Abstract: There are described methods and systems for operating an aircraft having two or more engines. One method comprises operating the two or more engines of the aircraft in an asymmetric operating regime, wherein a first of the engines is in an active mode to provide motive power to the aircraft and a second of the engines is in a standby mode to provide substantially no motive power to the aircraft; governing the first engine in the active mode using a first governing logic; and governing the second engine in the standby mode using a second governing logic, the second governing logic based on a target compressor speed and variable geometry mechanism (VGM) settings that are adjusted using trim values dependent on at least one parameter of the second engine in the standby mode.

Abstract: A combustion control device including a bleed valve control unit for controlling a bleed valve disposed on a bleed pipe for performing bleeding so that a part of the compressed air flowing into the casing is not used as combustion air in the combustor, a fuel control unit for controlling a fuel regulating valve for regulating a fuel flow rate of fuel supplied to the combustor, and a temperature acquisition unit. Upon reception of a load rejection signal for cutting off a load from the gas turbine, the bleed valve control unit controls a valve opening degree of the bleed valve from a closed state to an open state with a prescribed opening degree, and the fuel control unit controls the fuel regulating valve such that the acquired flame temperature falls within a predetermined temperature range defined by an upper limit value and a lower limit value.

Abstract: A control system for active stability management of a compressor element of a turbine engine is provided. In one example aspect, the control system includes one or more computing devices configured to receive data indicative of an operating characteristic associated with the compressor element. For instance, the data can be received from a high frequency sensor operable to sense pressure at the compressor element. The computing devices are also configured to determine, by a machine-learned model, a stall margin remaining of the compressor element based at least in part on the received data. The machine-learned model is trained to recognize certain characteristics of the received data and associate the characteristics with a stall margin remaining of the compressor element. The computing devices are also configured to cause adjustment of one or more engine systems based at least in part on the determined stall margin remaining.

Abstract: An on-ground engine starter interrupt system that prevents engine start up when either the throttle is open or the fuel control is engaged (or both) for reciprocating and turbine helicopters is disclosed. The on-ground engine starter interrupt system works for Robinson helicopter models R22, R44, and R66.

Abstract: A gas turbine includes: multiple fuel systems; a combustor that combusts fuels from the multiple fuel systems in compressed air to generate combustion gas; and a turbine that is driven by the combustion gas. A flow volume ratio calculation device which calculates the flow volume ratio of the fuels flowing in the multiple fuel systems includes calculators that receive values of a first parameter and a second parameter capable of expressing the combustion state in the combustor, and that calculate the flow volume ratio relative to the received values of the two parameters from a predetermined relationship between the two parameters and the flow volume ratio.

Abstract: Embodiments of the present invention generally relate to a vapor retention device and methods of using a vapor retention device to manage propellant for upper stage space vehicles. The use of a vapor retention device, in combination with controlled acceleration, drives liquid propellant from a propellant supply line communicating with an upper stage main engine back into a propellant tank and establishes an insulating liquid/gas propellant interface that prevents the exchange of gaseous propellant across the interface.

Abstract: Systems and methods for determining bi-propellant volume and adjusting a mixture ratio are discussed herein. A controller can calculate an adjusted mixture ratio and command the rocket engine to implement the adjusted mixture ratio by opening or closing valves of the propellant tanks, which changes the volumetric flow rates of each of the propellants. The adjusted mixture ratio can be calculated by an algorithm based on sensed or calculated data associated with each propellant. The adjusted mixture ratio can be used to evenly deplete the propellants to reduce the amount of each propellant remaining after a mission and to improve propellant use, which allows for an increase in a non-propellant payload.

Abstract: An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

Abstract: A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner and an inner liner. At least one of the outer liner and the inner liner has an upstream liner portion and a downstream liner portion with an annular gap therebetween. At least one dilution flow assembly is arranged to bridge across the annular gap. The at least one dilution flow assembly includes an upstream liner panel and a downstream liner panel with a dilution opening provided between the upstream liner panel and the downstream liner panel, and a plurality of dilution fence members arranged within the dilution opening and extending into a combustion chamber. The plurality of dilution fence members are arranged in successive arrangement in a circumferential direction and are arranged such that successive dilution fence members are alternatingly offset in an axial direction.

