RU2696516C1 - Control method of two-shaft gas turbine engine with adjustable guide vanes of compressor and fan - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engine building, namely, to control of two-shaft gas turbine engine with adjustable guide vanes. Method of control of two-shaft gas turbine engine with adjustable guide vanes of compressor and fan includes control of low and high pressure rotors rotation speed by changing fuel flow to main combustion chamber, regulation of guiding devices position by signal from position sensor of guiding devices of corresponding rotor. At the same time prior to operation of the engine, setting the rotor rpm ratio for each engine operating mode, further in the course of engine operation in case of absence of signal from position sensor of guide vanes of one of rotors, rotation frequency of this rotor is controlled by action on speed of its guiding devices movement proceeding from previously set ratio of rotor rotational speeds.

EFFECT: higher reliability of engine control system without additional redundancy of guide vanes position sensors.

1 cl, 1 dwg

Description

The invention relates to aircraft engine construction, namely to the control of a twin-shaft gas turbine engine with adjustable guide vanes.

A known method of controlling the position of the rotary guide vanes of a compressor of a gas turbine engine (patent RU 115832 U1, IPC F02C 9/00, 12/14/2011).

The disadvantages of this method is that in case of loss of information about the actual position of the guide vanes, for example, when position sensors fail, the positioning of the guide vanes becomes impossible, which can lead to surging of the engine and, as a result, to an emergency.

The technical result achieved by using the claimed invention is to increase the reliability of the engine control system without additional redundancy of the position sensors of the guide vanes.

The specified technical result is achieved by the fact that in the method of controlling a twin-shaft gas turbine engine with adjustable compressor and fan guides, including controlling the rotational speed of low and high pressure rotors by changing the fuel consumption in the main combustion chamber, adjusting the position of the guide vanes by a signal from the sensor of the position of the guide vanes the corresponding rotor, while before starting the operation of the engine establish the ratio of the reduced frequencies BP rotors for each operating mode of the engine, then during engine operation in the absence of a signal from the position sensor of the guide vanes of one of the rotors, the regulation of the rotor with a serviceable position sensor of the guide vanes is continued by changing the fuel consumption in the main combustion chamber, and the rotor with a faulty guide position sensor apparatuses regulate the impact on the installation angle of its guide apparatuses based on the previously established ratio of the given rotational speeds of the rotors.

The control method is based on the fact that the position of the guide vanes uniquely determines the ratio of the reduced rotational speeds of the rotors of the twin-shaft engine, and therefore the ratio between the reduced rotational frequencies of the low pressure rotors (n1пп) and high pressure (n2пр) n1пp = f (n2пp) at steady-state engine operation is achieved only if the guiding devices are set to the position specified by the programs n2nр = f (α2ad) or n1pr = f (α1ad), where α1ad and α2ad are the preset values of the position of the guiding devices Suspension high and low pressure respectively. To implement the relation n1пp = f (n2пp), the rotational speed of one of the rotors is supported by influencing the fuel consumption in the combustion chamber, and the rotational speed of the other rotor is supported by increasing / decreasing the mismatch of the speed of movement of the actuator of the guiding apparatus of the compressor of the integrating type (for example, hydraulic cylinder), by increasing / decreasing the control action on the actuator.

The essence of the claimed invention is illustrated in FIG. 1 diagram of a control system for a twin-shaft gas turbine engine with adjustable guide vanes of the compressor and fan, through which the claimed method can be implemented.

The control system of a twin-shaft gas turbine engine with adjustable guide vanes of the compressor and fan is equipped with sensors for measuring its operation parameters, measured value adjusters, and gas-turbine engine parameters regulators:

1. The adjuster of the frequency of rotation of the high pressure rotor (RVD)

2. The first adder

3. The speed controller

4. Fuel dispenser

5. The speed sensor RV D

6. Engine air temperature sensor

7. The sensor rotational speed of the low pressure rotor (RND)

8. The position sensor of the guiding apparatus of the low pressure compressor (ON KND)

9. FP - functional converter

10. The first block division

11. The second block division

12. The adjuster of the rotational speed of the low pressure rotor (RND)

13. The second adder

14. PD - regulator of the reduced rotor speed of the low pressure rotor

15. Switch

16. The executive mechanism of MI on KND integrating type

17. Diagnostic unit

18. Position adjuster ON KND

19. Summing amplifier

20. Engine

The system works as follows:

Depending on the position of the ORE (not shown in Fig. 1), the setpoint (1) of the high-pressure rotor rotational speed (RVD) generates a preset value of the rotational speed of the high-pressure rotor, in the first adder (2) the difference between the setpoint (1) value and the value of the speed of the high pressure hoses from the sensor (5). The value calculated by the first adder (2) is fed to the input of the high-pressure rotor speed controller (3), which generates the required fuel consumption in the engine to maintain the high-speed rotor speed set by the master (1). The output signal of the high-pressure rotor speed controller (3) is fed to the input of the fuel dispenser (4), which provides fuel to the combustion chamber of the engine (20).

The position of the RND guiding devices can be controlled by one of two programs formed by the setters (12) and (18).

The position program α1set = f (n1pr) formed by the setter (18), depending on the reduced rotational speed of the low pressure rotor, is executed with a working position sensor (8). The program of the rotational speed of the low pressure rotor formed by the setter (12) according to the reduced frequency of rotation (n1пp = f (n2пp)) is executed when the sensor (8) of the position on the low pressure switch is faulty.

The signal from the air temperature sensor (6) at the engine inlet is fed to a functional converter (FP) (9), the output signal of which (reduction coefficient) is fed to the input of the division unit (11) as a divider, and as a divisible input to the block (11) ) a signal is sent from the sensor (7) of the rotational speed of the low pressure rotor.

The output signal of the unit (11) is the reduced frequency of rotation of the low-pressure rotor, which is fed to the input of the adjuster (18) of the position of the guides of the low-pressure compressor (ON KND). The input of the summing amplifier (19) is supplied with the output of the setter (18) and a signal from the sensor (8) of the position of the guide vanes of the low-pressure compressor. The output of the summing amplifier (19) is the control signal of the guides of the low-pressure compressor.

The signal from the temperature sensor (6) at the engine inlet is fed to a functional converter (FP) (9), the output signal of which (reduction coefficient) is supplied as a divider to the input of the division unit (10), and the signal from the sensor (5) of the rotor speed high pressure acts as a dividend at the input of the division unit (10). The output signal from block (10) (reduced frequency of rotation of the high pressure rotor) is an input signal to block (12) for generating the programmed value of the frequency of rotation of the low pressure rotor, which generates a set value of the frequency of rotation of the low pressure rotor as:

n1pr (back) = f (n2pr)

where n1pr (back) is the set value of the rotational speed of the low pressure rotor,

n2pr = n2 / √ (TVX / 288) - reduced frequency of rotation of the high-pressure rotor,

Tvh - air temperature at the engine inlet.

The second adder (13) generates the difference specified by the setter (12) and formed by the divider (11) of the values of the reduced speed of the RND. This difference is fed to the input of the PD controller (14) of the reduced rotation speed of the low pressure rotor, the output signal of which determines the speed of movement of the guide vanes. The signal from the PD controller (14) of the reduced speed of the low pressure rotor is fed to the input of the switch (15) located in the regulation position by the backup control regulator of the guides of the low pressure compressor, and then the signal from the PD controller (14) of the reduced speed of the low pressure rotor is received to the actuator (16) of the guide vanes of the low-pressure compressor providing movement of the guide vanes of the low-pressure compressor.

The choice of the control program for the guiding devices is carried out by the switch (15). At the first input of the switch, the output signal of the PD controller (14) of the reduced frequency of rotation of the low pressure rotor is received, at the second input, the output of the summing amplifier (19). The amplifier is made with a high gain that provides quick positioning of the guide devices in the position set by the setter (18). The output of the diagnostic unit (17) is a logic signal of the sensor failure (8) of the position of the guide vanes of the low-pressure compressor. This signal is equal to zero with a working position sensor, and one when a failure is detected. The output of the diagnostic unit (17) is fed to the control input of the switch (15), which, when the signal is zero, connects the output of the adder (18) to the actuator, and if the signal is single, the output of the PD regulator (14) of the reduced rotor speed of the low pressure.

When using the actuator of the guiding apparatus of the low-pressure compressor of an integrating type, for example, a hydraulic cylinder, the speed of movement of the actuator is proportional to the input control signal.

Moreover, the larger the mismatch, the greater the speed of movement of the actuator, respectively increasing or decreasing the magnitude of the control action on said actuator.

If the actual reduced speed exceeds a predetermined value, the PD controller (14) of the reduced speed of the low-pressure rotor generates a signal to open the guide vanes, as a result, the power consumed by the low-pressure compressor increases at a practically constant flow rate of the high-pressure rotor (1) fuel. When the difference between the program and actual values decreases, the speed of movement of the actuator decreases proportionally. Due to this, a smooth approach to the equilibrium value of the rotational speed is achieved, and, as a result, the stability of regulation. Thus, stable maintenance of a given engine operating mode in a failure situation is ensured.

Claims (1)

A method of controlling a twin-shaft gas turbine engine with adjustable compressor and fan guiding apparatus, comprising controlling the rotational speed of low and high pressure rotors by changing the fuel consumption in the main combustion chamber, adjusting the position of the guiding apparatuses by a signal from the position sensor of the guiding apparatuses of the corresponding rotor, characterized in that up to the start of operation of the engine establish the ratio of the reduced rotational speeds of the rotors for each operating mode tor, then during engine operation in the absence of a signal from the position sensor of the guide vanes of one rotor rotation frequency of the rotor is adjusted to influence its speed of movement of the guide vanes on the basis of a previously set ratio given rotor speed.

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