Patents by Inventor Gabriel L. Suciu

Gabriel L. Suciu 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: 12085025
    Abstract: A gas turbine engine includes, among other things, a propulsor section including a propulsor, a core engine, a gear arrangement that drives the propulsor. A compressor section includes a first compressor section and a second compressor section. A turbine section includes a first turbine and a second turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than 40. The pressure ratio across the second compressor section is between 7 and 15, and the pressure ratio across the first compressor section is between 4 and 8.
    Type: Grant
    Filed: November 7, 2023
    Date of Patent: September 10, 2024
    Assignee: RTX CORPORATION
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • Patent number: 12044183
    Abstract: An example gas turbine engine includes a propulsor assembly consisting of a propulsor and a first turbine. An epicyclic gear train defines a gear reduction ratio of greater than 2.3. A weight of the propulsor assembly is less than 40 percent of a total weight of the gas turbine engine, excluding any nacelle. A first spool includes a first shaft that connects a first compressor and the first turbine. The first shaft drives the propulsor through the gear train to drive the propulsor at a lower speed than the first spool. A second spool includes a second shaft connecting a second compressor and a second turbine. A weight of the propulsor is greater than a weight of the first turbine.
    Type: Grant
    Filed: May 16, 2023
    Date of Patent: July 23, 2024
    Assignee: RTX CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 11946412
    Abstract: A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.
    Type: Grant
    Filed: September 13, 2019
    Date of Patent: April 2, 2024
    Assignee: RTX CORPORATION
    Inventors: Gabriel L. Suciu, James D. Hill
  • Publication number: 20240076050
    Abstract: A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the gear train.
    Type: Application
    Filed: June 28, 2023
    Publication date: March 7, 2024
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • Publication number: 20240068411
    Abstract: A gas turbine engine includes, among other things, a propulsor section including a propulsor, a core engine, a gear arrangement that drives the propulsor. A compressor section includes a first compressor section and a second compressor section. A turbine section includes a first turbine and a second turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than 40. The pressure ratio across the second compressor section is between 7 and 15, and the pressure ratio across the first compressor section is between 4 and 8.
    Type: Application
    Filed: November 7, 2023
    Publication date: February 29, 2024
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • Patent number: 11913349
    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, first and second bearings, and a fan drive shaft interconnecting the gear system and the fan. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. 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: February 1, 2023
    Date of Patent: February 27, 2024
    Assignee: RTX CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu, William K. Ackermann, Daniel Bernard Kupratis, Michael E. McCune
  • Publication number: 20240035419
    Abstract: An example gas turbine engine includes a propulsor assembly consisting of a propulsor and a first turbine. An epicyclic gear train defines a gear reduction ratio of greater than 2.3. A weight of the propulsor assembly is less than 40 percent of a total weight of the gas turbine engine, excluding any nacelle. A first spool includes a first shaft that connects a first compressor and the first turbine. The first shaft drives the propulsor through the gear train to drive the propulsor at a lower speed than the first spool. A second spool includes a second shaft connecting a second compressor and a second turbine. A weight of the propulsor is greater than a weight of the first turbine.
    Type: Application
    Filed: May 16, 2023
    Publication date: February 1, 2024
    Inventors: Frederick M. SCHWARZ, Gabriel L. SUCIU
  • Publication number: 20240003317
    Abstract: A propulsor fan and drive system having reduced noise emission is disclosed. The propulsor fan includes a blade fan having a plurality of blades. The blades may include a dual pin-root design to secure the blade fan to a hub and a shroud at tips of the blades. The blades may include one or more knife edge seals that protrude from a surface of the shroud.
    Type: Application
    Filed: June 9, 2023
    Publication date: January 4, 2024
    Inventors: Gabriel L. Suciu, Matthew Alan Dempsey, Andy Le, Devon Jedamski, Wesley Kenneth Lord
  • Patent number: 11846238
    Abstract: A turbofan gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10. A gear arrangement drives the fan section. A compressor section includes a low pressure compressor section and a high pressure compressor section. A turbine section drives the gear arrangement. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section, and greater than 40. The pressure ratio across the high pressure compressor section is between 7 and 15, and the pressure ratio across the low pressure compressor section is between 4 and 8.
    Type: Grant
    Filed: October 1, 2020
    Date of Patent: December 19, 2023
    Assignee: RTX CORPORATION
    Inventors: Karl L. Hasel, Joseph B. Staubach, Brian D. Merry, Gabriel L. Suciu, Christopher M. Dye
  • Patent number: 11846237
    Abstract: An exemplary gas turbine engine assembly includes a fan section including a fan, a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox includes a set of gears. A compressor is driven by the first towershaft. A transmission couples a starter generator assembly to the set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft in response to rotation of the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft in response to rotation of the second towershaft.
