SU1114142A1 - Method of determining power of gas-turbine engine of gas-pumping plant - Google Patents

Abstract

METHOD FOR DETERMINING THE POWER OF A GAS TURBINE ENGINE OF A GAS-LINE-RELATED AGGREGATE UNIT IN THE PROCESS OF HIS GAS-RING, INCLUDING THE PRESSURE AND TEMPERATURE OF THE ENTRY INTO THE ENGINE AND THE TWO OF CHARACTERISTICS OF THE INPUT AND CURRENT OPERATING TIMES OF THE OPERATION AND THE DEFINITION OF THE LOW CURRENT INPUT AND TABLE and with the fact that, in order to increase the accuracy, as the characteristic parameters, the rotational speed of the rotor of the engine compressor and the static air pressure behind the compressor are chosen, the measurement of all parameters the current moment of operation is carried out at the value of the reduced rotation frequency of the rotor, which is equal to its value at the initial moment, and the coefficient of power loss from the equation is determined (liPlysz./PiiL lllPK.TftK / Pu.taU 1 - s / PH "WITH). - gas-dynamic coefficient; Where with a rate equal to 1.6-2; Рл Р., And accordingly the pressure “tech” is from the air behind the compressor in the initial and current moments of operation ;: 4: wW PU And, respectively, the pressure of the air inlet, at the entrance to the engine 4 IN :) the body is in the same moments. .

Description

The invention relates to gas turbine engines (GTE), in particular to GGDs operating as part of a gas pumping unit (HPA) of main gas pipelines.

It is known that during the operation of gas turbine engines as part of gas compressor units in ground conditions, due to the dustiness of the environment, there is a fairly intensive pollution of the air path of the compressor, as a result of which the operational characteristics of the gas turbine unit deteriorate: the power decreases, the specific fuel consumption of the HGD increases. With the duration of operation, a change in the geometric size of the flow part of the digester can also occur, which will affect its operation characteristics. In practice, the maintenance of the level of characteristics is ensured by periodic washing and cleaning of the flow path of the CCD. In order to maintain the 4th performance of the CCD at the proper level, it is necessary to periodically evaluate its output parameters - power, fuel gas consumption. A known method for determining the power of a gas turbine installation is by measuring the indirect parameters of the gas temperature before and after the low pressure turbine, the flow rate of the working fluid through the installation and the power of the turbocharger obtained by calculation. The known method is relatively labor intensive due to the need to measure a large number of parameters and to conduct a large number of tests. The closest to the description is the method for determining the power of the gas turbine engine of the gas pumping unit during its operation, including measuring the pressure and air temperature at the engine inlet and two other characteristic parameters at the initial and current excursion points and determining the power loss coefficient from them. The disadvantage of the method is low accuracy due to non-observance of the engine (5 and engine operating modes at initial and current operating moments. The aim of the invention is to improve the accuracy of determining power pressure and air temperature at the engine inlet and two other characteristic parameters at the initial and current moments of operation and determining the power loss factor from them and, as characteristic parameters, choose the rotor speed of the compressor rotor and the static air pressure behind the compressor, measure all parameters currently in operation at a value of the reduced frequency of the rotor rotation equal to its initial value, and determine the coefficient K, power losses from CPi4pji / E m iziEtm 5i-rfiKil L (РКИС. / РИИСХ 1 J - gas-dynamic coefficient equal to 1.6-2; Ktek - air pressure behind the compressor at the original and current operating times; R., and R. .. - respectively, the pressure is the source of air flow at the engine inlet - the same points. The value of the coefficient C depends on the hydraulic losses in the input and output devices ITEA to the characteristics of the power turbine. The performance of HPA of various designs differs in hydraulic resistances, determined by the presence of air cleaning devices on the engine inlet and on exhaust regenerator installations, a silencer, etc. For the specific HPA performed, the non-value of the coefficient C is constant, so it can be determined with the release of the first copies of gas pumping units of this series. As the statistics of the determination of the coefficient C of individual gas pumping units GPU-Ts-6.3 shows, the spread of the value of C does not exceed 2%. The error in estimating the change in power in this case is 0.4%, which is quite acceptable. This greatly simplifies the method of determining the operational loss of power and reduces its labor intensity. The gas-dynamic coefficient C is determined as follows. At the steady state operation of the gas-pumping unit, the reduced frequency of the rotating roto, p. ra compressor (-.t), where n - the rotor speed; Tj, - air temperature at the engine inlet, static air pressure P behind the compressor, air pressure Pf at the engine inlet and the ratio pt - total gas pressures at the inlet and outlet of the power turbine, after which the operating mode j is changed; 3-5 % over reduced rotation frequency

values, measure the static air pressure behind the compressor and the ratio iiTg of the total gas pressures at the inlet and outlet of the power turbine and calculate the coefficient C using the formula

