Patents by Inventor Jorn A. Glahn

Jorn A. Glahn 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: 10107198
    Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: October 23, 2018
    Assignee: United Technologies Corporation
    Inventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney
  • Patent number: 10107131
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section, a shaft including a bearing system, a turbine section in communication with the shaft, a speed change mechanism coupling the fan section to the turbine section and a biasing device configured to apply a biasing force against the shaft.
    Type: Grant
    Filed: March 11, 2014
    Date of Patent: October 23, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Jorn A. Glahn
  • Patent number: 10087782
    Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.
    Type: Grant
    Filed: March 12, 2014
    Date of Patent: October 2, 2018
    Assignee: United Technologies Corporation
    Inventors: Cheng-Zhang Wang, Jorn A. Glahn, David F. Cloud, Peter M. Munsell, Clifton J. Crawley, Jr., Robert Newman, Michelle Diana Stearns
  • Publication number: 20180265223
    Abstract: A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (fmotoring), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. The memory records the current heat state at shutdown and a shutdown time of the gas turbine engine. The model for determining the time period is for motoring the gas turbine engine at a predetermined speed Ntarget that is less than a speed to start the gas turbine engine, where tmotoring is a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time. The controller modulates a starter valve to maintain the gas turbine engine within a predetermined speed range of NtargetMin to NtargetMax for homogenizing engine temperatures.
    Type: Application
    Filed: May 22, 2018
    Publication date: September 20, 2018
    Inventors: Matthew D. Teicholz, Jeffrey W. Sutliff, William H. Greene, JR., Kenneth J. White, Matthew R. Feulner, John P. Virtue, JR., Jorn A. Glahn, Philip D. Hoover, Victor M. Pinedo, Jason B. Solomonides
  • Patent number: 10047677
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. A buffer system includes a first circuit that supplies a first buffer supply air and a second circuit that supplies a second buffer supply air. The first circuit includes a first bleed air supply and a second bleed air supply. The second circuit includes a third bleed air supply and a fourth bleed air supply and at least one of the first circuit and the second circuit includes a variable area ejector.
    Type: Grant
    Filed: June 30, 2015
    Date of Patent: August 14, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jorn A. Glahn, Clifton J. Crawley, Jr., Philip S. Stripinis, William K. Ackermann
  • Patent number: 10040577
    Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: August 7, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew D. Teicholz, Jeffrey W. Sutliff, William H. Greene, Jr., Kenneth J. White, Matthew R. Feulner, John P. Virtue, Jr., Jorn A. Glahn, Philip D. Hoover, Victor M. Pinedo, Jason B. Solomonides
  • Publication number: 20180045115
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft and first and second bearing structures that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.
    Type: Application
    Filed: October 26, 2017
    Publication date: February 15, 2018
    Inventors: Jorn A. GLAHN, William K. ACKERMANN, Clifton J. CRAWLEY, Philip S. STRIPINIS
  • Publication number: 20170335770
    Abstract: According to an aspect, a method includes predicting, by a processor, a projected oil-wetted metal temperature in a lubrication system of a gas turbine engine at shutdown based on one or more thermal models prior to shutdown of the gas turbine engine. The processor determines a coking index based on the projected oil-wetted metal temperature and a coking limit threshold associated with one or more engine components. An oil coking mitigation action is triggered as a shutdown management event of the gas turbine engine based on the coking index.
    Type: Application
    Filed: May 20, 2016
    Publication date: November 23, 2017
    Inventors: Jorn A. Glahn, Denman H. James, Amy R. Grace
  • Patent number: 9816436
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft, a first bearing structure and a second bearing structure that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.
    Type: Grant
    Filed: May 21, 2014
    Date of Patent: November 14, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jorn A. Glahn, William K. Ackermann, Clifton J. Crawley, Philip S. Stripinis
  • Publication number: 20170233103
    Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed.
    Type: Application
    Filed: February 12, 2016
    Publication date: August 17, 2017
    Inventors: Matthew D. Teicholz, Jeffrey W. Sutliff, William H. Greene, JR., Kenneth J. White, Matthew R. Feulner, John P. Virtue, JR., Jorn A. Glahn, Philip D. Hoover, Victor M. Pinedo, Jason B. Solomonides
  • Publication number: 20170130732
    Abstract: A gas turbine engine compressor section has a hub carrying a last row of compressor blades. A compressor exit guide vane is downstream of the last row of compressor blades. A housing is radially inward of the compressor exit guide vane. A non-contact seal is positioned on one of the housing and the hub.
