KR20050008975A - Method for Yielding Capacity Data of Gas Turbin - Google Patents

Abstract

PURPOSE: A method for calculating/graphing data to measure performance of a gas turbine is provided to precisely and easily analyzing the performance of the gas turbine by determining conditions of each part of a compressor, a combustor, and the gas turbine based on weather data and site elevation information, and calculating/graphing the data to measure the performance based on the conditions. CONSTITUTION: The site elevation information and the weather data are inputted(S301). A combustion ratio of the air and fuel is determined by analyzing a fuel and composition of the fuel(S302). A pressure loss of the air at a compressor inlet and the pressure loss of the gas at a turbine outlet are determined by using stored pressure loss data of each model(S303). A modified air temperature, which is the air temperature at a site elevation, is calculated by using the site elevation information and the weather data(S304). The pressure at the compressor inlet is calculated by using the air pressure, the pressure loss at the compressor inlet, and the modified air temperature(S305). A wet air pressure of the air temperature is calculated by using a saturated pressure and the site elevation(S306).

Description

Method for Yielding Performance Data of Gas Turbine {Method for Yielding Capacity Data of Gas Turbin}

The present invention relates to a method for calculating the performance data of a gas turbine, and in particular, the conditions of each part of the compressor, the combustor, and the gas turbine are determined by receiving data on the atmosphere and information on the height of the site where the gas turbine is installed. The present invention relates to a method of calculating a data capable of measuring the performance of a turbine and further graphing the calculated performance data to accurately and easily perform the performance analysis of the gas turbine.

Conventionally, in order to measure the performance of a gas turbine, it is necessary to purchase a commercial program to check various performances of the gas turbine and its performance, and there is a problem in that it is difficult to understand the performance change of the gas turbine.

The present invention is to solve the problems as described above, the object of the compressor, the combustor and gas turbine by receiving data about the atmosphere and the height of the site where the gas turbine is installed, which is the basic data for turbine performance analysis It is to determine the conditions of each part, to calculate the data that can measure the performance of the gas turbine based on this, and further to make the performance analysis of the gas turbine accurate and easy by graphing the calculated performance data.

1 is a view showing a schematic configuration of a general turbine system.

2 is a diagram illustrating a configuration of a performance data calculation system according to the present invention.

3 is a flowchart illustrating a performance data calculation operation according to the present invention.

4 shows a change in turbine efficiency with increasing compression ratio.

5 is a view showing a change in turbine power (Net work) with increasing compression ratio.

Fig. 6 is a diagram showing conditions of respective parts of a compressor, a combustor, and a turbine.

7 is a view showing a change in a correction curve according to a change in compressor inlet temperature.

8 is a view showing a correction curve change according to the change in specific humidity.

9 is a view showing a change in a correction curve according to a change in relative humidity.

Explanation of symbols on the main parts of the drawings

11: compressor 12: combustor

13: gas turbine 20: performance data calculation system

21: data input unit 22: DB

23: performance data calculator 24: data output unit

Method for calculating the performance data of the gas turbine of the present invention for achieving the above object, the step of receiving the information (Weather Data) for the atmosphere together with the height (Site Elevation (H)) information of the site where the turbine is installed; ; Determining a ratio of the combustion amount of air and fuel through analysis of the type of fuel and the fuel component; Determining pressure loss (PiL) of the compressor inlet air and pressure loss (PoL) of the turbine outlet gas by using previously stored pressure loss data for each model; Calculating a modified atmospheric temperature (T1) which is an atmospheric temperature at the height (H) by using the site height (H) information and the atmospheric temperature (Ta) information; Calculating a compressor inlet pressure P1 using the atmospheric pressure Pa, the compressor inlet pressure loss PiL and the calculated correction atmospheric temperature T1; The saturation pressure Ps corresponding to the atmospheric temperature Ta is retrieved from the previously stored saturation pressure Ps table for each atmospheric pressure Ta using the atmospheric temperature Ta, and the retrieved saturation pressure Ps Calculating the wet air pressure Pv at the atmospheric temperature Ta using the site height H information; Calculating an absolute humidity (W) using the compressor inlet pressure (P1) and the calculated wet air pressure (Pv); Calculating a correction compression ratio (σ) according to the change of the atmospheric temperature with respect to the compression ratio P2 / P1 under the ISO condition using the operation principle of the compressor; Determining a compressor inlet side condition using an air flow rate (Q1), a compressor inlet pressure (P1), an inlet temperature (T1), and an entropy (S1) of inlet side air calculated during the fuel analysis; Determining a combustor inlet side condition using the determined compressor inlet side condition; Determining a turbine inlet side condition using the determined combustor inlet side condition; Determining a turbine outlet side condition using the determined turbine inlet side condition; Computing the performance data of the gas turbine using the determined conditions of the compressor, the combustor and the gas turbine.

