Turbine Engine Patents (Class 73/116.03)
  • Patent number: 10364698
    Abstract: A system and method of non-intrusive thrust measurement of a gas turbine engine. The system comprises a transmitter disposed at a boundary of fluid flow and at least one receiver adapted to receive transmissions from the transmitter. A processor is coupled to the receivers to determine a parameter from a characteristic of the transmission at the receiver suite and adapted to determine a thrust parameter from the parameter. A method for non-intrusively measuring engine thrust includes transmitting a wave across the exhaust plume, receiving the transmitted wave and determining a measurement parameter of the exhaust plume based on a characteristic of the received wave, and comparing the measurement parameter to a reference parameter and determining the thrust based on the comparison.
    Type: Grant
    Filed: June 8, 2017
    Date of Patent: July 30, 2019
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC.
    Inventor: C. Edward Hodge
  • Patent number: 10107203
    Abstract: Systems and methods for controlling a fluid based system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states, the dynamic states input to an open loop model based on the model operating mode, wherein the open loop model generates current state derivatives, solver state errors, synthesized parameters as a function of the dynamic states and a model input vector. A constraint on the state derivatives and solver state errors is based on a series, of utilities that are based on mathematical abstractions of physical laws that govern behavior of the component. The model processor may include an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: October 23, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Boris Karpman, Richard P. Meisner, Matthew Donald, Thomas E. Case
  • Patent number: 9932985
    Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.
    Type: Grant
    Filed: February 3, 2015
    Date of Patent: April 3, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Nick Nolcheff
  • Patent number: 9879612
    Abstract: Commanding GTs to base load level based upon measured ambient condition for each GT; commanding each GT to adjust a power output to match scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and an emissions scale factor, wherein the nominal emissions value at the ambient condition and the emissions scale factor are stored in a pre-existing emissions model for the GT.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: January 30, 2018
    Assignee: General Electric Company
    Inventors: Lewis Berkley Davis, Jr., Scott Arthur Day, Timothy Andrew Healy, Rebecca Kathryn Jaiven, Harold Lamar Jordan, Jr., Rex Allen Morgan
  • Patent number: 9882454
    Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring an actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: January 30, 2018
    Assignee: General Electric Company
    Inventors: Lewis Berkley Davis, Jr., Scott Arthur Day, Harold Lamar Jordan, Jr., Rex Allen Morgan
  • Patent number: 9856796
    Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.
    Type: Grant
    Filed: December 7, 2015
    Date of Patent: January 2, 2018
    Assignee: General Electric Company
    Inventors: Lewis Berkley Davis, Jr., Scott Arthur Day, Harold Lamar Jordan, Jr., Rex Allen Morgan
  • Patent number: 9856797
    Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: modelling each GT in the set of GTs at a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring an actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: January 2, 2018
    Assignee: General Electric Company
    Inventors: Rex Allen Morgan, Lewis Berkley Davis, Jr., Scott Arthur Day, Harold Lamar Jordan, Jr.
  • Patent number: 8884628
    Abstract: Systems, methods and apparatus for monitoring rub detection in a machine are provided. An electrical signal may be provided for transmission to and into a component of the machine. A capacitance associated with the electrical signal in the component may be monitored. Based at least in part upon a determined change in the monitored capacitance, a potential rub condition for the component of the machine.
    Type: Grant
    Filed: January 5, 2012
    Date of Patent: November 11, 2014
    Assignee: General Electric Company
    Inventor: Wesley Donald Franklin
  • Patent number: 8471702
    Abstract: A method for monitoring the health of a compressor of a gas turbine is disclosed. The method includes receiving a plurality of turbine data points, wherein the plurality of turbine data points may include one or more operating parameters, at least one of a computer discharge temperature (CTD), and one or more performance parameters. The plurality of turbine data points may be categorized based on the one or more operating parameters. A statistical variability measure of at least one of the CTD and the one or more performance parameters may be computed for each of the plurality of bands. An alarm indicator may be computed based on the at least one statistical variability measure. The method may also include combining two or more of the operating parameters, the CTD and the performance parameters using sensor fusion techniques. The alarm indicator may be computed based on the combined parameters.
