RU2592360C2 - Aircraft turbojet engine control method - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: control method of aircraft jet turbine engine (JTE) relates to aircraft engineering, namely to methods of control, optimizing parameters of JTE. During implementation of method maximum pressure in combustion chamber is additionally limited to P_{k. lim}, defined for each specific engine by full pressure after compressor, measured at engine bench tests of real atmospheric conditions, for which the preset pressure value P_{k. lim. prel.,} measuring with this mode total pressure after compressor P*_{k. meas.} and pressure in combustion chamber P_k, while restricting maximum pressure value in combustion chamber is determined by following relationship: P_{k. lim}=P_k+(P_{lim. allowable}-P*_{k meas.}), where P_{lim. allowable} is maximum tolerable pressure in combustion chamber.

EFFECT: method implementation allows to ensure safe operation of engine in all modes of operation.

1 cl

Description

The invention relates to methods for regulating an aircraft turbojet engine (turbojet engine), and in particular to methods of regulation that optimize the parameters of a turbojet engine.

A known method of regulating aircraft turbojet engines, including operational restrictions on the maximum values of the rotational speeds of low and high pressure rotors and gas temperatures at maximum engine operation. A combined control law of a two-shaft gas generator is possible, formed taking into account operational restrictions for the maximum mode of its operation (see Yu.N. Nechaev. Control laws and characteristics of aircraft power plants. M: Mashinostroenie, 1995, p. 253).

This method is not optimal from the point of view of safe operation of the turbojet engine due to the fact that it ensures the safe operation of high and low pressure rotors, but does not ensure the safe operation of the engine combustion chamber.

The objective of the invention is to increase the safety of the operation of the turbojet engine in all modes of its operation.

The expected technical result is achieved by the fact that in the known method for regulating an aircraft turbojet engine, including operational restrictions on the maximum values of the rotational frequencies of low and high pressure rotors and gas temperatures at the maximum engine operating mode, according to the invention, they further limit the maximum value of the pressure in the combustion chamber to P _{to. ogre} , the value of which is determined for each specific engine by the value of the total pressure behind the compressor, measured during bench tests of the engine in real atmospheric conditions, for which a pressure value P _{k. ogre is} pre-set _{. anticipating} below the value of the total pressure behind the compressor at maximum mode, the engine is driven out in accordance with the rotational speed from the idle mode until the engine operation mode is limited to P _{K. anticipating} that in this mode the total pressure behind the compressor R * _{k is} measured _{. ism} and the pressure in the combustion chamber R _k , and the limit value of the maximum pressure in the combustion chamber is determined by the following relationship:

P _{to. Ogre} = P _to + (P _{previous add.} -P * _{to. Meas.} ),

where P _{before. add} - the maximum allowable pressure in the combustion chamber, and enter it into the engine controller.

The invention consists in ensuring operational safety of aeronautical turbojet by further limiting the maximum pressure in the combustion chamber P _{k. Res.}

The method of regulation of an aircraft turbojet engine is implemented as follows.

When conducting tests on the ground bench in the "low gas" mode in the engine regulator preset the limiter R _{K. ogre. anticipated} 1.5 kg / cm ² lower than the total pressure behind the compressor at maximum speed under specific atmospheric conditions. For example, at maximum operation under specific atmospheric conditions, the total pressure behind the compressor is 19 kg / cm ² . Enter in the controller the value of P _{to ogre. Pre} = 19-1,5 = 17.5 kg / cm ^2.

Further, by smoothly increasing the engine operating mode, it is withdrawn before the engine operating mode is limited. In this mode, measure the total pressure behind the compressor R * _{k. Ism} = 19 and the pressure P _k = 18.5 by the sensor of the engine regulator. Further according to the formula

P _{K. ogre} = P _to + (P _{previous add.} -P * _to. Meas _. ) = 18.5 + (38-19) = 37.5 kg / cm ² determine the setting of the maximum pressure limiter in the combustion chamber and enter it into the engine regulator.

The implementation of the invention will provide increased reliability of aviation turbojet engines.

Claims (1)

A method for regulating an aircraft turbojet engine, including operational restrictions on the maximum rotational speeds of low and high pressure rotors and gas temperatures at the maximum engine operating mode, characterized in that they further limit the maximum value of the pressure in the combustion chamber to P _K. a specific engine by the value of the total pressure behind the compressor, measured during bench tests of the engine in real atmospheric conditions x, for which the pre-set pressure value P _{k. Res. anticipating} below the value of the total pressure behind the compressor at maximum speed, the engine is driven out in accordance with the rotational speed from the idle mode until the engine operation limits are limited to P _{K. before} that, in this mode, the total pressure behind the compressor P * _{k is} measured _{. ism} and the pressure in the combustion chamber P _k , and the limit value of the maximum pressure in the combustion chamber is determined by the following dependence:
P _{to. Ogre} = P _to + (P _{previous add.} -P * _{to. Meas.} ),
where P _{prev. add} - the maximum permissible pressure in the combustion chamber.