Furthermore, the performance data calculation method of the gas turbine of the present invention is characterized in that it further comprises the step of graphing and outputting the calculated performance data.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

1 is a diagram illustrating a compressor 11, a combustor 12, and a turbine 13 to which the present invention is applied. Referring to FIG. 1, the steam compressed by the compressor 11 is combusted by the fuel in the combustor 12, flows into the turbine 13 with high temperature gas, and then drives and discharges the gas turbine 13.

2 is a diagram illustrating a schematic configuration of a performance data calculation system according to the present invention, and FIG. 3 is a flowchart illustrating a turbine performance analysis operation of the system.

Referring to FIGS. 2 and 3, first, the performance data calculator 23 provides information on the atmosphere together with information on the height of the site on which the turbine 13 is installed through the data input unit 21. Data) is input (S301). The atmospheric information is information on the temperature Ta, the pressure Pa and the relative humidity RH of the atmosphere.

Then, the ratio of the combustion amount of the air and the fuel is determined by analyzing the type of fuel and the fuel component (S302), and the pressure of the air at the inlet side of the compressor 11 using the pressure loss data for each model pre-stored in the DB 22. The loss PiL and the pressure loss PoL of the gas at the outlet of the turbine 13 are determined (S303).

Thereafter, using the site height H information and the atmospheric temperature Ta information, a modified atmospheric temperature T1 which is an atmospheric temperature at the corresponding height H is calculated through the following equation (S304).

Then, using the atmospheric pressure Pa, the compressor 11 inlet pressure loss PiL, and the calculated correction atmospheric temperature T1, the compressor 11 inlet pressure P1 is obtained through the following equation. It calculates (S305).

Subsequently, the saturation pressure Ps corresponding to the corresponding atmospheric temperature Ta is searched for in the saturation pressure Ps for each atmospheric pressure Ta previously stored in the DB 22 using the atmospheric temperature Ta. Using the retrieved saturation pressure Ps and the site height H, the wet air pressure Pv at the atmospheric temperature Ta is calculated through the following equation (S306).

Where RH is the relative humidity (%) of the atmosphere.

Then, the absolute humidity W is calculated through the following equation using the compressor 11 inlet pressure P1 and the calculated wet air pressure Pv (S307).

Here, Gw is the amount of wet steam in the air and Ga is the amount of dry air in the air.

Then, the correction compression ratio (σ) according to the change of the atmospheric temperature with respect to the compression ratio (P2 / P1) at ISO conditions of 15.6 deg.C and 60% relative humidity according to the operating principle of the compressor is calculated through the following equation. (S308).

Where n is the polytropic index, T2 is the temperature (273.15 + T1) in the actual adiabatic compression of the combustor 12 inlet, and P2 is the combustor 12 inlet pressure.

Then, the compressor 11 inlet condition is determined using the air flow rate Q1, the compressor 11 inlet pressure P1, the inlet temperature T1, and the entropy S1 of the inlet air, which are calculated during the fuel analysis. In operation S309, the inlet condition of the combustor 12 as described below is determined using the determined condition of the inlet side of the compressor 11 (S310).

P2 = P1 * σ

T2s = (T1 + 273.15) * σ ^{(1.4-1) /1.4]-273.15}

T2 = T1 + (T2s- T1) / Nc

S2s = S1

S2 = Cv LN (T2 / T1) + S1

Here, T2s is the temperature in the theoretical adiabatic compression process at the inlet of the combustor 12, S2s is the entropy in the theoretical adiabatic compression process, S2 is entropy in the actual adiabatic compression process, Nc is the adiabatic efficiency of the compressor (%) , Cv is the heat insulation specific heat of air.

Subsequently, the turbine 13 inlet side condition is determined using the determined combustor inlet side condition (S311).

P3 = P2 * 97% (3% pressure loss in the combustion chamber)

T3 = 1374 (design parameters of the turbine model)

S3 = S4s

Where P3 is the inlet pressure of the turbine 13, T3 is the inlet temperature of the turbine 13, S3 is the entropy at the inlet side of the turbine 13, and S4s is the entropy in the theoretical thermal insulation process at the outlet side of the turbine 13. to be.

Then, the turbine outlet side conditions as described below are determined using the determined turbine 13 inlet side conditions (S312).

P4 = P3 / σ + PoL

T4s = (T1 + 273.15) * (P4 / P3) ^{[(1.4-1) /1.4]} -273.15

T4 = T3- (T3-T4s) * Nt

S4s = S1 + Cv LN (T4s / T1)

S4 = S1 + Cv LN (T4 / T1)

Where P4 is the turbine 13 outlet pressure, T4 is the temperature in the actual adiabatic compression process at the turbine 13 outlet side, T4s is the temperature in the theoretical adiabatic compression process at the turbine 13 outlet side, and S4 is the turbine. (13) The entropy in the actual adiabatic compression process on the outlet side, Nt, is the adiabatic efficiency of the gas turbine 13.

Then, the following performance data is calculated using the conditions of the determined compressor 11, combustor 12, and gas turbine 13 (S313).

