Patents by Inventor Joseph B. Staubach

Joseph B. Staubach 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).

  • Patent number: 11635022
    Abstract: A method is provided during which an aircraft powerplant is provided. The aircraft powerplant includes a combustor and a water recovery system. The water recovery system includes a condenser and a reservoir. Fuel is combusted within the combustor to provide combustion products. Water is extracted from the combustion products using the condenser. The water recovery system is operated in one of a plurality of modes based on likelihood of contrail formation. The modes include a first mode and a second mode, where the water is collected within the reservoir during the first mode, and where the water passes through the water recovery system during the second mode.
    Type: Grant
    Filed: February 11, 2022
    Date of Patent: April 25, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Neil J. Terwilliger, Joseph B. Staubach, David L. Ma
  • Patent number: 11629647
    Abstract: Waste heat management systems are described. The waste heat management systems include a turbine engine having a compressor section, a combustor section, a turbine section, and a nozzle. The compressor section, the combustor section, the turbine section, and the nozzle define a core flow path that expels through the nozzle. The waste heat management systems also include an auxiliary power unit (APU) system and a waste heat recovery system operably connected to the APU system. The APU system is integrated into a working fluid flow path of the waste heat recovery system.
    Type: Grant
    Filed: March 27, 2020
    Date of Patent: April 18, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Joseph B. Staubach, Amanda J. L. Boucher
  • Patent number: 11614036
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a circumferential array of blades, a low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area and a low pressure turbine section. The low pressure turbine section includes a maximum gas path radius, the blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the blades is equal to or greater than 0.35, and is less than 0.55.
    Type: Grant
    Filed: November 19, 2021
    Date of Patent: March 28, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 11603798
    Abstract: Aircraft engines include a burner section and a turbine section arranged along a shaft, wherein an exhaust from the burner section is directed through the turbine section to drive rotation of the turbine section and a core flow path passes through the burner section and then the turbine section. A condenser assembly is arranged downstream of the turbine section along the core flow path. A cryogenic fuel source is configured to supply fuel to the burner section along a fuel line passing through the condenser assembly and the fuel within the fuel line is configured to pick up heat from the exhaust from the burner section and condense water therefrom.
    Type: Grant
    Filed: February 11, 2022
    Date of Patent: March 14, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Neil J. Terwilliger, Joseph B. Staubach, Joseph E. Turney
  • Publication number: 20230056536
    Abstract: Aircraft propulsion systems including a closed loop-supercritical fluid system having a turbine, a cooler heat exchanger, a compressor, and a recovery heat exchanger arranged along a closed-loop flow path of a supercritical fluid. A shaft is operably coupled to the turbine and configured to be rotationally driven by the turbine. A fan is configured to generate thrust, the fan operably coupled to the shaft to be rotationally driven by the shaft. A burner is configured to combust a fuel and air from the fan to generate a combusted gas and supply said combusted gas to the recovery heat exchanger of the closed loop-supercritical fluid system and out an exhaust nozzle.
    Type: Application
    Filed: August 20, 2021
    Publication date: February 23, 2023
    Inventors: Amanda Jean Learned Boucher, Joseph B. Staubach
  • Publication number: 20230010158
    Abstract: A turbine engine system includes aircraft systems including at least one hydrogen fuel tank, engine systems comprising a compressor section, a combustor section having a burner, and a turbine section, and a hydrogen fuel flow supply line configured to supply hydrogen fuel from the at least one hydrogen fuel tank into the burner for combustion. The turbine engine system has a bypass ratio between 5 to 20.
    Type: Application
    Filed: July 8, 2022
    Publication date: January 12, 2023
    Inventors: Marc J. Muldoon, Joseph B. Staubach, Charles E. Lents
  • Publication number: 20230011956
    Abstract: A turbine engine system includes at least one hydrogen fuel tank, a core flow path heat exchanger in a core flow path; and engine systems located in the core flow path. The engine system including at least a compressor section, a combustor section having a burner, and a turbine section. The core flow path heat exchanger is arranged in the core flow path downstream of the combustor section. The hydrogen fuel is supplied from the at least one hydrogen fuel tank through a hydrogen fuel supply line, passing through the core flow path heat exchanger and then supplied into the burner for combustion.
    Type: Application
    Filed: July 8, 2022
    Publication date: January 12, 2023
    Inventors: James Wiedenhoefer, Joseph B. Staubach, Marc J. Muldoon, Charles E. Lents, Brian M. Holley
  • Publication number: 20220412263
    Abstract: An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.
    Type: Application
    Filed: August 26, 2022
    Publication date: December 29, 2022
    Inventors: Lance L. Smith, Peter Cocks, Joseph B. Staubach
  • Patent number: 11519289
    Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.
    Type: Grant
    Filed: December 6, 2019
    Date of Patent: December 6, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Gabriel L. Suciu, Om P. Sharma, Joseph B. Staubach, Marc J. Muldoon, Jesse M. Chandler, David Lei Ma
  • Patent number: 11511872
    Abstract: Aircraft propulsion systems and aircraft having such propulsion systems are described. The aircraft propulsion systems include a fan, a motor operably connected to the fan by a drive shaft, and an aircraft power generation system operably coupled to the motor to drive rotation of the fan through the drive shaft, wherein the aircraft power generation system comprises a fuel cell configured to generate at least 1 MW of electrical power.
