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US20120072091 TEMPERATURE ESTIMATION APPARATUS FOR AEROPLANE GAS TURBINE ENGINE  
In a temperature estimation apparatus for an aeroplane gas turbine engine, there are provided with a calculator that calculates a low-pressure turbine outlet temperature change (dEGT) based on...
US20100332103 NOX Compliant Peak for Gas Turbine  
A gas turbine comprises a plurality of target exhaust temperature determination modules, the plurality of target exhaust temperature modules comprising a nitrogen oxide (NOx) compliance module...
US20110160979 METHOD OF ESTIMATING THE MAXIMUM POWER GENERATION CAPACITY AND FOR CONTROLLING A SPECIFIED POWER RESERVE OF A SINGLE CYCLE OR COMBINED CYCLE GAS TURBINE POWER PLANT, AND A POWER GENERATING SYSTEM FOR USE WITH SAID METHOD  
An estimation unit can estimate, on a real-time basis, a maximum power generation capacity of a single cycle or combined cycle gas turbine power plant. For example, the actual power output and the...
US20130218437 GAS TURBINE SEQUENCING METHOD AND SYSTEM  
A method to develop a software based sequencer for a turbine including: selecting a general purpose sequencer software module having standardized software for sequencing turbines through defined...
US20130238215 MONITORING OF A FILTER OF THE FUEL-SUPPLY SYSTEM OF AN AIRCRAFT ENGINE  
A monitoring method for monitoring a filter of a feed circuit for feeding an aircraft engine with fuel, the method including: detecting clogging of the filter; issuing an indication message;...
US20130158831 DETECTION OF THE INGRESS OF WATER OR HAIL INTO A TURBINE ENGINE  
A detection method for detecting ingestion of water or hail in a gas turbine engine, the engine including at least a compressor, a combustion chamber, and a turbine, the method including:...
US20130054108 SYSTEM AND METHOD FOR PREDICTING TURBINE RUB  
A system for predicting turbine rub includes a monitoring system configured to form operational values for a turbine based on information received from the turbine and a correlation engine...
US20110160980 ESTIMATING HEALTH PARAMETERS OR SYMPTOMS OF A DEGRADING SYSTEM  
The present invention is concerned with the estimation of health parameters p(k) representing symptoms of a slowly degrading system, in particular industrial gas turbines. According to the...
US20130311060 ENGINE WASH OPTIMISATION  
The present invention provides a method of optimising engine wash event scheduling. An underlying deterioration gradient and a total deterioration gradient are determined. A number of engine wash...
US20140257666 Online Enhancement for Improved Gas Turbine Performance  
A system is provided that includes a memory storing a turbomachinery degradation model configured to model degradation of a turbomachinery over time. The system also includes a controller...
US20120277968 MOISTURE MONITORING SYSTEM FOR GAS TURBINE ENGINES  
A moisture monitoring system includes a control in communication with a sensor system to determine moisture data from a moisture level in a composite material structure.
US20140005909 REAL TIME LINEARIZATION OF A COMPONENT-LEVEL GAS TURBINE ENGINE MODEL FOR MODEL-BASED CONTROL  
A method for model-based control of a gas turbine engine is disclosed. An operating point of the gas turbine engine is generated from measured parameters using a component-level model. The...
US20100307158 SYSTEMS RELATING TO TURBINE ENGINE CONTROL AND OPERATION  
A combustion turbine engine that includes: a compressor; a combustor that receives fuel from a fuel line; a turbine; a heat exchange portion comprising a portion of the fuel line in heat transfer...
US20130204468 METHOD AND A DEVICE FOR PERFORMING A HEALTH CHECK OF A TURBINE ENGINE OF AN AIRCRAFT HAVING AT LEAST ONE SUCH ENGINE  
A method of performing a health check of at least one turbine engine (3). During a development step (STP0), the installation losses (1) are quantified for a plurality of test values for a reduced...
US20140058644 METHOD, SYSTEM, AND APPARATUS FOR REDUCING A TURBINE CLEARANCE  
A method for reducing a turbine clearance between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. Said method includes determining, with a flight...
US20150000300 GAS TURBINE HAVING FUEL MONITORING  
The invention relates to a method for detecting a fuel leakage in the fuel distribution system between a fuel control valve and at least one burner of a gas turbine during the operation of the gas...