    Type: Grant
    Filed: December 22, 2010
    Date of Patent: June 25, 2013
    Assignee: General Electric Company
    Inventors: Ravi Yoganatha Babu, Vinay Bhaskar Jammu, Achalesh Kumar Pandey, Sudhanshu Rai
  • Publication number: 20130068005
    Abstract: A test bench for a reaction engine including a nozzle having a divergent. The bench includes a mechanism for holding the divergent in position, capable of holding the divergent so that its axis is vertical, and capable of interacting with a downstream portion of the divergent located in the downstream half thereof to limit distortion and/or displacement of this downstream portion. The test bench enables the divergent to remain undamaged even if lateral forces are applied to it during testing.
    Type: Application
    Filed: February 16, 2011
    Publication date: March 21, 2013
    Applicant: SNECMA
    Inventors: Noel David, Michel Fiolek, Jacques Lelong, Nicolas Ravier, Romain Stephant
  • Patent number: 8375722
    Abstract: An apparatus and method for inducing waves within a container arranged to permit a through-flow of fluid flowing generally from an inlet of the container to an exit of the container, wherein the container has wave inducing means located at the exit of the container, the wave inducing means being operable to vary the area of the exit thereby inducing waves within the container. The apparatus may form part of a combustor test rig.
    Type: Grant
    Filed: July 3, 2007
    Date of Patent: February 19, 2013
    Assignee: Rolls-Royce plc
    Inventors: Nickolaos Pilatis, Arthur L Rowe
  • Patent number: 8371178
    Abstract: A turbopump for a rocket engine includes a rotor shaft with a turbine connected to drive the rotor and a centrifugal impeller connected to be driven by the rotor. An electromagnetic powered motor is formed as part of the turbopump and is powered to drive the rotor at a low speed in order to test for an amount of torque required to drive the rotor at the low speed. A load cell is connected to the motor that rotates the rotor shaft. From the use of a load cell the amount of torque required to rotate the rotor can be determined and compared to a known value in order to determine if the turbopump is damaged and requires repairs.
    Type: Grant
    Filed: June 30, 2011
    Date of Patent: February 12, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Andrew P Wall
  • Patent number: 8327698
    Abstract: The fundamental idea of the invention consists of the construction of the test device from a stationary inner basic structure (1, 7 to 11) that juts out from the wall of the test bench and houses the drive shaft (13) for the fan to be tested, from mobile, interchangeable external housing modules (18 to 24) which can be aligned in relation to one another by means of connected optical elements (32, 33), from interchangeable fittings (41 to 44, 48) for conducting air and noise reduction, in addition to interchangeable measuring devices (38 to 40) that are connected to a modular telemetry unit for determining performance data and aerodynamic and acoustic conditions required by the fan and the fittings.
    Type: Grant
    Filed: July 13, 2009
    Date of Patent: December 11, 2012
    Assignee: AneCom Aero Test GmbH
    Inventors: Stefan Sand, Edmund Ahlers, Carsten Heydorn, Carsten Daum, André Steinborn, Ian Hobson, Axel Riepe
  • Publication number: 20120192631
    Abstract: Apparatus and methods for testing a turbomachine, with the apparatus including a loading device housing, a disk, and a non-contacting seal. The loading device housing has an inner surface and a fluid inlet configured to receive a pressurized gas. The disk is located outside of a turbomachine housing in which the turbomachine is disposed and is coupled to a shaft of the turbomachine, proximal an axial end of the shaft. The disk is received in the loading device housing and is axially moveable in the loading device housing while the shaft is rotating. The non-contacting seal is disposed between the inner surface and the disk.
