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).

  • Adaptive fan reverse core geared turbofan engine with separate cold turbine
    Patent number: 10533493
    Abstract: A turbine engine includes a first fan including a plurality of fan blades rotatable about an axis and a reverse flow core engine section including a core turbine axially forward of a combustor and compressor. The core turbine drives the compressor about the axis and a transmission system. A geared architecture is driven by the transmission system to drive the first fan at a speed less than that of the core turbine. A second fan is disposed axially aft of the first fan and forwarded of the core engine and a second turbine is disposed between the second fan and the core engine for driving the second fan when not coupled to the transmission.
    Type: Grant
    Filed: July 6, 2016
    Date of Patent: January 14, 2020
    Assignee: United Technologies Corporation
    Inventor: Daniel Bernard Kupratis
  • FAN DRIVE GEAR SYSTEM DC MOTOR AND GENERATOR
    Publication number: 20190383157
    Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other things, a fan driven by a fan shaft rotatable about an engine axis; a fan drive electric motor providing a supplemental drive input to the fan; a turbine section driving an input shaft; a geared architecture driven by the input shaft of the turbine section and coupled to the fan shaft to provide a main drive input for driving the fan; and a generator including a rotor supported on the input shaft and a stator disposed on a static structure relative to the rotor, wherein the generator communicates electric power to power the fan drive electric motor.
    Type: Application
    Filed: June 19, 2018
    Publication date: December 19, 2019
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz, William G. Sheridan
  • AIRFOIL COOLING SYSTEM
    Publication number: 20190383165
    Abstract: An airfoil cooling system may include an airfoil that defines a first cooling chamber and a second cooling chamber. The first cooling chamber may be configured to receive a first cooling airflow from a first fluid source and the second cooling chamber may be configured to receive a second cooling airflow from a second fluid source that is different from the first fluid source. The airfoil may be a vane of a gas turbine engine. For example, the vane may be a first vane of a plurality of vanes of a turbine section of the gas turbine engine. The first cooling chamber may be a leading edge chamber of the first vane and the second cooling chamber may be an aft chamber of the first vane that is positioned aft of the leading edge chamber.
    Type: Application
    Filed: June 19, 2018
    Publication date: December 19, 2019
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Daniel Bernard Kupratis
  • CROSSOVER COOLING FLOW FOR MULTI-ENGINE SYSTEMS
    Publication number: 20190383218
    Abstract: A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.
    Type: Application
    Filed: June 19, 2018
    Publication date: December 19, 2019
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Daniel Bernard Kupratis
  • Geared turbofan arrangement with core split power ratio
    Patent number: 10502163
    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 at least a first compressor section and a second compressor section. A power ratio is provided by the combination of the first compressor section and the second compressor section. A method of design a gas turbine engine is also disclosed.
    Type: Grant
    Filed: December 10, 2015
    Date of Patent: December 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • TURBOFAN WITH BLEED SUPERCHARGED AUXILIARY ENGINE
    Publication number: 20190368417
    Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines connected by an inter-engine gas path. The first gas turbine engine has a first spool with a first compressor section, and a second spool with a second compressor section downstream of and rotationally independent from the first compressor section. The second gas turbine engine is configured to provide power to at least one of the first and second spools of the first gas turbine engine. The inter-engine gas path is disposed to receive gas flow bled from a bleed location in the first gas turbine engine downstream of the first compressor section, and to supply this gas flow to an inlet of the second gas turbine engine.
    Type: Application
    Filed: June 4, 2019
    Publication date: December 5, 2019
    Inventors: Neil Terwilliger, Daniel Bernard Kupratis, Christopher J. Hanlon
  • HYBRID AMPLIFICATION OF HIGH SPOOL MOTORING VIA LOW SPOOL POWER EXTRACTION AND MOTORING OF A DIFFERENTIAL GEARED GENERATOR
    Publication number: 20190368424
    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: Application
    Filed: May 29, 2018
    Publication date: December 5, 2019
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, William G. Sheridan
  • HYBRID ELECTRIC FAN WITH STALL FREE LOW PRESSURE COMPRESSOR
    Publication number: 20190353104
    Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes among other possible things, a fan section including a plurality of fan blades, a first electric motor assembly that provides a first drive input for driving the fan blades about an axis, a turbine section, and a geared architecture driven by the turbine section and coupled to the fan section to provide a second drive input for driving the fan blades, and second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure controls a speed of the fan blades provided by a combination of the first drive input and the second drive input.
    Type: Application
    Filed: May 16, 2018
    Publication date: November 21, 2019
    Inventors: Daniel Bernard Kupratis, Christopher J. Hanlon, William G. Sheridan
  • Gas turbine engine with cold turbine and multiple core flowpaths
    Patent number: 10393067
    Abstract: A gas turbine engine includes a spool configured to rotate about an axial centerline. The spool includes a fan rotor and a cold turbine rotor. The fan rotor is rotatably driven by the cold turbine rotor. A cold turbine inlet passage is configured to direct an airflow along a radial inward trajectory to the cold turbine rotor.
    Type: Grant
    Filed: August 25, 2016
    Date of Patent: August 27, 2019
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Francis R. Moon, Arthur W. Utay
  • Split compressor turbine engine
    Patent number: 10385774
    Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.
    Type: Grant
    Filed: September 19, 2016
    Date of Patent: August 20, 2019
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Tania Bhatia Kashyap, Mark F. Zelesky, Arthur W. Utay, Gabriel L. Suciu, Thomas N. Slavens, Kevin L. Rugg, Brian Merry
  • Gas turbine engine with two-spool fan and variable vane turbine
    Patent number: 10378454
    Abstract: A method of operating a gas turbine engine includes modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust.
    Type: Grant
    Filed: January 13, 2016
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Daniel Bernard Kupratis
  • Twin centrifugal single spool engine
    Patent number: 10364041
    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: Grant
    Filed: July 25, 2016
    Date of Patent: July 30, 2019
    Assignee: 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
  • Cooling air heat exchanger scoop
    Patent number: 10364749
    Abstract: A heat exchanger for a gas turbine engine includes a cooling air scoop that has a leading edge nose that is positioned adjacent to a downstream-most stator cascade of a fan section of the gas turbine engine. The cooling air scoop subtends only a sector of a circumference of the gas turbine engine. The heat exchanger also includes a cold side that is connected to the cooling air scoop and a hot side that is connected to a compressor section of the gas turbine engine.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: July 30, 2019
    Assignee: United Technologies Corporation
    Inventors: Paul R. Hanrahan, Daniel Bernard Kupratis
  • GAS TURBINE ENGINE WITH FAN TIED COMPRESSOR
    Publication number: 20190186357
    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including fan blades, an outer housing that surrounds the fan to define a bypass flow path, a compressor section in fluid communication with the fan, the compressor section including a low pressure compressor section and a high pressure compressor section, a turbine section including a fan drive turbine section driving the fan and the low pressure compressor section and a high pressure turbine section driving the high pressure compressor section. A gear reduction including an epicyclic gear train is between the fan drive turbine section and the low pressure compressor section such that the low pressure compressor section and the fan are rotatable at a common speed and such that the fan is rotatable at a lower speed than the fan drive turbine section.
    Type: Application
    Filed: February 22, 2019
    Publication date: June 20, 2019
    Inventors: Gabriel L. Suciu, Frederick M. Schwarz, William K. Ackermann, Daniel Bernard Kupratis
  • Gas turbine engine with stage dependent material selection for blades and disk
    Patent number: 10309232
    Abstract: A gas turbine engine includes a shaft defining an axis of rotation and a fan driving turbine configured to drive the shaft. The fan driving turbine comprises a plurality of stages that are spaced apart from each other along the axis. Each stage includes a turbine disk comprised of a disk material and a plurality of turbine blades comprised of a blade material. The disk material and the blade material for one of the plurality of stages is selected based on a location of the one stage relative to the other stages of the plurality of stages.
    Type: Grant
    Filed: March 13, 2012
    Date of Patent: June 4, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis
  • GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE
    Publication number: 20190153960
    Abstract: A gas turbine engine turbine has a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, the high pressure turbine rotatable with the high pressure compressor as a high pressure spool in a first direction about an engine longitudinal axis, the low pressure turbine rotatable as a low pressure spool in the first direction about the engine longitudinal axis, a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, a fan section including a fan having a plurality of fan blades, the fan connected to the low pressure spool via a geared architecture such that the fan is rotatable about the engine longitudinal axis in a second direction opposed to the first direction, and a bypass ratio greater than 6.
    Type: Application
    Filed: November 12, 2018
    Publication date: May 23, 2019
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis
  • Gas turbine engine with high speed low pressure turbine section and bearing support features
    Patent number: 10287914
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
    Type: Grant
    Filed: April 4, 2017
    Date of Patent: May 14, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu, William K. Ackermann, Daniel Bernard Kupratis, Michael E. McCune
  • Geared turbofan gas turbine engine architecture
    Patent number: 10288011
    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.
    Type: Grant
    Filed: April 17, 2017
    Date of Patent: May 14, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David P. Houston, Daniel Bernard Kupratis, Frederick M. Schwarz
  • Geared turbofan gas turbine engine architecture
    Patent number: 10288010
    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.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: May 14, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David P. Houston, Daniel Bernard Kupratis, Frederick M. Schwarz
  • Gas turbine engine airfoil with auxiliary flow channel
    Patent number: 10280757
    Abstract: A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure side surface and a suction side surface that join together at a leading edge and a trailing edge and a flow channel that extends between the pressure side surface and the suction side surface.
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: May 7, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz