JP2964646B2 - Operating devices for gas turbine engines - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a device for operating a gas turbine engine in a facility equipped with a gas turbine engine system.

[0002]

2. Description of the Related Art In general, a gas turbine engine, especially a gas turbine engine for a small aircraft, employs a starter-generator system using a brushed DC machine to generate electric power used during start-up and operation. For the supply, a method is adopted in which a fuel pump or a lubricating oil pump is driven and supplied by power taken out from a rotating shaft of a gas turbine engine. The same applies to various facilities using gas turbine engines other than aircraft.

[0003]

A starter generator system using a brushed DC machine has the following problems.

The commutator and the brush of the brush-equipped DC machine are consumables, which need to be replaced periodically, which requires labor and time and is uneconomical.

[0005] Since a DC machine has a complicated structure, a large size and a large weight as compared with an AC machine, it is said that vehicles such as automobiles using a gas turbine engine, for example, aircraft are reduced in size and weight, and space is effectively used. Not fit for purpose.

Since a gas turbine engine has a high rotational speed, a reduction gear mechanism must be interposed between a fuel pump or a lubricating oil pump and the engine shaft, and between a brushed DC machine and the engine shaft. However, this method does not meet the purpose of reducing the size and weight of vehicles such as automobiles using gas turbine engines, for example, reducing the size and weight of aircraft, and effectively utilizing space.

The fuel supplied to the gas turbine engine is supplied by driving the fuel pump while reducing the rotational speed of the engine by a speed reducer. However, the relationship between the engine speed and the required fuel flow rate is not constant. However, it is difficult to always discharge the required fuel flow rate from the fuel pump with respect to the rotational speed that changes in accordance with the output demand, so that excess fuel is discharged from the fuel pump and supplied to the combustion section of the engine. At present, excess fuel is returned to the suction side and collected, resulting in large power loss.

SUMMARY OF THE INVENTION In view of the above circumstances, an object of the present invention is to provide a gas turbine engine operating device capable of reducing the size and weight of gas turbine engine equipment, facilitating maintenance, and improving engine efficiency. Is what you do.

[0009]

According to a first aspect of the present invention, there is provided a synchronous machine directly connected to a shaft of a gas turbine engine, and the synchronous machine is connected to the synchronous machine at start-up and is shut off during operation. And a switch 7 for switching between the external power supply and the converter 9 at startup and for connecting the synchronous machine 5 and the converter 9 during operation.
And an inverter 10 connected to the converter 9 and transmitting electric power from the external power supply to the synchronous machine 5 via the switch 6 at the time of start-up. The pump is driven by the power supply and by the synchronous machine 5 during operation.

According to a second aspect of the present invention, there is provided a synchronous machine 5 directly connected to a shaft of a gas turbine engine, and a switch 6 which is connected to the synchronous machine 5 at the time of starting and which is switched off during operation. When starting, the external power supply and the converter 9 are used, and during operation, the synchronous machine 5 and the converter 9 are used.
And an inverter 10 connected to the converter 9 and transmitting power from the external power supply to the synchronous machine 5 via the switch 6 at the time of starting. The inverter 10 and the switch 22 The inverter 1 is connected during operation by connecting the AC equipment power supply terminal 23 in series.
0 and an AC equipment power supply terminal 23 are connected by switching a switch 22. Further, a pump driving motor is connected to the converter 9 so that the pump is driven by an external power source at the start and by the synchronous machine 5 at the time of operation. It is something to do.

[0011] The invention of claim 3 is claim 1 or claim 2.
An engine output control device 30 for outputting a speed instruction to a pump driving motor, a spark instruction to a spark plug 24, and the like based on a rotation speed of the synchronous machine 5, a pressure and temperature of a gas turbine engine, an output power command, and the like. It is provided with.

[0012]

According to the first aspect of the present invention, at the time of starting, power can be supplied to the synchronous machine 5 from the external power supply via the switch 7, the converter 9, the inverter 10, and the switch 6, and the synchronous machine 5 is operated as a starter. During operation, the switch 6 is switched to shut off the synchronous machine 5 and the inverter 10, and the switch 7 is switched to connect the converter 9 and the synchronous machine 5. The output of the synchronous machine 5 is switched to the switch 7, the converter 9
And the synchronous machine 5 can be operated as a generator, and the output of the synchronous machine 5 can be supplied to the pump driving motor via the switch 7 and the converter 9 during operation, and the synchronous machine 5 can be used as a power source. it can.

According to the second aspect of the present invention, during operation, the output of the inverter 10 can be supplied to the AC device from the AC device power supply terminal 23 via the switch 22 to use the synchronous machine 5 as a power source. Sometimes synchronous machine 5
Can be supplied to the pump driving motor via the switch 7 and the converter 9, and the synchronous machine 5 can be used as a power source.

According to the third aspect of the present invention, the engine output control device 30 controls the speed of the motor for driving the pump from start to operation, issues a spark instruction to the spark plug, and controls the output of the gas turbine engine. Can be.

[0015]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIG. 1 taking an aircraft gas turbine engine as an example.

In FIG. 1, reference numeral 1 denotes an aircraft gas turbine engine, 2 denotes a turbine constituting the aircraft gas turbine engine 1, which generates a rotational force by an air flow to drive a compressor 3, and 4 denotes a compressor 3 This is a combustion chamber for burning a gas mixture of an air flow and a fuel generated by the above.

Reference numeral 5 denotes a synchronous machine which is directly connected to the turbine 2 shaft of the aircraft gas turbine engine 1 and operates as a starter generator. The synchronous motor 5 includes a main winding 5a, an igniter power supply winding 5b, and an engine output control device power supply. It comprises a winding 5c, a speed detecting winding 5d and a permanent magnet 5e.

The "start" side input terminal 6b of the switch 6 and the "operation" side input terminal 7a of the switch 7 are connected in parallel to the main winding 5a of the synchronous machine 5, respectively. The input terminal 7b is connected to the external AC power supply terminal 8 and the output terminal 7c of the switch 7.
, A converter 9 and an inverter 10 are connected in series.

A motor speed controller (automatic speed controller) for controlling the speed of the motor 12 for driving the fuel pump 11
A speed regulator 13 and a motor speed controller (automatic speed regulator) 16 for controlling the speed of a motor 15 for driving a lubricating oil pump 14
And a DC equipment power supply terminal 17 are respectively connected in parallel to the output terminal of the converter 9, and the fuel pump 11 is connected to a fuel nozzle 18 provided in the combustion chamber 4 of the aircraft gas turbine engine 1. The fuel pump 11 is connected via a pipe 19 so that fuel can be supplied to the fuel nozzle 18 by the fuel pump 11.

Further, an external DC power supply terminal 20 is connected to each input terminal of the inverter 10 and the motor speed control devices 13 and 16 via a switch 21, and the output terminal of the inverter 10 operates the switch 22. The output terminal 7c of the switch 7 is connected to the "start" side input terminal 22b of the switch 22, and the output terminal 22c of the switch 22 is connected to the AC equipment power supply terminal 23. 6 is connected to the “operation” side input terminal 22 a of the switch 22.

Further, an igniter power supply winding 5b of the synchronous machine 5 is connected to an igniter 25 for generating a spark from a spark plug 24 disposed in the combustion chamber 4 of the aircraft gas turbine engine 1. Thermometers 26 and 27 and a pressure gauge 2 are provided on the air inflow side and the air outflow side of the compressor 3 in the aircraft gas turbine engine 1.
8 and 29 are provided respectively, and these thermometers 26 and 2 are provided.
7 and the detected temperature value signal T and the detected pressure value signal P from the pressure gauges 28 and 29 are input to the engine output control device 30.

The engine output control device 30 comprises a microprocessor, a memory external input / output unit, and a power supply unit.
c and the output terminal 22c of the switch 22 to supply operating power.

The speed detecting winding 5d of the synchronous machine 5 is connected to the engine output control device 30 and the inverter 10 so that the detected rotational speed signal of the synchronous machine 5 is inputted and the engine output control is performed. The device 30 is connected to the igniter 25 so that a spark instruction of the spark plug 24 can be issued.

Further, an inverter 10 and motor speed controllers 13 and 16 are connected to the engine output control device 30, respectively. A motor speed instruction signal is input to each of the control signals 16, and switching operation sections of the switches 6, 7, and 22 are connected to the engine output control device 30. Thus, the switching operation of the switches 6, 7, 22 during start-up and operation is performed.

In the drawing, reference numeral 31 denotes an engine output control device 30.
This is an operation lever for outputting an engine power command signal to the control lever.

Next, the converter 9 and the inverter 10 will be described with reference to FIG.

The converter 9 combines a diode and converts the input from AC to DC and outputs it.

The inverter 10 converts the input from DC to AC by controlling the on / off operation of a plurality of switching transistors (six in the figure) by a switching control circuit 101 and outputs the converted signal.

The inverter 10 will be described in detail.
A voltage setter 102, an adder / subtractor 103, an amplifier 104, the switching control circuit 101, and a protection circuit 105 are connected in series, and the switching control circuit 101 appropriately turns on / off a switching transistor based on a set voltage value of the voltage setter 102. It operates so that a desired output (for example, three-phase 400 Hz AC voltage) is obtained,
An output-side voltage detector 106 and an output-side current detector 107 are connected to the protection circuit 105, and both detectors 10
When the detected voltage value and the detected current value from the switches 6 and 107 are equal to or larger than the set values (excessive voltage and excessive current), a signal is input from the protection circuit 105 to the switching control circuit 101 and the switching transistor is activated by a command from the switching control circuit 101 The output is adjusted by appropriately turning on and off to protect the output side device. Also, the output terminal of the output side voltage detector 106 is connected to the adder / subtractor 103, and the detected voltage value is fed back to the adder / subtractor 103 and compared with a set voltage value, and the difference signal from the adder / subtractor 103 is subjected to switching control. The switching operation of the circuit 101 is corrected so that the output voltage matches the set voltage. That is, it operates as an AC constant voltage device.

In the inverter 10, a speed setter 108, an adder / subtractor 109, and an amplifier 110 are connected in series, and a switch 111 for switching between a "start" mode and an "operation" mode by the engine output control device 30 is provided. The switching control circuit 101 is provided with an oscillator 112 having a required frequency (for example, 400 Hz) and the amplifier 11.
0 and the rotor (rotor) position converter 113 are connected to each other, and in the "start" mode (the state of FIG. 2), the amplifier 110 and the rotor position converter 113 are switched via the switch 111 and in the "operation" mode. Oscillator 1 via switch 111
12 are connected to the switching control circuit 101, respectively. Further, the synchronous machine 5 generates AC power having a frequency determined by the number of poles and the rotor rotational speed. The rotational speed change signal of the synchronous machine 5 is transmitted from the speed detecting winding 5d to the rotor position converter 113 and the speed-voltage converter 114. The rotor position caused by the change in the rotation speed of the synchronous machine 5 is detected by the rotor position converter 113 and sent to the switching control circuit 101 via the switch 111 as a frequency signal. The speed signal due to the speed change is converted into a voltage signal by the speed-voltage converter 114, and is added to the adder / subtractor 1.
09 and the speed setting unit 108
And a difference signal (a phase correction signal for leading and lagging the phase) from the amplifier 110 and the switch 111
To the switching control circuit 101, and corrects the switching operation of the switching control circuit 101.
That is, it operates as a speed control device of the synchronous machine 5. Further, the speed setting in the speed setting unit 108 may be performed by a speed command of the engine output control device 30 or a speed command of a worker.

As described above, the speed control of the synchronous machine 5 depends on which coil is excited by detecting the rotation angle of the rotor (rotor) of the synchronous machine 5; Excitation is performed at an angle (leading phase) that is more advanced than the position (position), and is excited at an angle (lagging phase) that is later than the rotor angle (position) of the synchronous machine 5 during deceleration. The speed setting device 10
8, the speed may be set so as to slowly change from 0 to the idle speed, or the speed may be set to the idle speed from the beginning. In the latter case, the synchronous machine 5 is operated at the maximum torque due to the current limitation. It is accelerated and becomes constant at the set speed. Further, when the synchronous machine 5 is at a low speed, the back electromotive force is small, and if it is left as it is, an excessive current flows from the inverter 10 to the synchronous machine 5. In this case, the output side current detector 107 The output current is detected and sent to the protection circuit 105, the switching operation of the switching control circuit 101 is corrected based on the output signal of the protection circuit 105, the output voltage of the inverter 10 is reduced, the output current is limited, and the Will be protected.

Hereinafter, the operation of the aircraft gas turbine engine 1 will be described.

First, the starting will be described.

The external AC power supply terminal 8 is connected to the external AC power supply, the operating lever 31 is advanced from the stop position to the idle operation position, and a required engine power instruction signal is output to the engine output control device 30. Device 30
Switches the switches 6, 7, 22 to the "start" side (state of FIG. 1). At this time, the AC power supplied to the external AC power supply terminal 8 is supplied to the engine output control device 30 via the switch 22 and serves as an operating power source for the engine output control device 30.

The AC power supplied to the external AC power supply terminal 8 reaches the converter 9 via the switch 7, and is converted from AC to DC by the converter 9, and is converted to DC by the inverter 10 and the switch 6. The synchronous machine 5 is sent to the main winding 5a, and the rotation speed is increased. Further, since the synchronous machine 5 is directly connected to the turbine 2 shaft of the aircraft gas turbine engine 1, the turbine 2 rotates integrally with the synchronous machine 5, and the rotation causes the air flow in the combustion chamber 4 to become the ignitable air flow. The engine output control device 30 sends a rotation speed instruction signal to the motor speed control device 13 from the engine output control device 30 based on input signals such as the detected pressure values of the pressure gauges 28 and 29 and the detected speed value of the speed detection winding 5 d of the synchronous machine 5. And the fuel pump 11 is appropriately driven to send the fuel to the fuel nozzle 18 via the pipe 19 and inject the fuel into the combustion chamber 4. On the other hand, the igniter 25
Is operable by the electric power from the igniter power supply winding 5b, and the spark plug 24 can be sparked at any time. The fuel is injected from the fuel nozzle 18 by an instruction signal based on the input signal to the engine output control device 30, and the instruction signal is sent to the igniter 25 to activate the spark plug 24 to generate a spark, so that the fuel injected from the fuel nozzle 18 is discharged. The fuel is ignited, the turbine 2 is accelerated by the combustion energy, and the aircraft gas turbine engine 1 is accelerated to the idling speed together with the rotational force of the synchronous machine 5. At this time, the instruction signal of the "start" mode is also sent from the engine output control device 30 to the inverter 10, so that the inverter 10 operates as the speed control device of the synchronous machine 5, and the synchronous machine 5 It is operating as. Further, a speed instruction signal of the motor 15 is also sent from the engine output control device 30 to the motor speed control device 16,
The lubricating oil pump 14 is appropriately driven to supply an appropriate amount of lubricating oil to a required location.

Next, the operation will be described.

When the rotation speeds of the turbine 2 and the compressor 3 of the aircraft gas turbine engine 1 increase and reach the idle speed, the idle speed is detected by the speed detection winding 5d of the synchronous machine 5, and the detected speed value Based on the signal, a switching instruction signal for switching from “start” to “operation” is sent from the engine output control device 30 to the switches 6, 7, 22 and the inverter 10. In this state, the synchronous machine 5 operates as a generator, and the electric power generated by the synchronous machine 5 changes in voltage and frequency due to a change in the rotation of the aircraft gas turbine engine 1. After that, the inverter 10 sets a constant voltage and a constant frequency.
The inverter 10 operates as an AC constant voltage device. If the synchronous machine 5 is provided with an emission voltage regulator and can change the exciting current, the voltage can be kept constant even if the rotation speed of the aircraft gas turbine engine 1 changes.
The DC device power supply terminal 17 can be used as a power source for the DC device of the airframe.

Normally, the DC power supply terminal 17 connected to the external DC power supply terminal 20 is connected to the DC power supply terminal 17 by turning on the switch 21 as shown in FIG. Can be used as a power source for DC devices. When the synchronous machine 5 operates as a generator, the synchronous machine 5 is connected to the AC equipment power supply terminal 23 via the switch 7, the converter 9, the inverter 10, and the switch 22 to connect the AC equipment power supply terminal 23 to the body. , And the DC device power supply terminal 17 can be used as a power source for the DC device of the body.

Further, the deceleration and stop of the aircraft gas turbine engine 1 are performed by setting the operation lever 31 to the stop position. The engine output control device 30 decelerates to the motor speed control device 13 based on the instruction signal of the operation lever 31,
A stop signal is sent, and the fuel nozzle 1
Fuel injection from 8 into combustion chamber 4 is slowly stopped, and aircraft gas turbine engine 1 is stopped.

The start of the aircraft gas turbine engine 1 was performed by connecting an external AC power supply to the external AC power supply terminal 8, but the external DC power supply was connected to the external DC power supply terminal 20 and the switch 21 was turned on. Then, the aircraft 10 may be started by converting the direct current into the alternating current by the inverter 10 and supplying power to the synchronous machine 5 through the switch 6.

It should be noted that the present invention is not limited to the embodiment shown and described. For example, a single-shaft aircraft gas turbine engine has been described. The power take-off shaft of the engine and the synchronous machine are connected to each other. The drive control of pumps other than the fuel pump and the lubricating oil pump is also performed by the instruction signal of the engine output control device. The operation is performed in the same manner as the pump.
That the operator switches between 7 and 22 in accordance with the rotation speed of the synchronous machine 5, and that the operator adopts a gas turbine engine used in automobiles and ships other than aircraft.
And the like are arbitrary, and it goes without saying that various changes can be made without departing from the gist of the present invention.

[0042]

As described above, according to the gas turbine engine operating device of the present invention, the following excellent effects can be obtained.

(I) In any of the first to third aspects of the present invention, since the synchronous machine is used, maintenance of the brushes and commutators is not required, and only maintenance of the mechanical parts (bearings) is required.
Since maintenance can be simplified and the shaft can be directly connected to the gas turbine engine shaft, there is no need to use a reduction gear mechanism, so that weight and wear parts can be reduced. It is adapted to the purpose of effective use of space.

(Ii) In any one of the first to third aspects of the present invention, since the converter and the inverter are used in combination, the external power source used when starting the gas turbine engine may be AC or DC, which is convenient. The starter and the generator can be used more efficiently than a system having dedicated converters and inverters.

(Iii) In any one of the first to third aspects of the present invention, various facilities using a gas turbine engine system (for example, land plant facilities, power generation facilities of a combination that collects and uses power, etc.), aircraft, ships, It can be applied to gas turbine engines in automobiles, etc., and is versatile.

(Iv) In any of the first to third aspects of the present invention, the hydraulic pump such as the fuel pump is driven by using the output of the synchronous machine instead of the output of the gas turbine engine. The reduction gear mechanism for driving the machine can be omitted to reduce the weight and the consumable part, and can be adapted to the purpose of reducing the weight and size of the gas turbine engine equipment and effectively utilizing the space. Can always discharge a required amount of pump, so that it is not necessary to recover the surplus fuel on the suction side as in the related art, and the energy efficiency can be improved.

(V) In the invention of claim 3, since the starter and the generator are automatically operated by the synchronous machine, the size of the gas turbine engine equipment can be reduced, and even when the power is cut off, the gas turbine engine can be operated. The control of the engine can be continued, and the reliability can be improved, and the efficiency of the gas turbine engine can be improved.

[Brief description of the drawings]

FIG. 1 is a circuit diagram of an operating device of a gas turbine engine according to the present invention.

FIG. 2 is a circuit diagram showing details of a converter and an inverter in the operating device of the gas turbine engine of the present invention.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Aircraft gas turbine engine 2 Turbine 3 Compressor 4 Combustion chamber 5 Synchronous machine 6, 7 Switch 8 External AC power supply terminal 9 Converter 10 Inverter 11 Fuel pump 12 Motor 13 Motor speed control device 18 Fuel nozzle 22 Switch 23 AC equipment power supply terminal 24 spark plug 25 igniter 30 engine output control device 31 operating lever

Claims (3)

(57) [Claims] A synchronous machine (5) directly connected to a shaft of a gas turbine engine, and a switch (5) connected to the synchronous machine (5) at start-up and switched to shut off the synchronous machine (5) during operation. 6) and a switch (7) for switching between the external power supply and the converter (9) at the time of starting and connecting the synchronous machine (5) and the converter (9) at the time of operation.
And an inverter (10) connected to the converter (9) and transmitting power from the external power supply to a synchronous machine (5) via a switch (6) at start-up. (9) An operating device for a gas turbine engine, wherein the pump is driven by an external power supply at the time of start-up and by a synchronous machine (5) at the time of operation. 2. A synchronous machine (5) directly connected to a shaft of a gas turbine engine, and a switch (5) which is connected to the synchronous machine (5) at the time of starting and which is switched off during operation of the synchronous machine (5). 6) and a switch (7) for switching between the external power supply and the converter (9) at the time of starting and connecting the synchronous machine (5) and the converter (9) at the time of operation.
And an inverter (10) connected to the converter (9) and transmitting power from the external power supply to the synchronous machine (5) via the switch (6) at the time of starting. The inverter (10) and the switch ( 22) and the AC equipment power supply terminal (23) are connected in series to operate the inverter (1) during operation.
0) and the AC equipment power supply terminal (23) are connected to the switch (2).
2) The connection is made by switching, and the pump driving motor is connected to the converter (9) so that the pump is driven by an external power source at the start and by the synchronous machine (5) at the time of operation. Characteristic gas turbine engine operating device. 3. A speed instruction to a pump driving motor based on a rotation speed of a synchronous machine (5), a pressure and a temperature of a gas turbine engine, an output power command, and the like;
The operating device for a gas turbine engine according to claim 1 or 2, further comprising an engine output control device (30) for outputting a spark instruction or the like to 4).