    Type: Application
    Filed: November 6, 2015
    Publication date: May 11, 2017
    Inventors: Frederick M. Schwarz, Jorn A. Glahn
  • Publication number: 20170107839
    Abstract: Aspects of the disclosure are directed to an engine of an aircraft comprising: a first seal located forward of a disk of a turbine section of the engine, a second seal located forward of the disk of the turbine section and radially inward of the first seal relative to an axial centerline of the engine, where the first and second seals are floating, non-contact seals.
    Type: Application
    Filed: October 19, 2015
    Publication date: April 20, 2017
    Inventors: Jorn A. Glahn, Frederick M. Schwarz
  • Patent number: 9470153
    Abstract: A compression pump for an engine is provided. The pump may include a first pump impeller operatively coupled to a main shaft of the engine, a first inlet configured to at least partially receive bypass airflow, and a first outlet configured to direct compressed air to a thermal management system. The first pump impeller may be rotatably fixed about a common axis of the compression pump. Additionally the compression pump may extend radially to one exterior side of the engine. Furthermore the compression pump can be coupled to the main shaft of the engine by an engine towershaft. A first intake manifold may be coupled to a first inlet of the compression pump and a first discharge manifold may be couple to a first outlet of the compression pump which may have one or more heat exchangers.
    Type: Grant
    Filed: October 5, 2011
    Date of Patent: October 18, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Jorn A. Glahn, Brian D. Merry, Christopher M. Dye
  • Patent number: 9394803
    Abstract: An engine comprises a fan configured to produce propulsive thrust from a fan discharge air stream. A bypass duct is located between a cowl and an engine core, the bypass duct is fluidly coupled to the fan. The bypass duct contains the air stream created by the fan. A pump system provides the air to an environmental control system. The pump system comprises an impeller having an inlet for receiving the air from the duct and an outlet for discharging the air to the environmental control system. An intake manifold is configured to receive the air from the bypass duct and to deliver the air to the inlet. A single discharge manifold is configured to deliver the air from the outlet to the environmental control system.
    Type: Grant
    Filed: March 14, 2012
    Date of Patent: July 19, 2016
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jorn A. Glahn, Brian D. Merry, Christopher M. Dye
  • Publication number: 20160053631
    Abstract: A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a first turbine section and a second turbine section. The first turbine section has a first exit area and rotates at a first speed. The second turbine section has a second exit area and rotates at a second speed. A first performance quantity is defined as the product of the first speed squared and the first exit area. A second performance quantity is defined as the product of the second speed squared and the second exit area.
    Type: Application
    Filed: November 5, 2015
    Publication date: February 25, 2016
    Inventors: Frederick M. Schwarz, Jorn A. Glahn
  • Publication number: 20160032775
    Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.
    Type: Application
    Filed: March 12, 2014
    Publication date: February 4, 2016
    Inventors: Cheng-Zhang Wang, Jorn A. Glahn, David F. Cloud, Peter M. Munsell, Clifton J. Crawley, JR., Robert Newman, Michelle Diana Stearns
  • Publication number: 20160024968
    Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.
    Type: Application
    Filed: March 14, 2014
    Publication date: January 28, 2016
    Inventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney
  • Publication number: 20150361887
    Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.
    Type: Application
    Filed: March 14, 2014
    Publication date: December 17, 2015
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney
  • Publication number: 20150300266
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. A buffer system includes a first circuit that supplies a first buffer supply air and a second circuit that supplies a second buffer supply air. The first circuit includes a first bleed air supply and a second bleed air supply. The second circuit includes a third bleed air supply and a fourth bleed air supply and at least one of the first circuit and the second circuit includes a variable area ejector.
    Type: Application
    Filed: June 30, 2015
    Publication date: October 22, 2015
    Inventors: Jorn A. GLAHN, Clifton J. CRAWLEY, JR., Philip S. STRIPINIS, William K. ACKERMANN
  • Patent number: 9163562
    Abstract: A gas turbine engine comprises a fan configured to produce propulsive thrust from a fan discharge air stream. A bypass duct is located between a cowl and an engine core, the bypass duct is fluidly coupled to the fan. An impeller pump has an intake manifold fluidly coupled to the bypass duct. The impeller pump has an outlet coupled to an outlet duct fluidly coupled to an environmental control system, wherein the impeller pump is configured to raise pressure of the fan discharge air stream and pump the fan discharge air into the environmental control system for cooling. An integrated drive pump is connected to the impeller pump for driving the impeller pump at a constant speed. The integrated drive pump is positioned on the engine core.
    Type: Grant
    Filed: March 14, 2012
    Date of Patent: October 20, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Jorn A. Glahn, Christopher M. Dye