US20130253734 SPEED CONTROL FOR A FIXED PTICH RAM AIR TURBINE  
A system of speed control for a ram air turbine of an aircraft includes a power electronics controller, at least one routing device in communication with the power electronics controller, at least...
US20110213537 Electronic Shaft Shear Detection Conditioning Circuit  
An electrical control system for distinguishing between an electrical fault and a shaft shear condition in a gas turbine engine, the control system including, in one aspect, a detection circuit...
US20120053811 METHOD AND A DEVICE FOR OPTIMIZING THE UTILIZATION OF AN ENGINE  
A method of optimizing the use of an aircraft power plant having at least one engine (1, 1′) operating within a performance envelope covering at least a first rating and a second rating, said...
US20140257667 METHOD OF SYNCHRONISING THE ENGINES OF AN AIRCRAFT  
A method of synchronizing engines of an airplane in accordance with at least one activation logic (10, 10′) defining a deactivated state (20), a primed state (22), and at least one activated state...
US20090069998 Event-driven starter controller  
An event-driven starter controller regulates the speed of a gas turbine engine based on detected events. The event-driven starter controller is used to supply motive force to the gas turbine...
US20120010800 AIRCRAFT ENGINE MANAGEMENT FOR FUEL CONSERVATION METHOD  
A method includes controlling an aircraft during descent, and controlling the engine pressure ratio of a jet engine so that the engine has a substantially equal pressure at the exhaust, and at the...
US20120109486 METHOD AND A DEVICE FOR MONITORING A REDUNDANT MEASUREMENT SYSTEM  
The invention relates to monitoring a redundant measurement system of an aeroengine by means of an electronic unit. The monitoring comprises a step of obtaining first measurements of a physical...
US20110118950 METHOD FOR ESTIMATION OF AT LEAST ONE ENGINE PARAMETER  
A system comprising determination of tuning parameters enabling optimal estimation of unmeasured engine outputs, e.g., thrust. The level of degradation of engine performance is generally described...
US20100318274 Combustor Flashback/Flame Holding Detection Via Temperature Sensing  
A combustor includes a combustor housing defining a combustion chamber having a plurality of combustion zones. A plurality of temperature detectors are disposed in communication with the...
US20100005912 METHOD AND TEST FIXTURE FOR EVALUATING A LUBRICATION CONTAINMENT SYSTEM  
A method for evaluating a lubrication containment system is disclosed herein. In one lubrication containment system applicable to the inventive method, a seal runner can be fixed to the rotatable...
US20100262350 CORRECTED MEGAWATT BACKUP CURVE METHODOLOGY  
The subject application involves a method of controlling operation of a gas turbine. The method includes determining a first temperature associated with a portion of the gas turbine during...
US20140244132 SYSTEM AND METHOD FOR 0N-WING ENGINE TRIM VERIFICATION  
Devices and methods relating to gas turbine engines and engine temperature trim verification are disclosed. An exemplary method comprises acquiring signals representing a plurality of engine...
US20110270502 EMPLOYING FUEL PROPERTIES TO AUTO-TUNE A GAS TURBINE ENGINE  
A tuning process is provided for monitoring fuel properties of a fuel being consumed by a gas turbine (GT) engine, and for dynamically tuning the GT engine as a function of changes to the...
US20090055070 SYSTEM AND METHOD FOR PREDICTION OF GAS TURBINE TRIPS DUE TO THERMOCOUPLE FAILURES  
Systems and methods for prediction of gas turbine trips due to component failures such as thermocouple failures. Exemplary embodiments include prediction of gas turbine trips due to component...
US20090164056 Method For Controlling The Consumption And For Detecting Leaks In The Lubrication System Of A Turbine Engine  
The present invention relates to a method for calculating the oil consumption and autonomy associated with the lubrication system of an airplane engine during flights, preferably a turbine engine,...
US20110270503 SELECTING AND APPLYING TO FUEL-FLOW SPLITS BIAS VALUES TO CORRECT FOR ELEVATED INLET AIR HUMIDITY  
Methods for controlling a gas turbine engine are provided, where a compressor inlet temperature, ambient temperature, and relative humidity are measured. Utilizing these measurements, it is first...