Abstract: A fuel/air supply device including a fuel supply arrangement designed to convey fuel to a fuel outlet of the fuel/air supply device, a primary air supply arrangement designed to convey air to an air outlet of the fuel/air supply device, and a secondary air supply arrangement connecting the primary air supply arrangement to the fuel supply arrangement at a position upstream of a fuel compressor that is included in the fuel supply arrangement. The secondary air supply arrangement includes an air conduit that has a restricted portion for defining a relatively small air passage in the air conduit, and can be used for realizing a fuel/air mixture of low calorific value if so desired on the basis of a supply of air to the fuel without needing complex control measures.

Abstract: A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

Abstract: A method of controlling a gas turbine engine including receiving an instantaneous thrust demand for current operation of the engine, determining the inlet flow rate and/or the pressure ratio within the compressor of the engine and determining whether the inlet flow rate and/or the pressure ratio match the working line for the compressor. The angle of one or more vane of the compressor is adjusted according to a closed control loop if the inlet flow rate and/or pressure ratio lie outside said desired range in order to adjust the inlet inflow rate and/or pressure ratio to meet the working line. The fuel flow to the engine combustor is adjusted concurrently in order to meet the thrust demand.

Abstract: A gas turbine fuel flow rate setting device includes a flow rate ratio computing unit and a flow rate computing unit. The flow rate ratio computing unit is configured to accept a parameter having a correlation with a gas turbine output, and use a predetermined flow rate ratio relationship between the parameter and a fuel flow rate ratio between a plurality of premixing nozzle groups to determine a fuel flow rate ratio corresponding to the parameter which has been accepted. The flow rate computing unit is configured to use the fuel flow rate ratio determined by the flow rate ratio computing unit to determine a flow rate of a fuel to be supplied to each of the plurality of premixing nozzle groups.

Abstract: A system includes a generator configured to be electrically coupled to a grid, an engine configured to drive the generator, and a solid state generator coupled between the grid and an energy storage device. The system further includes a bias controller configured to detect a frequency of the grid and to responsively provide a bias signal to a speed controller of the engine. The bias controller may include a frequency bias controller configured to generate a frequency bias load sharing signal responsive to the detected frequency of the grid and a load sharing controller that receives the frequency bias load sharing signal and that generates the bias signal responsive to the load sharing signal.

Abstract: A method of testing and/or controlling the operation of an axial turbomachine through which passes a gas stream, includes the following actions: measurement of operating parameters of the turbomachine, said parameters including pressure in the gas stream at different axial positions, and calculation of operating conditions of the turbomachine from the measured parameters and the Laplace coefficient ? of the gas passing through the turbomachine, wherein the measurement of parameters includes a measurement of the temperature of the gas stream, and the calculation of operating conditions includes a determination of the Laplace coefficient ? on the basis of the measurement of the temperature of the gas stream.

Abstract: A method of controlling an operating temperature of a first combustion zone of a combustor of a rotary machine includes determining a current operating temperature and a target operating temperature of a first combustion zone using a digital simulation. The method further includes determining a derivative of the current operating temperature with respect to a current fuel split using the digital simulation. The fuel split apportions a total flow of fuel to the combustor between the first combustion zone and a second combustion zone. The method also includes calculating a calculated fuel split that results in a calculated operating temperature approaching the target operating temperature. The method further includes channeling a first flow of fuel to the first combustion zone and a second flow of fuel to the second combustion zone.

Abstract: The invention relates to a method (E) for detecting the ignition of a turbine engine combustion chamber, the method (E) comprising the steps of: receiving (E11) a first measurement of the exhaust gas temperature downstream from the combustion chamber, before an attempt to ignite said combustion chamber; receiving (E12) a temperature threshold; receiving (E13) a secondary detection criterion; updating (E14) the received temperature threshold as a function of the secondary detection criterion received; receiving (E15) a second measurement of the exhaust gas temperature, after the attempt to ignite the combustion chamber; comparing (E16) the updated temperature threshold with the difference between the first and second exhaust gas temperature measurements; and determining (E17) the state of ignition of the combustion chamber.

Abstract: A control device for a two-shaft gas turbine power generation facility includes: a basic output calculation unit which obtains a basic output command value in accordance with a required output; a component separation unit which divides the basic output command value into high and low frequency components; an opening degree command output unit which obtains an opening degree of a fuel adjustment valve and outputs an opening degree command to the fuel adjustment valve; a basic power transmission and reception amount calculation unit which obtains a basic power transmission and reception amount of the electric power between an induction motor and a power system on the basis of the high-frequency component; and a power transmission and reception command output unit which outputs a power transmission and reception command indicating a power transmission and reception amount in accordance with the basic power transmission and reception amount to a frequency converter.

Abstract: A gas turbine system can estimate an amount of compressed air supplied to a combustor and limit a fuel amount according to the estimated compressed air amount. A control apparatus of the system includes a sensing unit to measure the turbine rotor speed; a compressed air amount estimation unit to estimate a change rate MR of an amount of compressed air produced by the compressor and supplied to the combustor, based on the measured turbine rotor speed; and a fuel amount control unit to control a fuel amount FC supplied to the combustor, based on the estimated change rate MR. The control apparatus can preemptively control the fuel amount in response to variations in the compressed air amount by a momentarily changing turbine rotor speed and can limit the turbine inlet temperature to below the maximum allowable temperature, to protect the turbine and/or combustor against fluctuations in compressed air amount.

Abstract: A flame produced within a premixer is promptly extinguished and a reduction in output power of a gas turbine associated with extinguishment is suppressed.

Abstract: A nozzle assembly group for a combustion chamber of an engine, with multiple nozzles for introducing fuel into the combustion chamber that are arranged next to each other, wherein each nozzle has a nozzle outlet opening and a fuel channel for conveying fuel in the direction of the nozzle outlet opening. According to the invention, it is provided that at least two different types of nozzles are provided, wherein the nozzles of different types have nozzle outlet openings with an identical cross section, and for predetermining different flow rates of fuel through the fuel channels of the nozzles of different types, a cross section of a fuel channel of one type of nozzle is different from a cross section of a fuel channel of another type of nozzle.

Abstract: A propulsion system is disclosed comprising a gas turbine engine and an acceleration schedule which determines the rate of acceleration of the gas turbine engine from an idle condition in response to a demand for increased thrust off-idle. The acceleration schedule determines the rate of acceleration in dependence upon the value of an engine parameter of the engine the value of which is substantially unaltered by variation in the magnitude of an electrical load drawn from the engine while it is operating in the idle condition.

Abstract: An asymmetrical electronic control system for a gas turbine, which is designed to control a set of functions associated with logic input data or data from sensors and associated with output data, in particular for an actuator, the system including a primary electronic control unit configured to process the entire set of functions; a secondary electronic control unit, partially redundant with the primary unit, configured to process only a strict subset of sufficient functions to operate or start the gas turbine in an acceptable degraded mode when the primary unit is faulty; a redundant or main chain selection and switching module for selecting one or other of the primary and secondary units in order to control the gas turbine according to the operating state of the primary unit.

Abstract: There is provided a method including: performing an upgrade of reducing a supply amount of cooling air supplied to a turbine and replacing at least some of components provided in the turbine with components adapted to the supply amount of cooling air; and changing a set value calculation function according to the post-upgrade supply amount of cooling air and the replaced components.

Abstract: A method (30) of controlling fuel flow in a gas turbine engine. First, detect a surge condition. Set fuel flow demand (Wf_D) proportional to compressor discharge pressure (P30). Detect actual fuel flow (Wf_A). Then apply an enhanced schedule (50) for fuel flow demand (Wf_D) while fuel flow demand (Wf_D) is less than a predefined proportion (k) of actual fuel flow (Wf_A). Also a gas turbine engine (10), fuel flow system (68) and fuel flow control system (76) each implementing the method (30).

Abstract: An object identification device that can accurately identify a detected object is obtained. A radar inputs a radar confidence for an object in each of categories to a CPU; a camera inputs a camera confidence for an object in each of categories to the CPU; the CPU weighted-averages the respective confidences of the radar and the camera for each category so as to obtain the average confidence of each category; then, the category having a highest average confidence is identified as the kind of the object.

Abstract: An overthrust protection system for an aircraft engine. The system comprises an engine overspeed protection unit comprising overspeed logic and an overspeed solenoid valve controlled by the overspeed logic, the overspeed logic configured to energize the overspeed solenoid valve for removing fuel flow to the engine upon detection of an overspeed condition of the aircraft engine; and an overthrust controller coupled to the overspeed protection unit and configured to measure engine thrust and to detect an overthrust condition when an engine thrust threshold has been exceeded, and configured to trigger energizing of the overspeed solenoid valve upon detection of the overthrust condition and an aircraft-on-ground condition.

Abstract: The present disclosure provides a method for controlling combustor cans of a gas turbine. Detectors disposed on combustor cans are operable to detect combustion vibration values of the combustor cans. The combustion vibration value is compared to a reference value. Combustor cans having a combustion vibration value greater than a reference value are assigned to a first group, and combustor cans having a combustion vibration value not greater than the reference value are assigned to a second group. The output of each combustor can in the first group is regulated to lower the combustion vibration value, thereby improving the stability of the gas turbine.

Abstract: A system includes a model-based control system configured to receive data relating to parameters of a machinery via a plurality of sensors coupled to the machinery and select one or more models configured to generate a desired parameter of the machinery based on a determined relationship between the parameters and the desired parameter. The one or more models represent a performance of a device of the machinery. The model-based control system is configured to generate the desired parameter using the data and the one or more models control a plurality of actuators coupled to the machinery based on the desired parameter. Further, the model-based control system is configured to empirically tune the one or more models based on the data, the one or more parameters, and the desired parameter, compare the empirical tuning to a baseline tuning, and determine an operational state of the device based on the comparison.

Abstract: A system for controlling an operation of a combustor in a gas turbine that includes: an acoustic sensor configured to periodically measure a pressure of the combustor and generate a raw data stream having the pressure data points resulting from the periodic measurements; and a blowout detection unit configured to receive the raw data stream from the acoustic sensor. The blowout detection unit may include a processor and a machine-readable storage medium on which is stored instructions that cause the processor to execute a procedure related to a detection of a blowout precursor. The procedure may include an ensemble approach in which the detection of the blowout precursor depends upon a outcomes generated respectively by separate detection analytics.

Abstract: A combustion control device is installed in a gas turbine including a compressor, a combustor, a turbine, a turbine bypass pipe through which compressed air from a casing is discharged to a turbine downstream part so as to bypass the turbine, and a turbine bypass valve that regulates a turbine bypass flow rate of the compressed air. The combustion control device includes: a fuel distribution setting unit that sets a turbine inlet temperature or a turbine inlet temperature-equivalent control variable on the basis of input data, and sets fuel distribution ratios on the basis of the turbine inlet temperature or the turbine inlet temperature-equivalent control variable; and a fuel valve opening setting section that sets the valve openings of fuel regulating valves. The fuel distribution setting unit includes correction means for modifying the fuel distribution ratios.

Abstract: A combustion control device (50) is installed in a gas turbine including a compressor (2), combustors (3), a turbine (4), a bleed air pipe (12) through which bleed air is returned to an inlet of an air intake facility (7), and an air bleed valve (22) that regulates the amount of bleed air extracted. The combustion control device (50) includes: a fuel distribution setting unit (70) that sets a turbine inlet temperature or a turbine inlet temperature-equivalent control variable on the basis of input data, and sets fuel distribution ratios on the basis of the turbine inlet temperature or the turbine inlet temperature-equivalent control variable; and a fuel valve opening setting section (81) that sets the valve openings of fuel regulating valves. The fuel distribution setting unit (70) includes correction means for modifying the fuel distribution ratios.

Abstract: A method may involve monitoring a first set of electrical properties associated with an electrical grid configured to couple to a generator and determining whether a transient event is present on the electrical grid based on the first set of electrical properties. The method may also involve determining a mechanical power present on a shaft of the generator based on a second set of electrical properties associated with the generator, the electrical grid, or both when the transient event is present and sending the mechanical power to a controller associated with a turbine configured to couple to the generator, wherein the controller is configured to adjust one or more operations of the turbine based on the mechanical power.

Abstract: A gas turbine drives a power generator by rotating a turbine using combustion gas generated in a combustor as a result of supplying the combustor with fuel and compressed air from a compressor, which is provided with an inlet guide vane at a front stage. An operation control device of the gas turbine enables an IGV priority open flag when the inlet guide vane is not fully open and when the system frequency is lower than or equal to a predetermined threshold value ? or there is a request for increasing the output of the gas turbine. When the IGV priority open flag is enabled, the operation control device sets the degree of opening of the inlet guide vane to be larger than before. Accordingly, the output can be increased without having to increase the turbine inlet temperature, regardless of the operational state of the gas turbine.

Abstract: In one embodiment, a gas turbine system includes a controller configured to receive fuel composition information related to a fuel used for combustion in a turbine combustor; receive oxidant composition information related to an oxidant used for combustion in the turbine combustor; receive oxidant flow information related to a flow of the oxidant to the turbine combustor; determine a stoichiometric fuel-to-oxidant ratio based at least on the fuel composition information and the oxidant composition information; and generate a control signal for input to a fuel flow control system configured to control a flow of the fuel to the turbine combustor based on the oxidant flow information, a target equivalence ratio, and the stoichiometric fuel-to-oxidant ratio to enable combustion at the target equivalence ratio in the presence of an exhaust diluent within the turbine combustor.

Abstract: A method to operate a combustor of a gas turbine is provided. The method includes monitoring the combustion gas temperature by temperature measurements downstream said combustor to measure a respective combustion gas temperature at different locations at respectively equal flow-distances to the burner of the combustion gas, comparing the temperature measurements, opening a valve or increasing the opening position of the valve to control the portion of oxygen containing gas to be tapped off when the comparison reveals that a difference between the temperature measurements exceeds a temperature difference threshold ?T1.

Abstract: An apparatus for controlling a gas-turbine aeroengine is configured to calculate a fuel command to supply fuel based on a calculated desired rotational speed of a low-pressure turbine calculated from an operation angle of a thrust lever installed at an aircraft cockpit pilot's seat, determines whether it is a time point for outputting a command to open/close a bleed-off valve equipped at a high-pressure compressor connected to a high-pressure turbine and to supply the fuel command based on the time point when it is determined to be the time point for outputting the command to open/close the bleed-off valve.

Abstract: A method of controlling a variable vane assembly includes the steps of sensing a first angular deflection of a first array of variable vanes about a first vane axis, and a second angular deflection of a second array of variable vanes about a second vane axis, the first array of variable vanes axially spaced from the second array of variable vanes, and adjusting the angular deflection of one of the first and second arrays of variable vanes, based on the sensed angular deflections from the other of the first and second arrays of variable vanes. A compressor including the variable vane assembly and a method of operating the variable vane assembly for a compressor are also disclosed.

Abstract: Combustion chamber includes a primary stage fuel burner to supply fuel into a primary combustion zone and secondary stage fuel burner supplies fuel into a secondary combustion zone. A sensor is positioned downstream from combustion chamber measuring concentration of one or more compounds. The sensor sends measurements of the concentration of compounds to a processor. The processor compares the measured concentration of the compound with a first threshold value and a second threshold value. The processor supplies more fuel to the primary stage fuel burner if the measured concentration is higher than the first threshold value, supplies more fuel to the secondary stage fuel burner if the measured concentration is higher than the second threshold value, maintaining fuel supply to the primary and secondary stage fuel burners if the measured concentration is lower than the first threshold value and lower than the second threshold value.

Abstract: Aspects of the present disclosure relate generally to a system including: a computing device in communication with a combustion system, wherein the computing device is configured to perform actions including: issuing an input to the combustion system; determining whether one of a dynamic output and an emission output corresponding to the input to the combustion system exceeds a first boundary condition; and adjusting the input to the combustion system by one of a first step change and a second step change; wherein the first step change corresponds to the dynamic output and the emission output not exceeding the first boundary condition, and the second step change corresponds to one of the dynamic output and the emission output exceeding the first boundary condition, the second step change being less than the first step change.

Abstract: A method of monitoring for combustion anomalies in a gas turbomachine includes sensing an exhaust gas temperature at each of a plurality of temperature sensors arranged in an exhaust system of the gas turbomachine, comparing the exhaust gas temperature at each of the plurality of temperature sensors with a mean exhaust gas temperature, determining whether the exhaust gas temperature at one or more of the plurality of temperature sensors deviates from the mean exhaust temperature by a predetermined threshold value, and identifying an instantaneous combustion anomaly at one or more of the temperature sensors sensing a temperature deviating from the mean exhaust temperature by more than the predetermined threshold value.

Abstract: In a method according to the present invention for calculating the combustion ratio RC of fuel added to an exhaust passage, the temperature To of the exhaust gas flowing in the exhaust passage located downstream of a region in which the fuel added to the exhaust passage is burned is acquired; the thermal capacity CE of the exhaust gas is acquired; the energy quantity QF of the fuel supplied to the exhaust passage is acquired; an increase ?To in exhaust temperature To immediately before the exhaust gas is heated is obtained; a change ratio dTo of the exhaust temperature To immediately before the exhaust gas is heated is obtained; a parameter Z relevant to the exhaust gas flowing in the exhaust passage is acquired; and the combustion ratio RC of the fuel added to the exhaust passage is calculated in accordance with RC=(CE/QF)(Z·dTo+?To).

Abstract: A gas turbine combustor includes: multiple gaseous fuel nozzles to inject gaseous fuel; a manifold to distribute gaseous fuel to the multiple gaseous fuel nozzles; a burner flange to secure a burner to an end cover; and a burner body to connect the manifold and the burner flange. Gaseous fuel passages are provided in the end cover, the burner flange, and the burner body. The gaseous fuel passage communicates with the manifold. A second manifold is provided in the burner flange. The gaseous fuel passage is provided in the burner body to make the second manifold communicate with the first mentioned manifold.

Abstract: A saddle-ride type vehicle includes a frame, an engine, a starter motor, a predetermined component, and a coupling member. The engine is supported by the frame. The starter motor is attached to the engine. The predetermined component is disposed adjacent to the starter motor. The coupling member couples the predetermined component to the starter motor.

Abstract: Systems and methods for regulating a bulk flame temperature in a dry low emission (DLE) engine are provided. According to one embodiment of the disclosure, a method may include measuring an exhaust gas temperature (EGT) and determining a target EGT. The target EGT is determined based at least in part on a compressor bleed air flow percentage and a combustor burning mode. The method may include calculating a bias based at least in part on the EGT and the target EGT and applying the bias to a bulk flame temperature schedule. The method may include regulating one or more staging valves and compressor bleeds of the DLE engine based at least in part on the bulk flame temperature schedule. The bulk flame temperature schedule is mapped to parameters of the staging valves and compressor bleeds to reduce nitric oxide, nitrogen dioxide, and carbon monoxide emissions.

Abstract: A system for testing a rotary machine includes a variable load coupled to a shaft driven by the rotary machine, and a controller configured to regulate the rotary machine and the variable load in a closed loop. A variation in a load value of the variable load causes a variation in a power produced by the rotary machine. The controller is further configured to determine a response time required for the power produced by the rotary machine and a power consumed by the variable load to be balanced.

Abstract: A gas turbine engine control system comprising a variable stator vane schedule for normal operation of the gas turbine engine. The system is configured to generate an arm signal indicating potential shaft break. Then the system is configured to alter the variable stator vane schedule to slew each variable stator vane to decrease the available surge margin in response to the arm signal. Or the system is configured to limit a response rate of a variable stator vane actuator in response to the arm signal. Or the system is configured to alter the variable stator vane schedule and limit the response rate of the actuator.

Abstract: Methods and systems are provided for dynamically auto-tuning a gas turbine engine. Initially, parameters of the gas turbine engine are monitored to determine that they are within predefined upper and lower limits such that a margin exists. A first incremental adjustment of an inlet guide vane (IGV) angle is performed. If the monitored parameters are still within the predefined upper and lower limits, a second incremental adjustment of the IGV angle is performed. It is determined that the monitored parameters are still within the predefined upper and lower limits. Additionally, it is determined that a predefined value of the IGV angle has been reached such that the IGV angle is not to be further increased or decreased.

Abstract: A method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply.