbine engine includes a turbine section that is configured to drive a fan through a fan shaft. The fan includes a plurality of fan blades rotatable about an axis of rotation of the gas turbine engine. A fan nacelle includes a first electrical machine component. The fan is located within the fan nacelle. A plurality of fan inlet guide vanes includes a second electrical machine component. The plurality of fan inlet guide vanes are rotatable about the axis.
    Type: Grant
    Filed: October 1, 2018
    Date of Patent: July 28, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Sean Danby
  • Hybrid amplification of high spool motoring via low spool power extraction and motoring of a differential geared generator
    Patent number: 10718271
    Abstract: A power extraction and amplification system for a gas turbine engine is disclosed. In various embodiments, the power extraction and amplification system includes a low spool tower shaft configured for engagement with a low speed spool, a high spool tower shaft configured for engagement with a high speed spool, a first motor, a generator, a differential gear box operably coupled to the low spool tower shaft, to the first motor and to the generator, and a second motor operably coupled to the generator and the high spool tower shaft.
    Type: Grant
    Filed: May 29, 2018
    Date of Patent: July 21, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, William G Sheridan
  • LOW PRESSURE COMPRESSOR CONTROL FOR A GAS TURBINE ENGINE
    Publication number: 20200182158
    Abstract: A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.
    Type: Application
    Filed: October 17, 2019
    Publication date: June 11, 2020
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Daniel Bernard Kupratis
  • Combined two engine cycle with at least one recuperated cycle engine for rotor drive
    Patent number: 10669933
    Abstract: A drive architecture comprises a rotor and a gearbox for driving the rotor. A pair of input gears provides rotational drive to the gearbox. A first recuperative cycle engine drives one of the pair of gears and a second engine drives the other of the pair of gears. The first recuperative cycle engine and the second engine are both gas turbine engines. A power takeoff from a drive shaft of the second engine supplies rotational drive to drive at least one component in the first recuperative cycle drive.
    Type: Grant
    Filed: July 10, 2018
    Date of Patent: June 2, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Daniel Bernard Kupratis
  • GEARED TURBOFAN ARRANGEMENT WITH CORE SPLIT POWER RATIO
    Publication number: 20200109684
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a compressor section including a low pressure compressor and a second compressor section, and a turbine section including a fan drive turbine and a high pressure turbine. The fan drive turbine drives the low pressure compressor and a gear arrangement to drive the fan section. A core split power ratio is provided by power input to the high pressure compressor divided by a power input to the low pressure compressor measured in horsepower.
    Type: Application
    Filed: November 15, 2019
    Publication date: April 9, 2020
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • DIFFERENTIAL GEARED AMPLIFICATION OF AUXILIARY POWER UNIT
    Publication number: 20200102885
    Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.
    Type: Application
    Filed: September 28, 2018
    Publication date: April 2, 2020
    Inventors: Daniel Bernard Kupratis, Neil Terwilliger, Michael M. Romero
  • TURBOFAN WITH MOTORIZED ROTATING INLET GUIDE VANE
    Publication number: 20200102849
    Abstract: A gas turbine engine includes a turbine section that is configured to drive a fan through a fan shaft. The fan includes a plurality of fan blades rotatable about an axis of rotation of the gas turbine engine. A fan nacelle includes a first electrical machine component. The fan is located within the fan nacelle. A plurality of fan inlet guide vanes includes a second electrical machine component. The plurality of fan inlet guide vanes are rotatable about the axis.
    Type: Application
    Filed: October 1, 2018
    Publication date: April 2, 2020
    Inventors: Daniel Bernard Kupratis, Sean Danby
  • Geared architecture with inducer for gas turbine engine
    Patent number: 10584642
    Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan. A first compressor section is arranged in an axial flow relationship with the second compressor and the first and second turbines. A geared architecture operatively connects the first shaft and the fan. An inducer operative couples to the gear train.