Qe = Q + Ff / 3600 (kg / sec)

Effi = 1-[(T4s-T1) / (T3-T2s)] (%)

Effa = 1-[(T4-T1) / (T3-T2)] (%)

Wic = 0.24 * (T2s-T1) * A /101.97 * Qe

Wac = 0.24 * (Ts-T1) * A /101.97 * Qe

Wit = 0.24 * (T3-T4s) * A /101.97 * Qe

Wat = 0.24 * (T3-T4) * A /101.97 * Qe

Pi = Wit-Wic

Pa = Wat-Wac

Work Ratio (Ri) = Wic / Wit

Work Ratio (Ra) = Wac / Wat

HRi = 860 / Effi (kcal / kw hr)

HRa = 860 / Effi (kcal / kw hr)

Where Qe is the flow rate of the exhaust gas, Q is the flow rate of the air, Ff is the amount of fuel, Effi is the theoretical thermal efficiency of the gas turbine 13, Effa is the actual thermal efficiency of the gas turbine 13, and Wic is the compressor 11. Is the theoretical power dissipated at, Wac is the actual power dissipated in the compressor 11, Wit is the theoretical generated power generated in the gas turbine 13, Wat is the actual generated power generated in the gas turbine 13, Pi is the theoretical active power, Pa is the actual active power, Ri is the theoretical power of the compressor 11 to the output of the gas turbine 13, Ra is the actual power of the compressor 11 to the output of the gas turbine 13, HRi is the theoretical heat rate and HRa is the actual calorie ratio.

Finally, the change in the efficiency of the turbine 13 according to the increase in the compression ratio considering the theoretical compression process and the actual compression process of the turbine 13 and the compressor 11 by using the calculated performance data (FIG. 4), and the compression ratio increase. According to the change of the turbine 13 output (Net work) (Fig. 5), the compressor 11 and the combustor 12, and the condition of the respective parts of the turbine 13 (Fig. 6), the compressor 11 inlet temperature Change in the correction curve according to the change (Fig. 7), change in the correction curve according to the change in non-humidity (Fig. 8), change in the correction curve according to the change in the relative humidity (Fig. 9), and the relationship between the turbine efficiency and output according to the increase in the compression ratio , The change in the calibration curve of the gas turbine according to the ambient temperature, the change in the calibration curve of the gas turbine 13 according to the change in the absolute humidity affected by the change in the ambient temperature, the change in the absolute humidity affected by the change in the relative humidity Of the calibration curve of the gas turbine 13 according to the Change in the correction curve of the gas turbine 13 according to the height of the edge, change in the correction curve of the gas turbine 13 according to the pressure loss at the inlet side of the compressor 11, and the gas turbine according to the pressure loss at the outlet side of the gas turbine 13 ( A graph showing a change in the correction curve of 13) is implemented and output through the data output unit 24 (S314).

In addition, the embodiment according to the present invention is not limited to the above description, and various alternatives, modifications, and changes can be made within the scope apparent to those skilled in the art.

As described above, the present invention receives data on the atmosphere and information on the height of the site where the gas turbine is installed, determines the conditions of each part of the compressor, the combustor, and the turbine, and based on the data, the data of the performance of the gas turbine can be measured. By calculating the and further graphing the calculated performance data, it is possible to easily measure the performance of the gas turbine, there is an effect that can confirm the performance change through the increase and decrease of the design data of the gas turbine.

Claims (2)

Receiving information on atmospheric temperature (Ta), atmospheric pressure (Pa), and relative humidity (RH), which are weather information (Weather Data), together with the height (Site Elevation) information of the site where the turbine is installed; Determining a ratio of the combustion amount of air and fuel through analysis of the type of fuel and the fuel component; Determining pressure loss (PiL) of the compressor inlet air and pressure loss (PoL) of the turbine outlet gas by using previously stored pressure loss data for each model; Calculating a modified atmospheric temperature (T1) which is an atmospheric temperature at the height (H) by using the site height (H) information and the atmospheric temperature (Ta) information; Calculating a compressor inlet pressure P1 using the atmospheric pressure Pa, the compressor inlet pressure loss PiL and the calculated correction atmospheric temperature T1; The saturation pressure Ps corresponding to the atmospheric temperature Ta is retrieved from the previously stored saturation pressure Ps table for each atmospheric pressure Ta using the atmospheric temperature Ta, and the retrieved saturation pressure Ps Calculating the wet air pressure Pv at the atmospheric temperature Ta using the site height H information; Calculating an absolute humidity (W) using the compressor inlet pressure (P1) and the calculated wet air pressure (Pv); Calculating a correction compression ratio σ according to the change of the atmospheric temperature with respect to the compression ratio P2 / P1 under the ISO condition using the operation principle of the compressor; Compressor inlet side condition, combustor inlet side condition, turbine inlet side condition using air flow rate Q1, compressor inlet pressure P1, inlet temperature T1, and entropy S1 of inlet side air calculated during the fuel analysis And sequentially determining turbine outlet conditions; And calculating the performance data of the gas turbine using the determined conditions of the compressor, the combustor, and the gas turbine. The method of claim 1, And graphing and outputting the calculated performance data.