RU148619U1 - FILLING SYSTEM FOR FUEL COLLECTORS OF COMBUSTION CHAMBERS OF A GAS TURBINE ENGINE - Google Patents

Abstract

1. A system for filling the fuel manifolds of the combustion chambers of a gas turbine engine, including a pump unit, having the possibility of its input connecting to the fuel tank, and the output, through the main fuel line through the distributor, with fuel dispensers into the manifolds of the combustion chamber, characterized in that at least one fuel the collector has a second input connected by the first additional fuel line to the output of the pumping unit, and an output connected by a second additional fuel line to the input to a pine block, and shut-off valves are installed in the additional fuel lines. 2. The system according to claim 1, characterized in that in the first additional fuel line there is a fuel pressure regulator connected to a gas pressure sensor in the combustion chamber.

Description

The utility model relates to the field of aircraft engine manufacturing and can be used in fuel supply systems of gas turbine engines (GTE) to control the supply of fuel to the manifolds of the main and / or afterburner of the GTE combustion chambers.

A study of the prior art showed that in the existing systems for controlling the supply of fuel to the main and afterburner combustion chambers of a gas turbine engine, the influence of the process of filling the fuel collectors on the regulation of engine thrust during acceleration is far from always taken into account. This leads to a stepwise change in the effective fuel consumption and, accordingly, to a stepwise change in the engine thrust during the throttle response. A stepwise change in the effective fuel consumption can lead to an undersupply of engine thrust at the right time. This reduces the reliability of the engines and the safety of their operation, and also increases the response time by the time of filling the fuel collector (1-3 sec.), Which is very important for controlling the operation of the gas turbine engine.

A known system for controlling the supply of fuel to the manifolds of the afterburner of a gas turbine engine, containing a series-connected block of sensors for engine and air parameters at the engine inlet, an electronic regulator of engine operating modes, and an electric hydro-converter unit. Afterburner fuel dispensers are connected to the output of the electro-hydraulic converters block, one for each afterburner fuel manifold, each dispenser is connected to its afterburner fuel manifold through its shutoff valve. Shutoff valves are controlled by an electronic controller.

During operation of the system, the temperature measured at the engine inlet air, the air pressure behind the engine compressor, the gas pressure behind the engine turbine, the position of the engine control lever and the fuel consumption in the main combustion chamber, measured by the sensor unit, the electronic controller of the main combustion chamber generates a preset flow rate fuel supplied to and from the collectors in the afterburner.

Depending on the value of the prescribed boost fuel consumption, the electronic controller generates control actions that enter the electrohydraulic converter, where they are converted into hydraulic control actions on the dispensers. The number of dispensers depends on the number of collectors of the afterburner and is determined by one dispenser per collector.

Starting the afterburner and bringing the engine to the minimum afterburner mode is ensured by the first dispenser and the first (starting) collector. When moving the engine control lever to the “minimum boost” platform, the electronic controller provides:

- Calculation of the prescribed boost fuel consumption for the “minimum boost” mode;

- transfer of the first dispenser to a position corresponding to a predetermined consumption of afterburning fuel;

- opening the first shutoff valve;

- inclusion of the unit "firing track".

After starting the afterburner and the engine enters the “minimum afterburner” mode, the electronic controller generates a signal to the pilot, “Afterburner is on”.

When the pilot transfers the engine control lever to the "maximum boost" position, the electronic controller provides:

- Calculation of the prescribed fuel consumption of afterburning fuel for the "maximum boost" mode;

- distribution of a predetermined afterburner fuel consumption between the batchers depending on the throughput of the afterburner fuel collector corresponding to the batcher;

- alternate inclusion in the work of the remaining dispensers.

In this case, when the second dispenser is turned on, the electronic controller provides:

- transfer of the second dispenser to a position corresponding to the afterburner fuel consumption set for it;

- calculation of the time of filling the second collector with fuel (the volumes of the collectors are stored in the memory of the electronic controller);

- opening of the second shutoff valve;

- transfer of the first dispenser while filling the second collector to a position corresponding to the afterburner fuel consumption set for it, increased by an amount corresponding to the volume of the second collector.

The translation is carried out evenly so that by the end of the filling time the flow will increase by the value of the collector volume.

At the moment of completion of filling the second collector by the command of the electronic regulator, the first dispenser returns to the position corresponding to the afterburning fuel consumption set for it in the shortest possible time.

The inclusion of the remaining dispensers is carried out similarly (see RF patent No. 2438031, CL F02C 9/28, 2011).

As a result of the analysis of the known solution, it should be noted that with such filling of the fuel collectors, a smooth change in the effective fuel consumption and, accordingly, a smooth change in the engine thrust during the throttle response are ensured. However, the process of filling the collectors is carried out for a rather long time, which significantly increases the injectivity time, in addition, the system does not provide for preliminary filling of the starting collector, which also increases the injectivity time.

A well-known fuel consumption control system at the start of a gas turbine engine, comprising a series-connected sensor block of engine and air parameters at the engine inlet, an electronic regulator of engine operating modes, an electrohydraulic converter unit, a fuel meter with a position sensor for the metering element. The output of the fuel metering device is connected to the first and second fuel collectors of the combustion chamber, and it is connected directly to the first fuel collector, and to the second through a switch controlled by an electronic controller. The first output of the switch is connected directly to the second collector of the combustion chamber, and its second output is connected to the second collector of the combustion chamber via a hydraulic resistance.

During the operation of the system, according to the parameters measured using the sensor unit, the electronic controller generates, according to a predetermined dependence, the required fuel consumption in the engine combustion chamber.

Depending on the required fuel consumption, the electronic regulator, using the flow characteristic of the first dispenser, which is stored in the non-volatile memory of the electronic regulator during the engine acceptance tests, determines the preset position of the dispenser, compares it with the actual position of the dispenser, and controls the fuel consumption by changing Using an electrohydroconverter, the position of the dispenser. Metered fuel is supplied to the first manifold of the combustion chamber.

Additionally, during the start-up of the gas turbine engine, the electronic speed controller measured using the sensor block compares the rotor speed of the engine rotor with the predetermined speed setting of the "small gas", which is stored in the non-volatile memory of the electronic controller during the engine acceptance tests.

When the engine speed reaches the “small gas” setting, the electronic controller blocks a further increase in the set engine rotor speed by the predetermined time required for the engine to warm up.

At the command of the electronic regulator, using a switch, a second collector is connected to the dosed fuel supply path behind the dispenser via a hydraulic resistance. The resistance value is chosen equal to the spill 15-20% of the total hydraulic resistance of the nozzles of the first collector.

After the engine warm-up time has elapsed, by command of the electronic regulator, a second collector is connected via a switch to the dosed fuel supply path directly behind the metering unit. At the same time, the electronic regulator removes the lock of the set rotational speed of the engine rotor, providing the possibility of transferring the gas turbine engine to operating modes (nominal, take-off, etc.) (see RF patent No. 2435973, class F02C 9/26, 2011) - the closest analogue.

As a result of the analysis of the known system, it should be noted that its disadvantage is that during the supply of additional fuel through hydraulic resistance and engine warming up, the engine mode does not change, and when the fuel is supplied, it can be dusted into the combustion chamber, in addition, the starting manifold is not pre-filled, which increases the response time.

The technical result of this utility model is to increase the speed of the control system by reducing the time it takes to fill the fuel of the fuel manifold included in the operation, as well as providing a smooth change in engine thrust at throttle response.

The specified technical result is ensured by the fact that in the filling system of the fuel manifolds of the combustion chambers of a gas turbine engine, including a pump unit, having the possibility of its input connecting to the fuel tank, and the output - through the main fuel line through the distributor - with fuel dispensers into the manifolds of the combustion chamber, is new that at least one fuel manifold has a second input connected by the first additional fuel line to the output of the pump unit, and the output connected the second additional fuel line with the inlet of the pump unit, and shut-off valves are installed in the additional fuel lines, while in the first additional fuel line a fuel pressure regulator can be installed connected with the gas pressure sensor in the combustion chamber.

The essence of the claimed utility model is illustrated by graphic materials on which the system diagram is presented. The diagram shows one combustion chamber and two collectors. Naturally, the number of combustion chambers, as well as their collectors, may be different. This does not change the essence of the declared decision.

On graphical materials, position 1 denotes a gas turbine engine combustion chamber, positions 2 and 3 are fuel manifolds, through nozzles 4 of which fuel is supplied to combustion chamber 1. The fuel collector filling system also includes a pump unit 5, connected by the main fuel line to the fuel tank 6. Outlet the pump unit through the main fuel line through the fuel distributor 7 is connected to the dispensers 8 and 9, which dispense the fuel into the collectors 2 and 3. One of the collectors (collector 3 in the diagram) there is an additional input connected by the first additional fuel line to the output of the pump unit 5 and an additional output connected by the second additional fuel line to the input of the pump unit 5. Shut-off valves 10 and 11 are installed in the additional lines. It is most expedient to connect the output of the shut-off valve 10 in close proximity to the output of the dispenser 9, and the shut-off valve 11 to the exit of the collector. Position 12 denotes a GTE operation control unit, which includes an automatic operation control system and a GTE operation control panel located in the cockpit. The control unit 12 is connected with the pump unit 5, with the distributor 7, with shut-off valves 10 and 11. In the first additional fuel line connecting the additional input of the manifold 3 to the output of the pump unit 5, a fuel pressure regulator 13 connected to the control unit 12 can be installed and with a sensor 14 of the gas pressure in the combustion chamber 1.

All elements and units of the system are standard and are used for their intended purpose.

As a distributor 7 and a regulator 13 can be used standard electronic or electromechanical regulators. As fuel dispensers, dispensers with an adjustable flow area are used. As shut-off valves, standard valves with controlled shut-off element are used.

The system operates as follows.

During the operation of the gas turbine engine, in one of the modes, for example, “small gas”, fuel is pumped from the tank 6 through the distributor 7 to the dispenser 8 from the tank 6, and through it, into the first manifold 2 and through the nozzles 4 of this collector it enters the combustion chamber for GTE operation in this mode. The collector 3 is not involved in the operation, that is, the distributor 7 turned off the fuel supply to the dispenser 9. At the command of block 12, the shut-off valves 10 and 11 are open and the fuel from the output of the pump unit 5 through the first additional fuel line through the regulator 13 enters the second input collector 3 and fills it with fuel. When filling this collector, the fuel from it through the outlet of the collector through the second additional fuel line enters the input of the pump unit 5. Thus, with the working first collector and the second collector not working, the latter is filled with fuel that constantly circulates along the circuit, which also prevents overheating fuel. The regulator 13 (if any) in this case, according to the testimony of the sensor 14 sets the pressure of the fuel circulating through the collector 3 so that it is always equal to or slightly less than the gas pressure in the combustion chamber 1. This excludes the flow (dusting) of fuel from the nozzles of the idle second collector 3 fuel into the combustion chamber 1.

When the engine runs to a more intensive mode, on command from block 12 (in accordance with the command of the pilot or control system), the dispenser 7 turns on the dispenser 9, opening the fuel supply to the second manifold 3. Almost simultaneously, a command is given to close the shut-off valves 10 and 11, which overlap the first and second additional fuel lines in which they are installed, and cut off the second inlet and outlet of the manifold 3 from the inlet and outlet of the pump unit 5, stopping the circulation of fuel through the manifold 3, which when that is filled with fuel.

From the dispenser 9, the fuel enters the already almost filled reservoir and almost immediately enters the nozzles 4 for its supply to the combustion chamber.

Thus, when you turn on a more intensive mode of operation of the gas turbine engine, which requires additional fuel supply, no time is wasted filling the fuel collector 3 put into operation, which significantly reduces the response time.

The system can work to fill almost all fuel collectors of both the main and afterburner combustion chambers.

It is also very important that the connection and filling of the collectors does not affect the dynamic properties of the engine, providing a reduction in the throttle response and a smooth change in engine thrust.

Claims (2)

1. A system for filling the fuel manifolds of the combustion chambers of a gas turbine engine, including a pump unit, having the possibility of its input connecting to the fuel tank, and the output - through the main fuel line through the distributor - with fuel dispensers into the manifolds of the combustion chamber, characterized in that at least one fuel the collector has a second input connected by the first additional fuel line to the output of the pumping unit, and an output connected by a second additional fuel line to the input to pine block, and in the additional fuel lines shut-off valves are installed. 2. The system according to claim 1, characterized in that in the first additional fuel line there is a fuel pressure regulator connected to a gas pressure sensor in the combustion chamber.

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