Class / Patent application number | Description | Number of patent applications / Date published |
073112050 | Compressor | 18 |
20090107223 | METHOD AND APPARATUS FOR TURBINE ENGINE DYANMIC CHARACTERIZATION - A method and apparatus for conducting dynamic characterization of a gas turbine engine which involves generating exciting pressure pulses and measuring responses in the engine, and, in one aspect then analyzing the measured response for engine dynamic characteristics. | 04-30-2009 |
20120137759 | SURGE PRECURSOR PROTECTION SYSTEMS AND METHODS - The present application provides a method of monitoring a compressor. The method may include the steps of determining a blade passing frequency, determining a power indication for a number of frequencies above and below the blade passing frequency, determining a ratio between a maximum power indication and a minimum power indication for the frequencies for a number of predetermined time intervals, and analyzing the ratio for each predetermined time interval to predict a surge condition of the compressor. | 06-07-2012 |
20120160021 | SIMILITUDE TESTING OF COMPRESSOR PERFORMANCE - A method for similitude testing of a turbomachine, the method comprising selecting a test gas having a molecular weight between 40 g/gmol and 150 g/gmol, a global warming potential (GWP) of less than 700, and a gas specific heat ratio of between 1 and 1.5; operating the turbomachine using the selected test gas; identifying at least one parameter while operating the turbomachine; establishing at least one test parameter associated with the at least one parameter; and comparing the at least one test parameter with a corresponding at least one specified parameter to determine whether the turbomachine has passed the similitude test. | 06-28-2012 |
20130014571 | APPARATUS FOR INSPECTING TURBOMACHINE COMPONENTS IN-SITUAANM Quinones; DiegoAACI RexfordAAST NYAACO USAAGP Quinones; Diego Rexford NY USAANM Banowetz; Daniel LawrenceAACI GlenvilleAAST NYAACO USAAGP Banowetz; Daniel Lawrence Glenville NY USAANM Lewis; Gareth William DavidAACI LexingtonAAST MAAACO USAAGP Lewis; Gareth William David Lexington MA USAANM Moldenhauer; Thomas EarnestAACI Burnt HillsAAST NYAACO USAAGP Moldenhauer; Thomas Earnest Burnt Hills NY US - An apparatus is provided for inspecting a component of a turbomachine in-situ. The apparatus includes an end effector having a frame defining a stable platform with a curved surface of the component, a spring loaded suspension attached to the frame, and a probe connected to a wedge member, where the probe and wedge member are connected to the spring loaded suspension. The probe is configured to inspect the component by passing signals through the wedge. | 01-17-2013 |
20140007663 | Method for Functionally Testing Turbomachines, and Test Device Therefor - In the course of a method for the function testing of turbo-machines, preferably exhaust gas turbochargers ( | 01-09-2014 |
20140047911 | Systems and Methods for Continuous Pressure Change Monitoring in Turbine Compressors - Systems and methods for continuous pressure change monitoring in turbine compressors. In one embodiment, a system can be provided. The system can include a dynamic pressure sensing device mounted to the turbine compressor. The dynamic pressure sensing device may be configured to provide continuous dynamic pressure data, which may be associated with one or more pressure change events. The system may further include a memory configured to store the continuous dynamic pressure data, and a processor configured to correlate the one or more pressure change events with one or more component failures of the turbine compressor, and, based at least in part on the correlation, diagnose the one or more component failures. | 02-20-2014 |
20140083176 | TURBOMACHINE INCLUDING A PRESSURE SENSING SYSTEM - A turbomachine includes a fan having a housing and a plurality of vanes rotatable within the housing. Each of the plurality of vanes includes a pressure side and a suction side. A pressure sensing system includes at least one pressure sensor mounted to one of the pressure side and the suction side of one or more of the plurality of vanes, and a pressure sensor receiver mounted to the housing. The at least one pressure sensor is configured and disposed to communicate pressure data to the pressure sensor receiver. | 03-27-2014 |
20140130583 | INSPECTION ARRANGEMENT - An inspection arrangement including an inspection element and a positioning tool for positioning the inspection element, the inspection element being attachable to the positioning tool by an attachment arrangement, and having a fixing element to present the inspection element in use, the fixing element including a plurality of radially extending resilient elements. | 05-15-2014 |
20140174163 | Systems and Methods For Measuring Fouling in a Turbine System - Systems and methods for measuring fouling in a gas turbine compressor include a conductivity resistance sensor disposed in a compressor inlet mouth. The degree of compressor fouling is correlated to changes in resistance measured by the conductivity resistance sensor. Measurements of resistance changes are converted to an indicia of fouling and used to trigger cleaning of the compressor. | 06-26-2014 |
20150027212 | METHOD AND SYSTEM FOR REAL TIME GAS TURBINE PERFORMANCE ADVISORY - A system and method for monitoring and diagnosing anomalies in an output of a gas turbine, the method including storing a plurality rule sets specific to a performance of the gas turbine. The method further including receiving real-time and historical data inputs relating to parameters affecting the performance of the gas turbine, periodically determining current values of the parameters, comparing the initial values to respective ones of the current values, determining a degradation over time of the at least one of the performance of the compressor, the power output, the heat rate, and the fuel consumption based on the comparison, recommending to an operator of the gas turbine a set of corrective actions to correct the degradation. | 01-29-2015 |
20150143882 | TURBO ROTATIONAL FREQUENCY DETECTION DEVICE - Based on entry/exit pressures of compressor | 05-28-2015 |
20150369642 | SENSOR APPARATUS, CORRESPONDING TURBOCHARGER AND METHOD OF MEASURING A MASS FLOW RATE - A sensor apparatus comprising a housing having an inner perimeter which defines an area through which gas may flow, the housing being provided with a first chamber which extends around the area through which gas may flow, an entrance being distributed around the first chamber, and a second chamber which extends around the area through which gas may flow, an exit being distributed around the second chamber, the first chamber being arranged to be upstream of the second chamber in use, wherein the sensor apparatus further comprises one or more sensors arranged to measure a pressure difference between pressure in the first chamber and pressure in the second chamber. Corresponding turbocharger and method of measuring a mass flow rate are also provided. | 12-24-2015 |
20160069777 | Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir - A process for testing a combustor or a compressor of a gas turbine engine, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through an air turbine to drive a compressor to produce high pressure and temperature compressed air, and where the compressed air can be discharged into a combustor and burned with a fuel for testing of the combustor under simulated conditions of a real gas turbine engine. | 03-10-2016 |
20170234320 | REAL TIME ROTATION BREAKAWAY DETECTION | 08-17-2017 |
073112060 | Surge or stall | 4 |
20090019925 | Method and Device for Determining the Occurrence of Rotating Stall in a Compressor's Turbine Blade II - A method and device for determining the occurrence of rotating stall in the turbine blade of a compressor, in which the blade pass frequency of at least one compressor stage and the associated vibration energy are monitored, the normal blade pass frequency being constituted by the operating speed of rotation of the compressor multiplied by the number of turbine blades in the stage, and in which incipient rotating stall in a compressor stage is indicated when, at the normal blade pass frequency of the compressor stage, the vibration energy falls below a predetermined first value at the same time as, at a blade pass frequency above the normal blade pass frequency, the vibration energy rises above a predetermined second value. | 01-22-2009 |
20100011846 | STALL AND SURGE DETECTION SYSTEM AND METHOD - A method for monitoring a compressor comprising a rotor is presented. The method comprises obtaining a dynamic pressure signal of the rotor, obtaining a blade passing frequency of the rotor, using the blade passing frequency signal for filtering the dynamic pressure signal, buffering the filtered dynamic pressure signal over a moving window time period, and analyzing the buffered dynamic pressure signal to predict a stall condition of the compressor. | 01-21-2010 |
20130186191 | METHOD AND DEVICE FOR DETECTING A ROTATIONAL SEPARATION ADVERSELY AFFECTING A TURBINE ENGINE COMPRESSOR - A method and device detecting a rotating stall affecting a turbine engine compressor. The detection method includes: detecting an abnormal acceleration of the engine or an operating line of the compressor that is characteristic of a failure of the engine; storing a reference temperature measured at an outlet from a turbine of the engine at an instant of detection; comparing a determined temperature threshold with the difference between a current temperature at the outlet of the turbine as measured after detection and the reference temperature; and identifying that a rotating stall is present in event of the threshold being exceeded. | 07-25-2013 |
20160025596 | METHOD AND SYSTEMS FOR DETECTION COMPRESSOR SURGE - A system for remote detection of surge in a fleet of turbine engines includes an on-site monitoring device coupled to each turbine engine of the fleet of turbine engines. The on-site monitoring device is configured to continuously receive operating parameter measurements indicative of operational and thermodynamic conditions of the turbine engine. The operational condition includes a compressor exit condition of the turbine engine compressor. The on-site monitoring device is configured to compile and transmit a snapshot of the operating parameter measurements to a remote monitoring unit. The remote monitoring unit is positioned remote from each turbine engine of the fleet of turbine engines. The remote monitoring unit is configured to receive the snapshot of operating parameter measurements from the on-site monitoring device. The remote monitoring unit is further configured to detect surge in the turbine engine based on analysis of the snapshot of operating parameter measurements. | 01-28-2016 |