Patents by Inventor William K. Ackermann

William K. Ackermann 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).

  • Geared Architecture for High Speed and Small Volume Fan Drive Turbine
    Publication number: 20170226935
    Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.
    Type: Application
    Filed: April 12, 2017
    Publication date: August 10, 2017
    Inventors: Michael E. McCune, Jason Husband, Frederick M. Schwarz, Daniel Bernard Kupratis, Gabriel L. Suciu, William K. Ackermann
  • Geared Architecture for High Speed and Small Volume Fan Drive Turbine
    Publication number: 20170218850
    Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.
    Type: Application
    Filed: April 12, 2017
    Publication date: August 3, 2017
    Inventors: Michael E. McCune, Jason Husband, Frederick M. Schwarz, Daniel Bernard Kupratis, Gabriel L. Suciu, William K. Ackermann
  • Geared Architecture for High Speed and Small Volume Fan Drive Turbine
    Publication number: 20170218849
    Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.
    Type: Application
    Filed: April 11, 2017
    Publication date: August 3, 2017
    Inventors: Michael E. McCune, Jason Husband, Frederick M. Schwarz, Daniel Bernard Kupratis, Gabriel L. Suciu, William K. Ackermann
  • Geared Architecture for High Speed and Small Volume Fan Drive Turbine
    Publication number: 20170218789
    Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.
    Type: Application
    Filed: April 12, 2017
    Publication date: August 3, 2017
    Inventors: Michael E. McCune, Jason Husband, Frederick M. Schwarz, Daniel Bernard Kupratis, Gabriel L. Suciu, William K. Ackermann
  • MULTI-SOURCE TURBINE COOLING AIR
    Publication number: 20170167386
    Abstract: A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.
    Type: Application
    Filed: December 10, 2015
    Publication date: June 15, 2017
    Inventors: Brian D. Merry, Gabriel L. Suciu, William K. Ackermann
  • COMPRESSOR CORE INNER DIAMETER COOLING
    Publication number: 20170167384
    Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
    Type: Application
    Filed: December 14, 2015
    Publication date: June 15, 2017
    Inventors: Gabriel L. Suciu, Brian D. Merry, Jesse M. Chandler, William K. Ackermann, Matthew R. Feulner, Om P. Sharma
  • Geared Architecture for High Speed and Small Volume Fan Drive Turbine
    Publication number: 20170159572
    Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.
    Type: Application
    Filed: February 20, 2017
    Publication date: June 8, 2017
    Inventors: Michael E. McCune, Jason Husband, Frederick M. Schwarz, Daniel Bernard Kupratis, Gabriel L. Suciu, William K. Ackermann
  • GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES
    Publication number: 20170114724
    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: January 6, 2017
    Publication date: April 27, 2017
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis, Brian D. Merry, Gabriel L. Suciu, William K. Ackermann
  • Geared architecture for high speed and small volume fan drive turbine
    Patent number: 9631558
    Abstract: A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.
    Type: Grant
    Filed: June 3, 2013
    Date of Patent: April 25, 2017
    Assignee: United Technologies Corporation
    Inventors: Michael E. McCune, Jason Husband, Frederick M. Schwarz, Daniel Bernard Kupratis, Gabriel L. Suciu, William K. Ackermann
  • Gas turbine engine with high speed low pressure turbine section and bearing support features
    Patent number: 9611859
    Abstract: A gas turbine engine includes a very high speed fan drive 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 mounted by bearings positioned at an outer periphery of a shaft driven by the high pressure turbine.
    Type: Grant
    Filed: April 13, 2012
    Date of Patent: April 4, 2017
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu, William K. Ackermann, Daniel Bernard Kupratis
  • NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT
    Publication number: 20170051621
    Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.
    Type: Application
    Filed: August 19, 2015
    Publication date: February 23, 2017
    Inventors: William K. Ackermann, Clifton J. Crawley, JR., Frederick M. Schwarz
  • NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT
    Publication number: 20170051631
    Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a bladed rotor assembly, a stator vane assembly, a fixed stator structure and a seal assembly. The bladed rotor assembly includes a rotor disk structure. The stator vane assembly is disposed adjacent the bladed rotor assembly. The fixed stator structure is connected to and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.
    Type: Application
    Filed: August 19, 2015
    Publication date: February 23, 2017
    Inventors: William K. Ackermann, Clifton J. Crawley, JR., Frederick M. Schwarz
  • SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT
    Publication number: 20170051751
    Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a rotor disk structure, a stator structure and a seal assembly. The rotor disk structure includes a rotor disk and a seal land circumscribing the rotor disk. The stator structure circumscribes the seal land. The seal assembly is configured for sealing a gap between the stator structure and the seal land, where the seal assembly includes a non-contact seal.
    Type: Application
    Filed: August 19, 2015
    Publication date: February 23, 2017
    Inventors: William K. Ackermann, Clifton J. Crawley, JR., Frederick M. Schwarz
  • AIR MIXING SYSTEMS HAVING MIXING CHAMBERS FOR GAS TURBINE ENGINES
    Publication number: 20170037782
    Abstract: Air mixing systems for gas turbine engines include a heat exchanger, a first extraction conduit fluidly coupled to an inlet of the heat exchanger, a second extraction conduit fluidly coupled to an outlet of the heat exchanger, an injection conduit fluidly coupled to the second extraction conduit, an onboard injector supply chamber fluidly coupled to the injection conduit, and an onboard injector fluidly coupled to the onboard injector supply chamber.
    Type: Application
    Filed: October 24, 2016
    Publication date: February 9, 2017
    Inventors: Frederick M. Schwarz, James D. Hill, William K. Ackermann
  • NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT WITH LINKAGE BETWEEN ADJACENT ROTORS
    Publication number: 20170009596
    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: Application
    Filed: July 8, 2015
    Publication date: January 12, 2017
    Inventors: Frederick M. Schwarz, William K. Ackermann
  • Gas turbine engine with high speed low pressure turbine section and bearing support features
    Patent number: 9540948
    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: Grant
    Filed: July 26, 2012
    Date of Patent: January 10, 2017
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis, Brian D. Merry, Gabriel L. Suciu, William K. Ackermann
  • SEGMENTED NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT
    Publication number: 20160376904
    Abstract: An assembly is provided for rotational equipment. The assembly includes a circumferentially segmented stator and a rotor radially within the stator. The assembly also includes a seal assembly configured for substantially sealing a gap radially between the stator and the rotor. The seal assembly includes a carrier and a non-contact seal seated with the carrier. The carrier includes a plurality of discrete carrier segments circumferentially arranged around the non-contact seal.
    Type: Application
    Filed: June 29, 2015
    Publication date: December 29, 2016
    Inventors: Frederick M. Schwarz, William K. Ackermann
  • FITTING FOR MID-TURBINE FRAME OF GAS TURBINE ENGINE
    Publication number: 20160312660
    Abstract: A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and each slot has an area within a range of 0.52 and 0.59 square inches.
    Type: Application
    Filed: April 27, 2015
    Publication date: October 27, 2016
    Inventors: James P. Chasse, JR., Ryan K. Snyder, William K. Ackermann, Pellegrino J. Pisacreta, Judith F. Brooks, Stephanie Ernst
  • GAS TURBINE ENGINE HAVING SECTION WITH THERMALLY ISOLATED AREA
    Publication number: 20160230597
    Abstract: A section of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a thermally isolated area, and a first rotor disk and a second rotor disk. Each of the first and second rotor disks are provided within the thermally isolated area.
    Type: Application
    Filed: February 9, 2015
    Publication date: August 11, 2016
    Inventors: Gabriel L. Suciu, William K. Ackermann, James D. Hill, Brian D. Merry
  • OVERCOOLED AIR COOLING SYSTEM WITH ANNULAR MIXING PASSAGE
    Publication number: 20160208703
    Abstract: A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.
    Type: Application
    Filed: January 20, 2015
    Publication date: July 21, 2016
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: James D. Hill, William K. Ackermann