    Type: Grant
    Filed: March 9, 2021
    Date of Patent: December 19, 2023
    Assignee: RTX CORPORATION
    Inventors: Gabriel L. Suciu, Hung Duong, Jonathan F. Zimmitti, William G. Sheridan, Michael E. McCune, Brian Merry
  • Patent number: 11808210
    Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A tap connects to the compressor section. A heat exchanger connects downstream of the tap. A cooling compressor connects downstream of the heat exchanger, and the cooling compressor connects to deliver air to at least one of the rotating components. A core housing has an outer peripheral surface and a fan housing defines an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is disposed within the at least one bifurcation duct.
    Type: Grant
    Filed: May 14, 2018
    Date of Patent: November 7, 2023
    Assignee: RTX CORPORATION
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Brian D. Merry, Nathan Snape
  • Patent number: 11808203
    Abstract: A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.
    Type: Grant
    Filed: September 13, 2019
    Date of Patent: November 7, 2023
    Assignee: RTX CORPORATION
    Inventors: Gabriel L. Suciu, James D. Hill
  • Publication number: 20230323836
    Abstract: A turbofan engine has 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: Application
    Filed: April 8, 2022
    Publication date: October 12, 2023
    Inventors: Paul R. Adams, Frederick M. Schwarz, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Gabriel L. Suciu
  • Patent number: 11781478
    Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.
    Type: Grant
    Filed: January 10, 2022
    Date of Patent: October 10, 2023
    Assignee: RTX CORPORATION
    Inventors: Marc J. Muldoon, Joseph B. Staubach, Jesse M. Chandler, Neil Terwilliger, Gabriel L. Suciu
  • Patent number: 11781490
    Abstract: A gas turbine engine includes a propulsor having a plurality of blades, a compressor section including a first compressor and a second compressor aft of the first compressor. The first compressor includes at least one array of first variable guide vanes that control operation of the first compressor. The second compressor includes at least one array of second variable guide vanes that control operation of the second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture is driven by the second turbine for rotating the propulsor.
    Type: Grant
    Filed: January 20, 2022
    Date of Patent: October 10, 2023
    Assignee: RTX CORPORATION
    Inventors: Glenn Levasseur, Gabriel L. Suciu, Gary M. Stetson
  • Patent number: 11731773
    Abstract: A gas turbine engine includes, among other things, a propulsor section including a rotor, a gear train, a low spool and a high spool. A static structure includes a first case and a second case. A mount system includes a forward mount and an aft mount arranged in a plane containing an engine axis of rotation. The forward mount is secured to the first case. The aft mount is secured to the second case.
    Type: Grant
    Filed: August 6, 2021
    Date of Patent: August 22, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • Publication number: 20230235715
    Abstract: A turbofan engine includes a propulsor section that has a propulsor shaft in driving engagement with a propulsor. An epicyclic gear system has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first turbine section rotates at a first speed, and a second turbine rotates at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area of the first turbine, a second performance quantity is defined as the product of the second speed squared and the second area of the second turbine, and a performance quantity ratio is between 0.5 and 1.5.
    Type: Application
    Filed: April 4, 2023
    Publication date: July 27, 2023
    Inventors: Michael E. McCune, Jason Husband, Frederick M. Schwarz, Daniel Bernard Kupratis, Gabriel L. Suciu, William K. Ackermann
  • Publication number: 20230193830
    Abstract: A gas turbine engine includes a compressor section including a first compressor, a turbine section including a first turbine and a second turbine, a first shaft and a second shaft, the first shaft interconnecting the first turbine and the second compressor, and a geared architecture. The first shaft is supported on a first bearing in an overhung manner. A performance ratio is between 0.5 and 1.5.
    Type: Application
    Filed: February 16, 2023
    Publication date: June 22, 2023
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis, Brian D. Merry, Gabriel L. Suciu, William K. Ackermann
  • Publication number: 20230167752
    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, first and second bearings, and a fan drive shaft interconnecting the gear system and the fan. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. 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: Application
    Filed: February 1, 2023
    Publication date: June 1, 2023
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu, William K. Ackermann, Daniel Bernard Kupratis, Michael E. McCune
  • Patent number: 11661894
    Abstract: An example gas turbine engine includes a propulsor assembly consisting of a fan module and a fan drive turbine module, an epicyclic gear train, a high spool and a low spool. A weight of the propulsor assembly is less than 40% of a total weight of a gas turbine engine. The high spool includes an outer shaft, a high pressure turbine and a high pressure compressor. The low spool includes an inner shaft, a low pressure turbine and a low pressure compressor. The inner shaft drives the propulsor through the gear train to drive the propulsor. A weight of the propulsor is greater than a weight of the low pressure turbine.
    Type: Grant
    Filed: December 20, 2021
    Date of Patent: May 30, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu