Abstract: Systems and methods for conditionally performing engine operational tests for a turbine engine are provided. A system comprising at least one processor can be configured to obtain sensor data associated with at least one sensor for a turbine engine. The sensor data identifies a current fuel flow associated with the turbine engine. The system can determine a predicted fuel flow of the turbine engine based at least in part on the current fuel flow and a fuel flow reduction associated with an engine operational test. The system can compare the predicted fuel flow to at least one threshold. The system can selectively initiate the engine operational test based on comparing the predicted fuel flow to the at least one threshold.

Abstract: Systems and methods for providing an automatic fuel polishing and on-demand fuel delivery for one or more gas turbine engine test cells are provided. The system can have a polishing loop that can continuously polish fuel. The polishing loop can have at least a fuel storage tank, a pump assembly, a filtration system, and a flow meter. The system can also have fuel delivery path coupled to the polishing loop at a three way junction. The three way junction can enable the continuous polishing loop when no test cells are operating. Upon initiation of one or more test cells, the delivery path can draw fuel from the polishing loop via the three way junction for use by the test cells. The flow meter can measure a corresponding drop in flow within the polishing loop and cause an increase in flow by the pump assembly.

Abstract: A circuit for metering fuel for a turbomachine, including a fuel metering element, a pump designed to pump a flow of fuel to the metering element, and a control valve designed to return, toward the pump, an excess flow of fuel delivered to the metering element as a function of a fuel pressure difference at the terminals of the metering element, the control valve is designed to modulate the excess flow returned toward the pump as a function of variations in the density of the fuel delivered to the metering element. A turbomachine can include such a circuit.

Abstract: A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.

Abstract: An apparatus externally detects the presence of a fault or malfunction in a gas turbine using the sound of air passing through vanes. The apparatus includes a sound sensor configured to sense a sound; a signal converter configured to convert the sensed sound into a digital signal; a data processor configured to perform a sound quality evaluation by analyzing a sound quality of the digital signal; and a display configured to display a result of the sound quality evaluation. The gas turbine includes a compressor housed in a compressor casing in which an inlet guide vane (IGV) assembly and a variable guide vane (VGV) assembly are installed. The sound sensor includes a plurality of microphones are installed outside the compressor casing at positions adjacent to at least one of a vane of the IGV assembly and a vane of the VGV assembly.

Abstract: A fuel system for an engine can include a fuel circuit and a primary fuel pump in fluid communication with the fuel circuit and configured to pump fuel to the engine as a function of engine speed. The primary fuel pump is configured to pump insufficient fuel flow to the engine during at least one engine speed or speed range. The system also includes a supplemental fuel pump in fluid communication with the fuel circuit configured to selectively pump fuel to the engine at least during the at least one engine speed or speed range to supplement fuel flow from the primary fuel pump to provide sufficient total fuel flow to the engine during all engine speeds.

Abstract: A gas turbine control device includes a detection value acquisition unit that acquires a detection value of at least one of a supply amount of fuel, pressure of compressed air, and electric power generated by a generator; a flue gas temperature acquisition unit that acquires a flue gas temperature detection value; a combustion gas temperature estimate value calculation unit that calculates a combustion gas temperature estimate value based on the detection value; a correction term acquisition unit that calculates a correction term based on a ratio between the combustion gas temperature estimate value and the flue gas temperature detection value; a corrected combustion gas temperature estimate value calculation unit that corrects the combustion gas temperature estimate value using the correction term to calculate a corrected combustion gas temperature estimate value; and a gas turbine controller that controls the gas turbine based on the corrected combustion gas temperature estimate value.

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.

Abstract: A vehicle includes an engine, a tank configured to provide a supply flow of natural gas, a valve controllable to provide a regulated flow of natural gas to the engine by modulating the supply flow of natural gas, a first conduit extending between the tank and the valve such that the supply flow of natural gas is received by the valve from the tank, and a second conduit extending between the valve and the engine such that the regulated flow of natural gas is provided from the valve to the engine. The regulated flow of natural gas is not diverted from the second conduit at any point along a length of the second conduit.

Abstract: The combustor of a gas turbine may include: a burner, including a plurality of nozzles, to eject fuel and air; and a duct assembly, coupled to one side of the burner, to combust the fuel and the air therein and transfer combustion gas to a turbine, where the burner may include a flow guide member to guide a flow of air to be drawn into the nozzles, and a plurality of holes may be formed in the flow guide member.

Abstract: A piece of equipment commonly used in many petrochemical and refinery processes is a pressure swing adsorption (PSA) unit. A PSA unit may be used to recover and purify hydrogen process streams, such as from hydrocracking and hydrotreating process streams. Aspects of the present disclosure are directed to monitoring PSA unit processes for potential and existing issues, providing alerts, and/or adjusting operating conditions to optimize PSA unit life. There are many process performance indicators that may be monitored including, but not limited to, flow rates, chemical analyzers, temperature, and/or pressure. In addition, valve operation may be monitored, including opening speed, closing speed, and performance. The system may adjust one or more operating characteristics to decrease the difference between the actual operating performance in the recent and the optimal operating performance.

Abstract: A combustion staging system is provided for fuel injectors of a multi-stage combustor of a gas turbine engine. The system has a splitting unit which receives a metered total fuel flow and controllably splits the metered total fuel flow into out-going pilot and mains fuel flows to perform pilot-only and pilot-and-mains staging control of the combustor. The splitting unit includes a metering valve and a spill valve, a first portion of the total metered fuel flow received by the splitting unit being an inflow to the metering valve and a second portion of the total metered fuel flow received by the splitting unit being an inflow to the spill valve. The metering valve is configured to controllably determine a fuel flow rate of a metered outflow formed from the first portion of the total metered fuel flow.

Abstract: Embodiments of a combined overspeed and fuel stream selector system are provided. In an embodiment, the assembly includes a conduit network, a Discharge Select Valve (DSV), and a shutoff valve. The DSV is fluidly coupled to a primary fuel inlet, a secondary fuel inlet, and a primary fuel outlet included in the conduit network. The shutoff valve is fluidly coupled between the primary fuel inlet and the primary fuel outlet. In a standard operation mode, the shutoff valve is maintained in an open position, while fuel received at the primary fuel inlet is directed through the shutoff valve, through the DSV, and to the primary fuel inlet. Conversely, in a backup operation mode, the shutoff valve is closed to block fuel flow from the primary fuel inlet to the primary fuel outlet, while the DSV directs fuel flow received at the secondary fuel inlet to the primary fuel outlet.

Abstract: A distribution method for a gas turbine engine distributes fuel based on a calculated ratio of air flow burnt to total air flow through all combustion zones in the gas turbine engine. This ratio is used to achieve a predetermined flame temperature in the gas turbine engine.

Abstract: A control method of a vehicle having an exhaust gas recirculation (EGR) system includes efficiently controlling a temperature of recirculated exhaust gas and, even when the temperature of recirculated exhaust gas excessively increases, damage to hardware, such as an intake manifold or parts of the exhaust gas recirculation system can be prevented. The control method includes: detecting the temperature of exhaust gas recirculated to an engine intake system by the EGR system; entering into a protection mode so as to control the temperature of the recirculated exhaust gas; determining a correction value such that the controller controls the temperature of the recirculated exhaust gas; and correcting an engine control value by using the determined correction value and controlling an engine according to the corrected engine control value.

Abstract: Method of determining at least one stability margin for a combustor (12), by obtaining modal characteristics of at least one spectral peak in the thermoacoustic dynamics, as well as determining the stability margin for the combustor (12) on the basis of the obtained modal characteristics, and an apparatus being adapted to carry, out said method.

Abstract: A regulator device for automatically regulating a power plant of a rotary wing aircraft having a turbine engine includes a computer system. The computer system, while implementation of an idling mode of operation of the turbine engine is requested and the aircraft is standing on ground, implements the idling mode of operation and operates the turbine engine in compliance with idling mode of operation as a function of operational and hierarchically ordered conditions either through a first mode of regulation by regulating a speed of rotation (Ng) of a gas generator of the turbine engine or through a second mode of regulation by regulating a speed of rotation (NTL) of a free turbine of the turbine engine.

Abstract: A fluid supply system (1) for turbine engine, includes a high pressure volumetric pump (4), a fluid metering device (6) and a control valve (8) configured to vary the flow rate of fluid in a bypass circuit (14) so as to regulate the pressure difference between an input and an output of the metering device (6). The control valve (8) includes an obturator, the variable position of which is measured by a sensor (20). An electronic regulation system (3) compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (14). The flow rate of the high pressure pump (4) is commanded so that the measured position of the obturator adapts to the position set-point.

Abstract: A plant or refinery may include equipment such as condensers, regenerators, distillation columns, rotating equipment, compressors, pumps, turbines, or the like. Different operating methods may impact deterioration in equipment condition, thereby prolonging equipment life, extending production operating time, or providing other benefits. Mechanical or digital sensors may be used for monitoring equipment to determine whether problems are developing. For example, sensors may be used in conjunction with one or more system components to perform invariant mapping, monitor system operating characteristics, and/or predict pressure, volume, surges, reactor loop fouling, gas quality, or the like. An operating condition (e.g., of one or more pieces of equipment in the plant or refinery) may be adjusted to prolong equipment life or avoid equipment failure.

Abstract: A fuel supply line system used for a gas turbine, including: fuel gas control valves used for controlling delivery to the gas turbine; a first line used for connecting the fuel gas source to the control valves; a second line used for connecting the control valves to the gas turbine; a monitoring device, configured to be used for determining the pressure inside the pipe at the outlet of the second line near said control valve; and a controller, configured to reduce the effective flow area of the pressure control valves or close the control valves when the determined pressure inside the pipe of the second line is greater than a predetermined pressure.

Abstract: A system for an engine defined about an axial centerline includes an inner case that includes a bushing, a duct case radially outward of the inner case with respect to the axial centerline, and a seal located on the duct case. The system further includes a borescope plug assembly that traverses the seal and the bushing in mounting to the inner case. The borescope plug assembly includes a spring, a housing sleeve, and a washer sleeve at least partially nested within the housing sleeve. The spring is isolated from the seal by the housing sleeve and the washer sleeve such that the spring is contact-free with respect to the seal.

Abstract: A plant or refinery may include equipment such as condensers, regenerators, distillation columns, rotating equipment, compressors, pumps, turbines, or the like. Different operating methods may impact deterioration in equipment condition, thereby prolonging equipment life, extending production operating time, or providing other benefits. Mechanical or digital sensors may be used for monitoring equipment to determine whether problems are developing. For example, sensors may be used in conjunction with one or more system components to perform invariant mapping, monitor system operating characteristics, and/or predict pressure, volume, surges, reactor loop fouling, gas quality, or the like. An operating condition (e.g., of one or more pieces of equipment in the plant or refinery) may be adjusted to prolong equipment life or avoid equipment failure.

Abstract: A multistage centrifugal compressor includes a casing, a rotor including a plurality of impellers, a diaphragm defining a gas flow path that includes a return flow path, and at least one liquid injection device configured to inject liquid into the gas flow path. The liquid injection device includes a liquid injection path, an internal path, a chamber, and a plurality of nozzles. The liquid injection path penetrates through the casing at a position corresponding to a return bend. The internal path receives a liquid supply pipe inserted from the liquid injection path through the return bend. The chamber is provided in the diaphragm along a circumferential direction and the liquid is introduced into the chamber through the internal path. The plurality of nozzles inject the liquid introduced into the chamber, to the gas flow path from different positions of the chamber in the circumferential direction.

Abstract: A method for operating a gas turbine installation with a measured compressor inlet temperature (Ti-actual) and a virtually constant turbine inlet temperature (TiTiso), wherein to provide safe operation of the gas turbine installation, an increase in a calculated exhaust gas temperature (ATK) is compensated by a reduced mass flow (m) of a flow medium flowing through a compressor of the gas turbine installation. An arrangement for operating the gas turbine installation includes a functional unit and a gas turbine installation with a compressor, a turbine, a control system for operating the method.

Abstract: A plant or refinery may include equipment such as condensers, regenerators, distillation columns, rotating equipment, compressors, pumps, turbines, or the like. Different operating methods may impact deterioration in equipment condition, thereby prolonging equipment life, extending production operating time, or providing other benefits. Mechanical or digital sensors may be used for monitoring equipment to determine whether problems are developing. For example, sensors may be used in conjunction with one or more system components to perform invariant mapping, monitor system operating characteristics, and/or predict pressure, volume, surges, reactor loop fouling, gas quality, or the like. An operating condition (e.g., of one or more pieces of equipment in the plant or refinery) may be adjusted to prolong equipment life or avoid equipment failure.

