Patents by Inventor Frederick M. Schwarz

Frederick M. Schwarz 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).

  • Intercooled cooling air with advanced cooling system
    Patent number: 10808619
    Abstract: A tap is connected to a location upstream of a downstream most location in a compressor to a heat exchanger. Downstream of the heat exchanger is a shut off valve and a cooling compressor. The cooling compressor is connected to a chamber provided with a check valve configured to selectively allow flow directly from a downstream location in the compressor. There is a system for stopping operation of the cooling compressor, and a control for closing the shut off valve. The cooling compressor is configured to compress air to a greater pressure than the higher pressure, such that the check valve is configured to maintain a closed position, but when said cooling compressor is not providing compressed air, the at least one check valve is configured to allow said higher pressure flow into the chamber. A method is also disclosed.
    Type: Grant
    Filed: April 19, 2018
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, Taryn Narrow
  • Geared turbofan with four star/planetary gear reduction
    Patent number: 10801355
    Abstract: A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.
    Type: Grant
    Filed: October 29, 2018
    Date of Patent: October 13, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, William G. Sheridan, Michael E. McCune, Gabriel L. Suciu
  • Intercooled cooled cooling integrated air cycle machine
    Patent number: 10794290
    Abstract: A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increases a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A valve is downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.
    Type: Grant
    Filed: November 8, 2017
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Nathan Snape, Joseph Brent Staubach, Frederick M. Schwarz
  • Non-contact seal assembly for rotational equipment with linkage between adjacent rotors
    Patent number: 10794208
    Abstract: An assembly is provided for rotational equipment such as a gas turbine engine for an aircraft propulsion system. This assembly includes a stator, a rotor and a seal assembly. The rotor extends axially along a centerline. The rotor includes a linkage, a first rotor disk, and a second rotor disk. The linkage extends axially from the first rotor disk to the second rotor disk. The linkage is removably attached to the second rotor disk. The seal assembly is configured for sealing a gap radially between the stator and the linkage. The seal assembly includes a hydrostatic non-contact seal.
    Type: Grant
    Filed: July 8, 2015
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, William K. Ackermann
  • Air foil with galvanic protection
    Patent number: 10794193
    Abstract: An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.
    Type: Grant
    Filed: August 23, 2016
    Date of Patent: October 6, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Mary Colby, Paul R Hanrahan, Frederick M Schwarz
  • Geared turbofan gas turbine engine architecture
    Patent number: 10794292
    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
    Type: Grant
    Filed: January 31, 2017
    Date of Patent: October 6, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • Turbine section of high bypass turbofan
    Patent number: 10794293
    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
    Type: Grant
    Filed: July 2, 2018
    Date of Patent: October 6, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Engine bleed system with multi-tap bleed array
    Patent number: 10794295
    Abstract: An engine bleed control system for a gas turbine engine of an aircraft is provided. The engine bleed control system includes a multi-tap bleed array including engine bleed taps coupled to a compressor source of a lower pressure compressor section before a highest pressure compressor section of the gas turbine engine. A highest stage of the engine bleed taps has a maximum bleed temperature below an auto-ignition point of a fuel-air mixture of the aircraft at idle engine power at a maximum aircraft altitude and a pressure suitable for pressurizing the aircraft at the maximum aircraft altitude. The engine bleed control system also includes a plurality of valves operable to extract bleed air from each of the engine bleed taps. A controller is operable to selectively open and close each of the valves based on a bleed air demand and control delivery of the bleed air to an aircraft use.
    Type: Grant
    Filed: March 15, 2016
    Date of Patent: October 6, 2020
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventor: Frederick M. Schwarz
  • Cooled cooling air system for a turbofan engine
    Patent number: 10794288
    Abstract: An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core. The cooled cooling air system including an air-air heat exchanger.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, Paul W. Duesler
  • Advanced distributed engine architecture-design alternative
    Patent number: 10794273
    Abstract: A gas turbine engine according to the present disclosure includes a first compressor and a first turbine for driving the first compressor. A core section includes a second compressor and a second turbine for driving the second compressor. A third turbine is arranged fluidly downstream of the first turbine and the second turbine and configured to drive a power take-off. A first duct system is arranged fluidly between the low-pressure compressor and the core section. The first duct system is arranged to reverse fluid flow before entry into the core section.