US20130204506 ENGINE SYSTEMS WITH EFFICIENT START CONTROL LOGIC  
An engine system for starting a gas turbine engine is provided. The system includes a starter generator coupled to the gas turbine engine and configured to provide torque to the gas turbine engine...
US20100168980 OPERATING A TURBINE AT BASELOAD ON COLD FUEL WITH HOT FUEL COMBUSTION HARDWARE  
A method and algorithm are provided to operate a gas turbine at baseload in an emission compliant capable mode to avoid combustion dynamics while operating with cold fuel and hot fuel combustion...
US20110004390 GAS TURBINE CONTROL METHOD AND DEVICE  
Provided is a gas turbine control method and control device whereby a design performance and an operating state based on ideal fuel flow rate and air flow rate simulated at the time of designing...
US20100138132 ENGINE HEALTH MONITORING  
A method of monitoring the health of a gas turbine engine of at least a pair of engines of an aircraft for example. The method comprising the steps of: a) obtaining steady state readings from...
US20140297155 AIRCRAFT POWER OUTTAKE MANAGEMENT  
A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the...
US20140121934 SYSTEM FOR DETECTING SHAFT SHEAR EVENT  
Systems and methods for detecting a shaft shear event in a turbine engine. An accelerometer coupled to the engine detects an axial acceleration indicative of a shaft shear event in the engine. A...
US20130073171 METHOD AND DEVICE FOR DETECTION OF CONTAMINATION BY FUEL OF THE OIL CIRCUIT OF A TURBINE  
A method for detection of contamination, by another fluid, of the oil circuit of a turbomachine fitted on an aircraft, the oil circuit including a tank provided with a device for measuring its oil...
US20140012481 AIRCRAFT ENGINE CONTROL DURING ICING OF TEMPERATURE PROBE  
Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals...
US20120029786 AIRCRAFT ENGINE CONTROL DURING ICING OF TEMPERATURE PROBE  
Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals...
US20090326781 TURBINE ENGINE TRAINING MANUAL MODE FUEL FLOW CONTROL SYSTEM AND METHOD  
A method of controlling a gas turbine engine in a vehicle having an automatic system configured to control fuel flow includes determining whether a vehicle operator is requesting to manually...
US20130211691 SYSTEM FOR REAL TIME SIMULATION OF THE ENVIRONMENT OF AN AEROENGINE  
A system for real time simulation of the environment of an aeroengine includes a digital computer having its inputs switched by a selection module included in the computer either to a respective...
US20090169367 Instability Mitigation System Using Stator Plasma Actuators  
An instability mitigation system is disclosed, comprising a stator stage located axially proximate to a rotor, the stator stage having a row of a plurality of stator vanes arranged around a...
US20140121935 Model Based Control Tuning Process for Gas Turbines  
Systems and methods for model based control tuning for gas turbine systems. In one embodiment, a nonlinear optimization process with multiple nonlinear constraints can create a set of control...
US20100036579 LOW MINIMUM IMPULSE BIT PROPELLANT GAS THRUSTER  
A gas thruster is configured to supply thrust over a relatively wide range, from a relatively low value to a relatively high thrust value, and exhibits relatively fine minimum impulse bit (MIB)...
US20070135987 System and method for turbine engine igniter lifing  
An igniter lifing system and method is provided that facilitates improved igniter plug wear and remaining life prediction. The igniter lifing system and method uses operating conditions measured...
US20110040470 Starter Control Valve Failure Prediction Machine To Predict and Trend Starter Control Valve Failures In Gas Turbine Engines Using A Starter Control Valve Health Prognostic, Program Product and Related Methods  
Starter control valve failure prediction machines, systems, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a...
US20110191004 GAS TURBINE CONTROL METHOD AND DEVICE  
To restrain combustion vibration more precisely by alleviating the relationship between the composition or heat quantity of the fuel and the combustion vibration characteristic and by grasping the...
US20090234554 GAS TURBINE ENGINE FIXED COLLECTIVE TAKEOFF COMPENSATION CONTROL SYSTEM AND METHOD  
A system and method of controlling a gas turbine engine controller in a rotorwing aircraft includes determining when a fixed collective takeoff (FCTO) of the rotorwing aircraft is being conducted....
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