Abstract: A tangible, non-transitory computer readable medium includes computer instructions stored thereon, the computer instructions, when executed by a processor, cause the processor to retrieve model inputs indicative of mechanical systems data, economic data, contractual data, regulatory data, or any combination thereof, associated with at least one compression system. Furthermore, the instructions cause the processor to retrieve a model that derives an operation schedule for the at least one compression system based on the model inputs. Then the instructions cause the processor to derive an operation schedule for the at least one compression system based on the model inputs and the model, and apply the operation schedule to the at least one gas compression system.

Abstract: A system controller manages a gas turbine engine driving a pump directly or indirectly coupled to the engine. The controller is programmed to automatically determine and adjust inputs to the gas turbine engine in order to cause the pump to produce a user-specified hydraulic output.

Abstract: A plant or refinery may include equipment such as condensers, regenerators, distillation columns, rotating equipment, compressors, pumps, turbines, or the like. Different operating methods may impact deterioration in equipment condition, thereby prolonging equipment life, extending production operating time, or providing other benefits. Mechanical or digital sensors may be used for monitoring equipment to determine whether problems are developing. For example, sensors may be used in conjunction with one or more system components to perform invariant mapping, monitor system operating characteristics, and/or predict pressure, volume, surges, reactor loop fouling, gas quality, or the like. An operating condition (e.g., of one or more pieces of equipment in the plant or refinery) may be adjusted to prolong equipment life or avoid equipment failure.

Abstract: A communication apparatus comprises a controller configured to control an output of a reverse power flow-power source that generates power for performing a reverse power flow from a facility to a power grid; and a transmitter configured to transmit reverse power flow-power source information about the reverse power flow-power source to a management server that transmits a power instruction message.

Abstract: The present disclosure relates to systems and methods that are useful in control of one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants, methods of starting power production plants, and methods of generating power with a power production plant wherein one or more control paths are utilized for automated control of at least one action. The present disclosure more particularly relates to power production plants, control systems for power production plants, and methods for startup of a power production plant.

Abstract: A fuel control system according to an exemplary aspect of the present disclosure includes, among other things, a fuel delivery valve selectively moveable to a closed position to shut off a flow of fuel to a downstream location. The system further includes a windmill bypass valve, and a shutoff pressure line between the windmill bypass valve and the fuel delivery valve. The windmill bypass valve is selectively operable to direct fuel to the shutoff pressure line to assist the movement of the fuel delivery valve to the closed position. A method is also disclosed.

Abstract: A plant or refinery may include equipment such as condensers, regenerators, distillation columns, rotating equipment, compressors, pumps, turbines, or the like. Different operating methods may impact deterioration in equipment condition, thereby prolonging equipment life, extending production operating time, or providing other benefits. Mechanical or digital sensors may be used for monitoring equipment to determine whether problems are developing. For example, sensors may be used in conjunction with one or more system components to perform invariant mapping, monitor system operating characteristics, and/or predict pressure, volume, surges, reactor loop fouling, gas quality, or the like. An operating condition (e.g., of one or more pieces of equipment in the plant or refinery) may be adjusted to prolong equipment life or avoid equipment failure.

Abstract: A method of starting a gas turbine engine includes determining an abnormal shutdown condition during operation of the gas turbine engine and determining a first set of lightoff parameters for the gas turbine engine. The method also includes restarting the gas turbine engine using the first set of lightoff parameters. The method further includes iteratively determining subsequent first sets of lightoff parameters and restarting the gas turbine engine using a respective subsequent first set of the determined subsequent first sets of lightoff parameters until the gas turbine maintains a first set of operational parameters, where the first set of operational parameters is representative of a robust lightoff of the gas turbine engine.

Abstract: A multi-position GSOV and control of the multi-position GSOV are disclosed. An example method may include determining a value of a parameter associated with a fuel train, wherein the fuel train is associated with an engine; determining a setting associated with the parameter; and causing, based on the value of the parameter and the setting, a position of a gas shut-off valve (GSOV) of the fuel train to be reconfigured to cause a flow rate of fuel flowing through the GSOV to change from a first flow rate to a second flow rate, wherein the second flow rate is greater than a zero percent flow rate and less than a one hundred percent flow rate.