    Type: Grant
    Filed: July 5, 2018
    Date of Patent: March 10, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • TURBOFAN WITH MOTORIZED ROTATING INLET GUIDE VANE
    Publication number: 20200063657
    Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a fan including a plurality of fan blades rotatable about an axis, a plurality of inlet guide vanes mounted forward of the plurality of fan blades, the plurality of inlet guide vanes selectively rotatable about the axis independent of the plurality of fan blades; and a motor for controlling rotation of the plurality of inlet guide vanes about the axis.
    Type: Application
    Filed: August 26, 2019
    Publication date: February 27, 2020
    Inventors: Daniel Bernard Kupratis, Dmitriy B. Sidelkovskiy, Neil Terwilliger, William G. Sheridan
  • HYBRID GAS TURBOFAN POWERED SUB-IDLE DESCENT MODE
    Publication number: 20200056497
    Abstract: A method of operating an aircraft hybrid gas turbofan during an idle mode of operation includes reducing a fuel flow to a primary gas turbine engine and boosting a high spool of the primary gas turbine engine using a secondary gas turbine engine via a first power linkage connecting the primary and secondary gas turbine engines, such that a net fuel reduction is achieved. The net fuel reduction accounts for fuel flow to the primary gas turbine engine and fuel flow to the secondary gas turbine engine.
    Type: Application
    Filed: June 4, 2019
    Publication date: February 20, 2020
    Inventors: Neil Terwilliger, Daniel Bernard Kupratis, Michael M. Romero
  • GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES
    Publication number: 20200049077
    Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.
    Type: Application
    Filed: October 10, 2019
    Publication date: February 13, 2020
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis, Brian D. Merry, Gabriel L. Suciu, William K. Ackermann
  • ADAPTIVE ENGINE WITH BOOST SPOOL
    Publication number: 20200040848
    Abstract: A gas turbine engine includes a first spool, a second spool, a primary combustor, and a diffuser. The first spool includes a first compressor rotationally driven by a first turbine via a first shaft. The second spool includes a second compressor driven by a second turbine via a second shaft. The first compressor, the diffuser, and the primary combustor are arranged in series to provide a compressed airflow discharged from the first compressor to the primary combustor via the diffuser, which includes walls that diverge towards the primary combustor. The second compressor is fluidly coupled to the diffuser to receive at least a portion of the compressed airflow from the diffuser. The second turbine is fluidly coupled to the diffuser to discharge an expanded airflow to the diffuser.
    Type: Application
    Filed: August 1, 2018
    Publication date: February 6, 2020
    Inventors: Paul R. Hanrahan, Daniel Bernard Kupratis
  • MULTI-ENGINE ARCHITECTURE WITH LINKAGES TO MULTIPLE SPOOLS
    Publication number: 20200032702
    Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.
    Type: Application
    Filed: June 4, 2019
    Publication date: January 30, 2020
    Inventors: Daniel Bernard Kupratis, Neil Terwilliger, Christopher J. Hanlon
  • GEARED TURBOFAN ARRANGEMENT WITH CORE SPLIT POWER RATIO
    Publication number: 20200025069
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan having a plurality of fan blades, and a nacelle surrounding the plurality of fan blades, a compressor section including a low pressure compressor and a high pressure compressor, the low pressure compressor including a plurality of stages, and the high pressure compressor including 6 or more stages. A turbine section includes a fan drive turbine that drives the fan section through a gear arrangement, and including a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor, the power ratio defined by the second power input divided by the first power input, and the power ratio is less than or equal to 1.
    Type: Application
    Filed: March 4, 2019
    Publication date: January 23, 2020
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • AIRCRAFT HYBRID PROPULSION FAN DRIVE GEAR SYSTEM DC MOTORS AND GENERATORS
    Publication number: 20200023982
    Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
    Type: Application
    Filed: July 19, 2018
    Publication date: January 23, 2020
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz, William G. Sheridan, Glenn Levasseur
  • DIVERSION OF FAN AIR TO PROVIDE COOLING AIR FOR GAS TURBINE ENGINE
    Publication number: 20200025080
    Abstract: A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages.
    Type: Application
    Filed: March 19, 2019
    Publication date: January 23, 2020
    Inventors: Daniel Bernard Kupratis, Anthony R. Bifulco