    Type: Application
    Filed: May 13, 2011
    Publication date: August 2, 2012
    Applicant: DRESSER-RAND COMPANY
    Inventors: Joseph A. Tecza, Scott M. Hanaka, Bruce E. Fuller
  • Patent number: 8115494
    Abstract: Systems, methods and apparatus for monitoring rub detection in a machine are provided. An alternating current voltage signal may be transmitted or communicated to at least one component of the machine. The transmitted signal may be monitored in the at least one component and at least one characteristic associated with the monitored signal may be compared to an expected value for the at least one characteristic. Based at least in part on the comparison, a rub condition or potential rub condition may be identified between the at least one component and another component of the machine.
    Type: Grant
    Filed: April 3, 2009
    Date of Patent: February 14, 2012
    Assignee: General Electric Company
    Inventor: Wesley Donald Franklin
  • Patent number: 8082778
    Abstract: The present invention relates to a turbofan propulsion simulator means, in particular for a turbofan of an aircraft or spacecraft, wherein the turbofan propulsion simulator means comprises a modular configuration, wherein the turbofan propulsion simulator means comprises a module, wherein the module is a turbine means to drive the turbofan of the turbofan propulsion simulator means, wherein the turbine means can be coupled with at least two fan means, characterized in that, the at least two fan means to be connected with the turbofan propulsion simulator means comprises almost or essentially the same mass and/or almost or essentially the same barycentre.
    Type: Grant
    Filed: October 21, 2009
    Date of Patent: December 27, 2011
    Assignee: Airbus Operations GmbH
    Inventors: Uwe Riekers, Jens-Rasmus Ohst, Karl Heinz Kleppe, Michael Huhnd
  • Publication number: 20110219862
    Abstract: The fundamental idea of the invention consists of the construction of the test device from a stationary inner basic structure (1, 7 to 11) that juts out from the wall of the test bench and houses the drive shaft (13) for the fan to be tested, from mobile, interchangeable external housing modules (18 to 24) which can be aligned in relation to one another by means of connected optical elements (32, 33), from interchangeable fittings (41 to 44, 48) for conducting air and noise reduction, in addition to interchangeable measuring devices (38 to 40) that are connected to a modular telemetry unit for determining performance data and aerodynamic and acoustic conditions required by the fan and the fittings.
    Type: Application
    Filed: July 13, 2009
    Publication date: September 15, 2011
    Applicant: ANECOM AEROTEST GMBH
    Inventors: Stefan Sand, Edmund Ahlers, Carsten Heydorn, Carsten Daum, André Steinborn, Ian Hobson, Axel Riepe
  • Publication number: 20100199755
    Abstract: A turbofan test cell pre-dressing unit that enables the installation of the engine in a test cell in minimal time is provided.
    Type: Application
    Filed: April 28, 2010
    Publication date: August 12, 2010
    Inventor: Daniel Mainville
  • Patent number: 7762153
    Abstract: A method for determining the radial deformation of a blade in a turbine that includes: 1) taking an initial measurement of the blade with one or more proximity sensors disposed around the circumference of a stage of blades; 2) after the initial measurement, taking a second measurement of the blade with the one or more proximity sensors; 3) making a determination of the radial deformation of the blade by comparing the initial measurement to the second measurement. The initial measurement and the second measurement may be taken while the turbine is operating.
    Type: Grant
    Filed: May 31, 2007
    Date of Patent: July 27, 2010
    Assignee: General Electric Company
    Inventors: Scott Hoyte, Eric Gebhardt, Erin Bauknight, Samuel Draper, John Grant
  • Patent number: 7735363
    Abstract: A turbofan text cell pre-dressing unit that enables the installation of the engine in a text cell in minimal time is provided.
