RU2612663C9 - Gas turbine engine operation - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: gas pressure is measured at compressor outlet, pressure and rotor speed are used as a comparison parameter, measurements are performed at a constant turbine outlet temperature at intervals of 0.2…0.5 s, measurement comparison and threshold determination of deviations are made by at least two preceding and two subsequent actual parameter values, the engine stop is carried out at 0.2…0.5 per cent decrease in rotor speed and at 1.0…1.5 per cent decrease in compressor discharge pressure.

EFFECT: prevention of the destruction of gas-air engine flow duct caused by various factors during the gas turbine engine operation at the ground-based installation.

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Description

The invention relates to the field of operation of gas turbine engines, in particular to engines used as a drive for gas pumping units and power plants.

The closest in technical essence and the achieved result is the well-known method of operating a gas turbine engine, which includes determining at the beginning of operation during acceptance tests the initial values of the gas temperature behind the turbine, gas pressure and rotor speed and determining acceptable threshold deviations from the initial values, and at operation periodically measuring the temperature, pressure and rotor speed of the engine rotor, comparing the measured and initial values and p adjusting the rotor speed or stopping it depending on the results of comparing measurements and threshold deviations.

/ RU No. 2168163 MPK7 G01M 15/00, publ. May 27, 2001 / / 1 /

However, this method does not allow to timely determine the beginning of the destruction of the elements of the gas-air path, which under the operating conditions of the gas turbine engine leads to significant damage to the engine elements.

The objective of the invention is to develop a method for the effective protection of the engine during operation and minimize damage.

The expected technical result is the assessment of the destruction of one or more engine components, the adoption of preventive measures to stop the gas turbine engine before significant damage is manifested.

The expected technical result is achieved by the fact that in the known method of operating a gas turbine engine, which includes determining at the beginning of operation during acceptance tests the initial values of the gas temperature behind the turbine, gas pressure and rotor speed and determining acceptable threshold deviations from the initial values, and when operation periodically measuring the temperature, pressure and rotor speed of the motor rotor, comparing the measured and initial values and frequency regulation If the rotor rotates or stops depending on the results of comparing measurements and threshold deviations, according to the proposal, the gas pressure is measured behind the compressor, the pressure and rotor speed are used as a comparison parameter, measurements are made at a constant gas temperature behind the turbine at time intervals of 0.2 ... 0.5 s, comparison of measurements and determination of threshold deviations is carried out using at least two previous and two subsequent current values of the parameters, and the engine is stopped at reducing the rotor speed by 0.2 ... 0.5% and the pressure behind the compressor by 1.0 ... 1.5%.

The invention proposes, additionally periodically, at each time interval of 0.2 ... 0.5 s, to measure the pressure behind the high-pressure compressor P _k , and as a comparison parameter it is proposed to use this pressure and rotor speed. If the deviation of the values of the measured parameters is below the acceptable threshold deviations from the initial values, then a smooth, for example fuel consumption, regulation of the rotor speed is carried out and the engine continues to operate. The measurement time interval of 0.2 ... 0.5 s is optimal, allowing you to objectively assess the condition of the engine and take preventive measures. If a decrease in rotor speed by 0.2 ... 0.5% and pressure behind the compressor by 1.0 ... 1.5%, including within the range of threshold deviations of other parameters, is detected during the measured period of time, the engine is stopped, which eliminates its significant damage.

The drawing shows a gas turbine engine installed in a gas pumping unit or power plant with a connected control system that implements the proposed method.

The gas turbine engine 1 includes: a compressor 2 (including a low and high pressure compressor), a turbine 3 (including a low and high pressure turbine), a free (power) turbine 4. To implement the proposed method, the change in pressure is controlled by the compressor P _to and rotor speeds relative to previous values.

Example

Before starting operation of the gas turbine engine 1, a measurement of its basic (initial) characteristics is carried out, including the determination of the initial pressure P _k behind the compressor 2 and the initial rotation frequencies. In the process of operation, measurements are carried out at each time interval of 0.2 ... 0.5 s, the pressure P _k and the rotational speeds of the rotors are checked, and their values are compared with two ... three previous values. By reducing the pressure P _to the compressor 2 by the amount of 1 ... 1.5% with simultaneous reduction of the rotational speed of the rotors in a 0.2 ... 0.5% ... with respect to two three preceding values in the absence of a control signal to change the engine operating condition signal producing formation of changes in the technical condition of the engine and subsequent engine shutdown.

The implementation of the invention allows to prevent the development of the destruction of the gas-air path of the engine caused by various reasons (improper operation, damage to the working blades, etc.) when operating a gas turbine engine in a ground installation. It allows you to reduce the cost of engine repair by timely stopping and, thereby, preventing the development of damage in the gas duct and engine systems.

Claims (1)

A method of operating a gas turbine engine, including determining at the beginning of operation during acceptance tests the initial values of the gas temperature behind the turbine, gas pressure and rotor speed and determining acceptable threshold deviations from the initial values, and during operation, periodically measuring temperature, pressure and speed rotor of the engine, comparing the measured and initial values and regulating the rotor speed or stopping it depending on the results of measurement measurements and threshold deviations, characterized in that the gas pressure is measured behind the compressor, the pressure and rotor speed are used as a comparison parameter, measurements are made at a constant gas temperature behind the turbine at time intervals of 0.2 ... 0.5 s, and measurements are compared and determination of threshold deviations is carried out according to at least two previous and two subsequent current parameter values, and the engine is stopped when the rotor speed is reduced by 0.2 ... 0.5% and the pressure per computer spring by 1.0 ... 1.5%.

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