T4

Г „I 1 -. 4 Kg OuKg-1,, PH.

t к, - - р- ;; ,, one

where K is the adiabatic coefficient of fuel combustion products, K is 1.33; IT - the value of the relationship full

gas pressure at the inlet and outlet of the power turbine at

/ n St),; H n

P c - the value of the static air pressure behind the compressor

with (J.-) ,;

ii-j- - the value of the relationship full

gas pressures at the inlet and at the outlet of the power turbine, measured with a change in the GTE operating mode in terms of the rotor speed of the compressor, i.e. at (-n; t-), otliN- Hi - ..

from +J-ST + 3-5% STn

P y - the value of the static air pressure behind the compressor measured when changing the GTE operating mode according to the frequency of rotation of the compressor;

, P . . i.e. with (-rfT) 2

1 N

The dependence presented by which the determination of the operational loss of GTE power is made, and the parameters included in it, are determined on the basis of a structural analysis of the system of equations describing the operation of the GTE using the small deviation method.

The drawing shows schematically a gas turbine gas pumping unit.

The gas turbine gas pumping unit contains an input guide unit 1 of compressor 2, a fuel gas supply line 3, a combustion chamber 4, a compressor drive turbine 5, a compressor drive power turbine 6 and an exhaust device 8 of the unit.

At the outlet of the compressor 2, in the zone of secondary air, which flushes the combustion chamber 4, holes are drilled evenly around the circumference, which go to the collector 9, averaging static pressure, measured by a pressure gauge 10.

ten

I

On the rotor of the compressor 2, a rotational speed meter 1I is installed, for example, an electro-tachometer.

In the gas path of the HPA power turbine, before the power turbine stage 6, a full gas pressure sensor 12, such as a pneumo-grab box, is installed, and a full-pressure sensor 13 is connected to the full-pressure gauge 14 behind the power turbine. The number of sensors and their installation are determined by the level of uniformity of the pressure field by

5 flow parts.

The method is carried out as follows.

At the initial moment of operation of the unit at the exit to the stationary Q with a ream, record the value of temperature and air pressure at the engine inlet, rotation frequency of the compressor rotor according to meter 11, static air pressure behind the compressor with a pressure gauge 10.

5 If it is necessary to determine the power at the current time of operation, by changing the flow rate of the fuel gas, it is set to measure II s. volume of air

0 in the engine, the value of the given rotational speed, equal to the value at the initial moment of operation. After that, the static pressure is measured according to the reading of the pressure gauge 10 and

5 coefficient of power loss at the current time with accounting of changes in air pressure at the engine inlet according to the formula

0 / lEji.-PjliejL

.L2 "te1 j

Ke 1 - Cf

..,

HHCK /

Coefficient C is calculated from the measurement data of the ratio of total pressures.

5 gas meter 14 and static pressure. Air after the compressor pressure gauge 10 taking into account the atmospheric pressure by the formula

WITH

 one.

i, t. „

Pk.- Guy

K, R.

Measurement of the ratio of the total pressures on the power turbine and the static pressures behind the compressor to determine the coefficient C is carried out with the release of the first copies of gas pumping units of this series. If necessary, the coefficient C can be determined on a specific unit in the current operation.

As shown by the experimental

The study of a large number of gas turbine engines, the proposed method for determining the power by input indirect parameters due to its objectivity and regularity of relations between the parameters, as well as compliance with similar modes of operation, provides a high degree of accuracy.

The dampings in the K coefficients, determined by the proposed method and calculated from the values of power measured directly on the CCD in the range of power change up to 15%, air pressure behind the compressor up to 8%, air consumption up to 6% 5%, did not exceed 1%. The proposed method is simpler, reduces labor intensity, expands the range of applicability and allows for regular monitoring of the technical condition of the units during operation and the quality of commercially produced gas turbine engines for gas-rectifying units.

Claims (1)

METHOD FOR DETERMINING THE POWER OF A GAS TURBINE ENGINE OF A GAS PUMPING UNIT during its operation, including measuring the pressure and air temperature at the engine inlet and two other characteristic parameters at the initial and current operating times and determining the power loss coefficient based on them In order to increase the accuracy, we select as the characteristic parameters the rotational speed of the rotor of the engine compressor and the static air pressure behind the compressor, measuring all the parameters in the current moment of operation is carried out at a value of the reduced frequency of rotation of the rotor equal to its value at the initial moment, and the coefficient of power loss is determined from the equation to ₅ = 1 - С where С R, and Rl Hiskh ^Kt ek L (Rkiskh / _uc Ph p 1 + r gasdynamic factor of 1.6-2, respectively, the air pressure of the compressor at the starting points and the current operation; ^ ^W Descending Ktek ^{wo '1' ve 'gstvenno} air pressure at the inlet into the engine at the same moments.