    Type: Grant
    Filed: June 20, 2007
    Date of Patent: June 15, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Daniel Mainville
  • Patent number: 7721529
    Abstract: An exhaust system for a combustion source is disclosed. The exhaust system may have a passageway connected to receive an exhaust flow from the combustion source, and a sensor disposed within the passageway. The sensor may generate a signal indicative of the concentration of a constituent in the exhaust flow. The exhaust system may also have a controller in communication with the sensor to receive the signal. The controller may be configured to selectively communicate a flow of calibration gas with the sensor during operation of the combustion source, and compare the signal received during the selective communication with a reference value. The controller may be further configured to adjust the sensor output in response to the comparison.
    Type: Grant
    Filed: November 30, 2006
    Date of Patent: May 25, 2010
    Assignee: Caterpillar Inc.
    Inventors: Mary Louise Kesse, Paul Adam Gamble, James Joshua Driscoll, Michael Paul Withrow
  • Publication number: 20090320578
    Abstract: A test apparatus can include a jet engine and a first frame configured to support the jet engine. In one example, the test apparatus can include means for flexibly coupling the jet engine to the first frame to allow movement between the jet engine and the first frame during a test procedure. In another example, a test apparatus is provided that is configured to support a jet engine. The test apparatus can include a frame, a flex member, a first attachment element and a second attachment element. In yet another example, a test apparatus can be provided with a frame, a flex member and a limiting element.
    Type: Application
    Filed: March 7, 2007
    Publication date: December 31, 2009
    Inventors: Arnold A. Peltzer, David J. Sowl, Kelley D. Kimball
  • Patent number: 7578178
    Abstract: A method of inspecting an internal feature of a gas turbine component includes removing a portion of the turbine component to expose the internal feature, treating the surfaces of the internal feature to provide the surfaces with a substantially uniform coloration, generating an electronic model of the internal feature, analyzing the electronic model generated with reference to a nominal electronic model, and providing an output based on the analysis of the electronic model generated.
    Type: Grant
    Filed: September 28, 2007
    Date of Patent: August 25, 2009
    Assignee: United Technologies Corporation
    Inventors: Jesse R. Boyer, Benjamin W. Meissner, Stephen D. Doll, Randall W. Joyner
  • Patent number: 7571057
    Abstract: A degradation monitoring system including: a machine; a sensor affixed to the machine, the sensors measuring a operational parameters of the machine; a set of filters receptive of information about the machine from the sensors and the filters responsively generate status signals; and comparators for comparing the status signals to stored signals, wherein the comparators indicate at least one of a presence of degradation of the machine, or a cause of degradation of the machine.
    Type: Grant
    Filed: September 16, 2005
    Date of Patent: August 4, 2009
    Assignee: General Electric Company
    Inventors: Fernando Javier D'Amato, Vivek Venugopal Badami, Jitendra Kumar
  • Publication number: 20090173148
    Abstract: The invention relates to a test bench for testing wind turbine equipment. The test bench comprises one or more load applying means directly or indirectly applying load to the equipment during said test and wherein the test bench comprises angle adjustment means for adjusting a test angle (A) of the equipment in relation to a horizontal plane. The invention further relates to methods for testing wind turbine equipment.
    Type: Application
    Filed: January 2, 2009
    Publication date: July 9, 2009
    Inventor: Jan Bisgaard Jensen
  • Publication number: 20090100918
    Abstract: Systems and methods for testing gas turbine engines are provided. In this regard, a representative system for testing a gas turbine engine having an inlet includes an inflatable seal having an interior chamber operative to receive pressurized gas such that the seal inflates to engage circumferentially about the exterior of an inlet of a gas turbine engine.
    Type: Application
    Filed: September 26, 2007
    Publication date: April 23, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventor: Miguel A. Cires
  • Publication number: 20080314134
    Abstract: A turbofan text cell pre-dressing unit that enables the installation of the engine in a text cell in minimal time is provided.
    Type: Application
    Filed: June 20, 2007
    Publication date: December 25, 2008
    Inventor: Daniel MAINVILLE