Abstract: A flow ratio calculation device includes: a flow volume ratio computer that, using a predetermined relationship between a first parameter that can express a combustion state in a combustor and a flow volume ratio of fuels flowing through multiple fuel systems, is configured to find the flow volume ratio based on a value of the first parameter; a correction value computer configured to find a correction value of the flow volume ratio when a load of a gas turbine changes; a fluctuation sensor configured to sense fluctuations in a value correlated with the load of the gas turbine; and a corrector configured to correct the flow volume ratio found by the flow volume ratio computer with the correction value found by the correction value computer when a fluctuation in the value correlated with the load of the gas turbine is sensed by the fluctuation sensor.

Abstract: The present disclosure provides methods and systems for controlling a propeller-driven aircraft powered by at least one gas turbine engine. A thrust change is obtained corresponding to a difference between an actual thrust and a desired thrust for an engine. When the thrust change is greater than a pre-determined threshold, a setting change to one or more control input(s) of the engine is determined. One or more commands are output to cause the setting change of the control input(s).

Abstract: A bypass valve for a fuel control includes a sleeve, a spool, and a biasing member. The sleeve has a body extending between a first end and a second. The first end defines a first bypass valve port. The body defines a second bypass valve port, a third bypass valve port, and a shutoff port. The second end defines a fourth bypass valve port. The spool is received within the inner bore and is movable between a first position and a second position. The biasing member biases the spool toward the first position.

Abstract: A gas turbine engine system includes a gas turbine engine and a control system including sensors for monitoring operating properties of the engine, a signaling device that outputs a discrete switching signal indicative of an engine load change, such as connecting or disconnecting an electrical load in an electrical power system powered by the gas turbine engine, and an electronic control unit. The control unit calculates an engine load estimate based upon the switching signal, the operating properties, and statistical information in a recursive statistical estimator.

Abstract: One example aspect of the present disclosure relates to a method. The method can include determining, by one or more autonomous distress tracking (ADT) devices installed in a designated fire zone, a state of the vehicle. When the state of the vehicle is the normal state, the method can include transmitting first data via a first transmitter at a first interval, wherein the first transmitter is configured to transmit messages over a frequency band used for normal communications. When the state of the vehicle is the possible distress state, the method can include transmitting second data via the first transmitter at a second interval. When the state of the vehicle is the distress state, the method can include transmitting third data continuously via a second transmitter, wherein the second transmitter is configured to transmit messages over a frequency band reserved for emergency communications.

Abstract: This disclosure includes engines that are capable of controlling an air-fuel ratio responsive to rapid changes in the calorific value of a fuel gas. Some engines include an A/F valve, a solenoid valve, and a control unit configured to close the A/F valve when an average opening degree of the solenoid valve is lower than a preset target opening degree, and open the A/F valve when the average opening degree is equal to or higher than the target opening degree. In some engines, when the opening degree of the solenoid valve has been an upper limit opening degree or a lower limit opening degree of the solenoid valve over a predetermined number of times, the control unit is configured to compare with the upper or lower limit opening degree, in lieu of the average opening degree, against the target opening degree to open or close the A/F valve.

Abstract: A regulator device for automatically regulating a power plant of a rotary wing aircraft having a turbine engine includes a computer system. The computer system, while implementation of an idling mode of operation of the turbine engine is requested and the aircraft is standing on ground, implements the idling mode of operation and operates the turbine engine in compliance with idling mode of operation as a function of operational and hierarchically ordered conditions either through a first mode of regulation by regulating a speed of rotation (Ng) of a gas generator of the turbine engine or through a second mode of regulation by regulating a speed of rotation (NTL) of a free turbine of the turbine engine.

Abstract: A turbomachine fuel circuit including: a low pressure pump; a high pressure pump; a low pressure conduit connecting the low pressure pump to the high pressure pump; a high pressure conduit supplied by the high pressure pump, in which a component is arranged; a mechanism for testing operation of the component; a check valve capable of closing off a segment of the conduit when the pressure in the low pressure conduit is less than a predetermined threshold value; and the testing mechanism is capable of detecting that the check valve at least partly closes off the segment.

Abstract: A fuel system for an aircraft includes a main pump, a servo pump, a servo minimum pressure valve, and a servo pump bypass connection element. The main pump receives fuel from a source. The servo pump also receives fuel from the source. The servo minimum pressure valve receives fuel from the main pump supplied through a first line and the valve receives fuel from the servo pump supplied through a second line. The servo pump bypass connection element connects the first line and the second line.

Abstract: Techniques are provided for detection of malfunctioning sensors in a multi-sensor IoT environment. An exemplary method comprises: obtaining sensor data from a plurality of sensors; and determining if a first sensor is malfunctioning based on a comparison of the sensor data of the first sensor with the sensor data obtained from one or more additional sensors within the plurality of sensors, wherein the additional sensors within the plurality of sensors are identified based on a location and/or a sensor type of the additional sensors relative to a location and/or a sensor type of the first sensor. Remedial steps are optionally performed for a given malfunctioning sensor based on one or more predefined policies. For example, the remedial steps may comprise resetting the given malfunctioning sensor, calibrating the given malfunctioning sensor, servicing the given malfunctioning sensor, and/or notifying one or more users of the malfunction.

Abstract: A control device (101) that controls a fuel gas supply system (100) that comprises: a compressor (1) that supplies compressed fuel gas to a load apparatus (15); an inflow amount regulating means (5) that regulates the amount of fuel gas that flows into the compressor (1); and an anti-surge valve (7) that is for returning to an inlet side of the compressor (1) fuel gas that is discharged from the compressor (1).

Abstract: A combustor includes fuel nozzles that extend in an axial direction of a combustor main body and are capable of injecting fuel from injection holes on a combustion chamber side. The combustor includes a phase adjusting unit which partially changes a flow path cross-sectional area of at least one of the fuel nozzles in the axial direction such that phases of flow rate fluctuation of fuel do not match with respect to at least two of the fuel nozzles.

Abstract: The invention concerns a fuel system (1) for a turbomachine comprising: —a control circuit (9a), —a main circuit (9b), —a flow rate regulator (2), suitable for regulating the flow of fuel in the control circuit (9a) and in the main circuit (9b) depending on the speed of the turbomachine, and —a drain tank (4) being designed to draw fuel from, store fuel in and drain fuel into the main circuit (9b) on the basis of the pressure difference between the main circuit (9b) and the tank (5) or the high-pressure pump (6) to which it is connected.

Abstract: During a stage (E0) of starting the turbine engine, the method of the invention comprises: an open-loop generating step (E10) of generating a fuel flow rate command (WF_OL) from at least one pre-established relationship; and a closed-loop monitoring step (E20-E30) of monitoring at least one operating parameter of the turbine engine selected from: a rate of acceleration (dN2/dt) of a compressor of the turbine engine; and a temperature (EGT) at the outlet from a turbine of the turbine engine; this monitoring step comprising maintaining (E30) the operating parameter in a determined range of values by using at least one corrector network (R1, R2, R3) associated with the parameter and suitable for delivering a signal for correcting the open-loop generated fuel flow rate command so as to maintain the operating parameter in the determined range of values.

Abstract: The invention relates to a fuel metering and distribution unit (10) which comprises in particular a slide valve (20) and a set of slots (41) configured with geometries, dimensions and positions such that: in a first range of displacement of the slide valve, the flow area (31) which feeds the outlet port of the start-up ramp is progressively opened with the displacement of the slide valve (20), while the area (41) of the set of slots which feeds the outlet port of the main ramp is closed, then, in a second range of displacement of the slide valve (20), the area (41) of the set of slots which feeds the outlet port (42) of the main ramp is progressively opened with the displacement of the slide valve, while the flow area (31) which feeds the outlet port of the start-up ramp is kept open, the outlet port (42) of the main ramp thus being able to receive a portion of the total metered flow rate at the flow area (31) feeding the outlet port of the start-up ramp.

Abstract: Methods and systems for processing a signal indicative of at least one operating condition of a gas turbine engine to remove noise associated therewith are provided. The method and systems receive a signal from one or more sensors operably coupled to a gas turbine engine, retrieves one or more known system parameters and a previously determined average signal, and processes the signal using the system parameter and the previously determined average signal to remove noise therefrom. In some of the described methods and systems, the processed signal is then compared to predetermined upper and lower limits, and, if the processed signal exceeds the limits, at least one component of the gas turbine engine, such as a fuel-flow split, is adjusted in an effort to bring the signal back within the limits.