    Type: Grant
    Filed: March 27, 2020
    Date of Patent: November 29, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Joseph B. Staubach, Amanda J. L. Boucher
  • Patent number: 11506124
    Abstract: Gas turbine engines are described. The gas turbine engines include a compressor section, a combustor section, a turbine section, and a nozzle, wherein the compressor section, the combustor section, the turbine section, and the nozzle define a core flow path that expels through the nozzle. A waste heat recovery system is operably connected to the gas turbine engine, the waste heat recovery system having a working fluid. An auxiliary cooling system is configured to provide cooling to a working fluid of the waste heat recovery system.
    Type: Grant
    Filed: March 27, 2020
    Date of Patent: November 22, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Joseph B. Staubach, Amanda J. L. Boucher
  • Publication number: 20220364504
    Abstract: A heat exchanger for heat exchange between a first fluid and a second fluid has a plurality of tube sections, each having; an interior for passing the first fluid; an exterior for exposure to the second fluid; a first leg; a second leg; and a turn joining the first leg to the second leg. A has: fiber members passing between legs of the tube sections; and an end plate.
    Type: Application
    Filed: May 14, 2021
    Publication date: November 17, 2022
    Inventors: Joseph B. Staubach, Marc J. Muldoon, James F. Wiedenhoefer
  • Publication number: 20220364513
    Abstract: An aircraft propulsion systems and aircraft having the same are described. The aircraft propulsion systems have one or more aircraft systems including at least one hydrogen tank and a first heat exchanger and one or more engine systems including at least a main engine core, a second heat exchanger, and a third heat exchanger. The main engine core comprises a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is configured to be supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the first heat exchanger of the aircraft systems, the second heat exchanger of the engine systems, and the third heat exchanger of the engine systems, and then supplied into the burner for combustion.
    Type: Application
    Filed: May 14, 2021
    Publication date: November 17, 2022
    Inventors: Marc J. Muldoon, Joseph B. Staubach, Charles E. Lents
  • Publication number: 20220364802
    Abstract: A heat exchanger for heat exchange between a first fluid and a second fluid has a plurality of tube sections, each comprising; an interior for passing the first fluid; an exterior for exposure to the second fluid; a first leg; a second leg; a turn joining the first leg to the second leg; and a first face and a second face. A support has at least one carbon member engaging the plurality of tube sections.
    Type: Application
    Filed: May 14, 2021
    Publication date: November 17, 2022
    Inventors: Joseph B. Staubach, Marc J. Muldoon, James F. Wiedenhoefer
  • Publication number: 20220349351
    Abstract: A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.
    Type: Application
    Filed: June 15, 2022
    Publication date: November 3, 2022
    Inventors: Charles E. Lents, Joseph B. Staubach, Larry W. Hardin, Jonathan Rheaume
  • Publication number: 20220349656
    Abstract: A heat exchanger has arcuate inlet and outlet manifolds and a plurality of tube banks, each tube bank coupling one of the inlet manifold outlets to an associated one of the outlet manifold inlets. Each tube bank partially nests with one or more others of the tube banks and has: a first header coupled to the associated inlet manifold outlet and the associated the outlet manifold inlet; a second header; and a plurality of tube bundles each having a first end coupled to the associated first header and a second end coupled to the associated second header. A flowpath from the each inlet manifold outlet passes sequentially through flowpath legs formed by each of the tube bundles in the associated tube bank to exit the tube bank to the associated outlet manifold inlet.
    Type: Application
    Filed: June 30, 2022
    Publication date: November 3, 2022
    Applicant: Raytheon Technologies Corporation
    Inventors: Joseph B. Staubach, Amanda Jean Learned Boucher, Jesse M. Chandler
  • Patent number: 11486311
    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a high pressure compressor section and a low pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the low pressure compressor section inlet, and a turbine having a high pressure turbine section and a low pressure turbine section driving the fan through a speed reduction mechanism, wherein the low pressure turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.
    Type: Grant
    Filed: April 14, 2021
    Date of Patent: November 1, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 11480108
    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a low pressure compressor section and a high pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the a low pressure compressor section inlet, a turbine in fluid communication with the combustor, the turbine having a high pressure turbine section and a low pressure turbine that drives the fan, a speed reduction mechanism coupled to the fan and rotatable by the low pressure turbine section to allow the low pressure turbine section to turn faster than the fan, wherein the low pressure turbine section includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas pat
    Type: Grant
    Filed: April 14, 2021
    Date of Patent: October 25, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 11480103
    Abstract: Gas turbine engines are described. The gas turbine engines include a compressor section, a combustor section, a turbine section, a nozzle section, wherein the compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section, and a waste heat recovery system. The waste heat recovery system includes a heat recovery heat exchanger arranged at the nozzle section, wherein the heat recovery heat exchanger is arranged within the nozzle section such that the heat recovery heat exchanger occupies less than an entire area of an exhaust area of the nozzle section and a heat rejection heat exchanger arranged to reduce a temperature of a working fluid of the waste heat recovery system.
    Type: Grant
    Filed: January 17, 2020
    Date of Patent: October 25, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Amanda J. L. Boucher, Joseph B. Staubach
  • Patent number: 11428162
    Abstract: Gas turbine engines are described. The gas turbine engines includes a compressor section, a combustor section, a turbine section, and a nozzle section. The compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section. A cooling duct is provided that is separate from the core flow path. A waste heat recovery system is arranged with a heat rejection heat exchanger arranged within the cooling duct and a blower is arranged within the cooling duct and configured to generate a pressure drop across the heat rejection heat exchanger.
    Type: Grant
    Filed: January 17, 2020
    Date of Patent: August 30, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Joseph B. Staubach, Amanda J. L. Boucher