    Type: Grant
    Filed: July 1, 2015
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Jeffery F. Perlak, Joseph B. Staubach, Gabriel L. Suciu, James D. Hill, Frederick M. Schwarz
  • Geared turbofan architecture for regional jet aircraft
    Patent number: 10794291
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan situated at an inlet of a bypass passage, and a core engine configured to drive the fan. The core engine includes a low pressure compressor section driven by a low pressure turbine section, and a high pressure compressor section driven by a high pressure turbine section. The fan has a fan diameter, Dfan, and the high pressure compressor section has a compressor diameter, Dcomp. The fan diameter Dfan and the compressor diameter Dcomp have an interdependence represented by a scalable ratio Dfan/Dcomp that is greater than about 4.5.
    Type: Grant
    Filed: February 4, 2016
    Date of Patent: October 6, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Frederick M. Schwarz
  • Fan drive gear system DC motor and generator
    Patent number: 10794216
    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: Grant
    Filed: June 19, 2018
    Date of Patent: October 6, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz, William G. Sheridan
  • Low-power bowed rotor prevention and monitoring system
    Patent number: 10787933
    Abstract: A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes a full authority digital engine control (FADEC) that controls operation of the gas turbine engine in a full-power mode and controls operation of the core turning motor to drive rotation of the engine core using a reduced power draw when the FADEC is partially depowered in a low-power bowed rotor prevention mode.
    Type: Grant
    Filed: June 20, 2016
    Date of Patent: September 29, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jesse W. Clauson, Frederick M. Schwarz
  • BOWED ROTOR START MITIGATION IN A GAS TURBINE ENGINE USING AIRCRAFT-DERIVED PARAMETERS
    Publication number: 20200291860
    Abstract: A bowed rotor start mitigation system for a gas turbine engine of an aircraft is provided. The bowed rotor start mitigation system includes a motoring system and a controller coupled to the motoring system and an aircraft communication bus. The controller is configured to determine at least one inferred engine operating thermal parameter based on at least one aircraft-based parameter received on the aircraft communication bus, where the at least one inferred engine operating thermal parameter is based on data describing a history of the aircraft before an engine shutdown. The motoring system is controlled to drive rotation of a starting spool of the gas turbine engine below an engine idle speed based on determining that the at least one inferred engine operating thermal parameter is within a preselected range.
    Type: Application
    Filed: January 17, 2020
    Publication date: September 17, 2020
    Inventors: Frederick M. Schwarz, Amy R. Grace
  • GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE
    Publication number: 20200284222
    Abstract: A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a high spool, and a low spool including a low pressure turbine that drives the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.
    Type: Application
    Filed: May 7, 2019
    Publication date: September 10, 2020
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • GAS TURBINE ENGINE WITH GEARED ARCHITECTURE
    Publication number: 20200277918
    Abstract: A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. A gear system is connected to the fan shaft and a plurality of planetary gears. A first set of opposed angled ring gear teeth are separated from a second set of opposed angled ring gear teeth. A lubricant flow path is located axially between the first set of opposed angled ring gear teeth and the second set of opposed angled ring gear teeth. An annular channel axially is aligned with the lubricant flow path. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1. A low fan pressure ratio is less than 1.45 across the fan blade alone.
    Type: Application
    Filed: January 7, 2020
    Publication date: September 3, 2020
    Inventors: Michael E. McCune, Lawrence E. Portlock, Frederick M. Schwarz
  • Hybrid electric aircraft system with distributed propulsion
    Patent number: 10759545
    Abstract: A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.
    Type: Grant
    Filed: June 19, 2018
    Date of Patent: September 1, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Zubair Ahmed Baig
  • Cooling air architecture for compact size and performance improvement
    Patent number: 10760492
    Abstract: A gas turbine engine has a fan and a compressor section with a first lower pressure location and a second higher pressure location. A heat exchanger and a higher pressure tap from the second higher pressure location pass through the heat exchanger. Air in the higher pressure tap is cooled by air from a lower pressure tap from the first lower pressure location. A valve controls flow to the heat exchanger from the lower pressure tap, the valve being controlled to limit flow from the lower pressure tap under certain conditions.
    Type: Grant
    Filed: April 13, 2016
    Date of Patent: September 1, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: John W. Golan, Frederick M. Schwarz
  • Geared turbofan engine gearbox arrangement
    Patent number: 10760488
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a plurality of fan blades. The plurality of fan blades has a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath. A core engine includes a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section. A method of designing a gas turbine engine is also disclosed.
    Type: Grant
    Filed: February 2, 2016
    Date of Patent: September 1, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, William G. Sheridan
  • Geared turbine engine with relatively lightweight propulsor module
    Patent number: 10753286
    Abstract: An example gas turbine engine includes a propulsor assembly including a fan and a fan drive turbine. A weight of the propulsor assembly is less than about 40% of a total weight of the gas turbine engine.
    Type: Grant
    Filed: October 5, 2018
    Date of Patent: August 25, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu