RU2348824C2 - Method for control of gas turbine engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention is related to the field of aviation propulsion engineering and may be used in electronic-hydromechanical systems (automatic control systems - ACS) for gas turbine engine (GTE) automatic control. Substance of invention consists in the fact hat frequency of engine rotor rotation is additionally measured and controlled, and if rotational frequency exceeds previously set value, command is generated, and control action of electronic control is blocked with the help of selector, and control action of hydromechanical control is sent to final control element, and engine is controlled from hydromechanical control.

EFFECT: higher reliability of ACS operation and, accordingly, higher reliability of GTE and safety of aircraft.

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Description

The invention relates to the field of aircraft engine manufacturing and can be used in electronic hydromechanical systems (ACS) for automatic control of gas turbine engines (GTE).

A known method of controlling a gas turbine engine implemented in an electronic hydromechanical self-propelled guns of a supervisory type (Keba I.V. Flight operation of a helicopter gas turbine engine, Moscow, Transport, 1976). The method consists in the fact that in order to improve control accuracy, the control action of the hydromechanical controller is adjusted in a limited range by an electronic corrector.

The disadvantage of this method is its low efficiency.

Closest to this invention by technical essence is a gas turbine engine control method implemented, for example, in an electronic-hydromechanical self-propelled guns of the TV7-117 engine, included in the power plant (SU) of the Il-114 aircraft (Operation manual for the TV7-117C engine, LNPO im. V.Ya. Klimova, Leningrad, 1988).

ACS contains an electronic regulator (ER), a backup hydromechanical regulator (GMR), a selector and a block of actuating elements (IE).

The method consists in the fact that in the ER with the help of ER sensors, the position of the engine control lever (ORE) and the SU parameters are measured, depending on the position of the ORE and the values of the SU parameters according to the laws of control implemented in the ER, the control action of the ER is formed in GMP with GMR sensors measure the position of the ore and the parameters of the SU, depending on the position of the ore and the values of the parameters of the SU according to the laws of control implemented in GMR, form the control action of the GMR, with a good ER using the selector, cut off the control effect of the GMR, and the control action of the ER is fed to the IE and the engine is controlled, if the ER fails, the control action of the ER is cut off with the help of the selector, and the control action of the GMR is fed to the IE and the engine is controlled.

The disadvantage of this method is the following.

The health of the ER is controlled by the integrated control unit (IAC). The effectiveness of IACs, although very high (the probability of failure detection in modern self-propelled guns with built-in monitoring tools is not lower than 0.99), but allows:

- occurrence and non-detection of single failures (undetected failures);

- unpaired two or more failures that occur simultaneously (non-localized failures).

These so-called undetected or non-localized ER failures have different effects on the performance of the controller itself, and through it on the engine's performance and the safety of the aircraft.

For example, uncontrolled failure of a computer that is the core of any modern ER (for example, a failure that makes it impossible to start the next cycle of ER operation after the previous one) can lead to serious (even catastrophic) consequences. Similar consequences can have a double failure, consisting in the simultaneous failure of the ER, requiring the transfer of control to GMR, and the failure of the selector (for example, the failure of the mechanical part of the electromagnet controlling the selector valve).

The aim of the invention is to increase the reliability of the ACS and, as a result, increase the reliability of the gas turbine engine and the safety of the aircraft.

This goal is achieved by the fact that in the method of controlling a gas turbine engine, which consists in the fact that in the electronic controller (ER) using the ER sensors measure the position of the lever (ORE) of the engine control and the parameters of the power plant (SU), depending on the position of the ORE and the value CS parameters according to the control laws implemented in the ER, form the control action of the ER, in the hydromechanical regulator (GMR) using GMR sensors measure the position of the ore and the parameters of the control system, depending on the position of the control system and the value of the control parameters On the control laws implemented in the GMP, the control action of the GMP is formed, with a working ER, the control action of the GMP is cut off with the help of a selector, and the control action of the ER is fed to the block of actuating elements (IE) and the engine is controlled, and the rotor speed of the engine is additionally measured and controlled, if the rotation speed exceeds the predetermined value in advance, a command is formed and, with the help of the selector, the control action of the ER is cut off, and the control action of the GMP is fed to the IE and the control The pressure from the engine GMR.

The drawing shows a diagram of a device that implements the inventive method.

The device contains series-connected first block 1 of sensors (DB), electronic controller 2 (ER), selector 3 "electronics - hydromechanics", block 4 actuators (IE), serially connected second block 5 of sensors, hydromechanical controller 6 (GMP), output which is connected to the selector 3, the built-in control unit (BVC) 7, the output of which is connected to the controlled input of the selector 3, the comparison device 8, the input of which is connected to the output of the DB 5, and the output to the input of the selector 3.

The device operates as follows. The electronic controller 2, based on the signals from the sensors from block 1, according to well-known dependences (see, for example, Shlyakhtenko S.M. Theory of dual-circuit turbojet engines, Moscow, Mechanical Engineering, 1979) generates a control action on IE 4, which carry out the required changes in the fuel consumption in the engine combustion chamber , the position of the blades of the inlet guide vane (VNA) of the compressor and valves (KPV) air bypass.

The performance of ER 2 is evaluated by BVK 12 according to well-known principles (see, for example, Bodler V.A. et al. Automatic control systems for aircraft engines, Moscow, Mechanical Engineering, 1973).

With a working ER 2, the selector 3 is in the “electronics” position and passes control commands of the ER 2 to the IE block 4.

In case of failure of the ER 2 element, or the sensor from block 1, or IE 4 detected by the BVK 7, by the command of the BVK 7, the selector 3 is shifted to the "hydromechanics" position and the engine control is transferred to GMP 6.

Regardless of the operation of ER 2 and BVK 7, additionally, in the comparison device 8, the rotor speed of the engine is constantly monitored: when the set value is exceeded in advance, a hydraulic command is generated at the output of device 8, by which the selector 3 is shifted to the "hydromechanics" position, and the engine control is transferred to GMP 6 regardless of the output of the BVK 7.

Thus, improving the quality of work of self-propelled guns and, as a result, improving the reliability of gas turbine engines and the safety of aircraft is ensured.

Claims (1)

The method of controlling a gas turbine engine, which consists in the fact that in the electronic controller (ER) using the ER sensors, the position of the engine control lever (ORE) and the power plant (SU) parameters are measured, depending on the position of the ORE and the value of the SU parameters according to the control laws implemented in the ER, the control action of the ER is formed, in the hydromechanical controller (GMR) using the GMR sensors measure the position of the ore and the parameters of the control system, depending on the position of the ore and the value of the control parameters according to the laws of control implemented in GMP form the control action of the GMR, with a working ER, the control action of the GMR is cut off with the help of a selector, and the control action of the ER is fed to the block of actuating elements (IE) and the engine is controlled, characterized in that they additionally measure and control the rotor speed of the engine rotor, if the rotational speed exceeds the predetermined value in advance, form a command and, using the selector, cut off the control action of the ER, and the control action of the GMP is fed to the IE and control the engine from GMP.