Gas turbine real-time performance evaluation method

Abstract

The present application relates to gas turbine technology field, especially a kind of gas turbine real-time performance evaluation method, the first control body including compressor, combustion chamber and turbine is carried out heat balance analysis one-calculates compressor inlet air mass flow;Second control body including combustion chamber is carried out heat balance analysis two-calculates turbine inlet equivalent temperature;Step one, the compressor inlet air mass flow and turbine inlet equivalent temperature of performance test time are obtained by heat balance analysis one, two of performance test time;Step two, according to the compressor inlet air mass flow and turbine inlet equivalent temperature of performance test time, turbine equivalent flow is calculated;Step three, determine the change rule of turbine equivalent flow in actual operation;Step four, the compressor inlet air mass flow, turbine inlet equivalent temperature, fuel flow and efficiency in actual operation are calculated by heat balance analysis one, two in actual operation and the change rule of turbine equivalent flow.Performance evaluation in actual operation is realized.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and in particular to a method for real-time performance evaluation of gas turbines. Background Technology

[0002] In the field of gas turbine operation and maintenance, whether assessing overall unit performance or diagnosing and resolving gas path faults, it is often necessary to evaluate gas turbine efficiency, compressor inlet flow rate, and turbine inlet temperature. These parameters cannot be directly measured by instruments and can be calculated using formulas based on test data in ISO 2314 (Gas Turbine Acceptance Testing Standard) during new unit performance testing. However, during daily operation, turbine flow meters that measure fuel quantity inevitably drift over time, reducing accuracy and making it impossible to obtain accurate fuel quantity and composition. Fuel quantity has a significant impact on efficiency accuracy; a 1% deviation in fuel quantity results in approximately a 1% deviation in efficiency. According to researchers' years of experience in gas turbine operation and maintenance, the deviation of turbine flow meter measurements after long-term operation exceeds 5%. Therefore, it is necessary to address the problem of unit performance evaluation under conditions of inaccurate fuel quantity measurement or missing composition. Summary of the Invention

[0003] In view of the above-mentioned deficiencies of the prior art, the technical problem to be solved by the present invention is to provide a real-time performance evaluation method for gas turbines, which can evaluate the on-site operating performance of gas turbines when fuel quantity measurement is inaccurate or components are missing.

[0004] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: a real-time performance evaluation method for a gas turbine, wherein the compressor, combustion chamber, and turbine are collectively regarded as the first control body, and the compressor inlet air mass flow rate is calculated by performing a heat balance analysis on the first control body; the combustion chamber is regarded as the second control body, and the turbine inlet equivalent temperature is calculated by performing a heat balance analysis on the second control body; the real-time performance evaluation method for a gas turbine includes the following steps in sequence: Step 1, based on the performance test data of the new gas turbine, the compressor inlet air mass flow rate and the combustion chamber inlet equivalent temperature are obtained through heat balance analysis one and heat balance analysis two during the performance test. Step 1: Turbine inlet equivalent temperature; Step 2: Calculate the turbine equivalent flow rate during the performance test based on the compressor inlet air mass flow rate and turbine inlet equivalent temperature during the performance test; Step 3: Determine the variation law of the turbine equivalent flow rate during actual operation of the gas turbine relative to the turbine equivalent flow rate during the performance test; Step 4: Based on the actual operating data of the gas turbine, calculate the compressor inlet air mass flow rate, turbine inlet equivalent temperature, and fuel flow rate during actual operation through heat balance analysis one and heat balance analysis two during actual operation and the variation law of turbine equivalent flow rate, and calculate the efficiency of the gas turbine based on the fuel flow rate during actual operation.

[0005] Preferably, the calculation formula for heat balance analysis one is as follows:

[0006]

[0007] The calculation formula for heat balance analysis II is as follows:

[0008]

[0009] In equations (1) and (2), m a1 M is the mass flow rate of the air at the compressor inlet. comb For fuel flow rate, η tc Fuel combustion efficiency, LHV is the lower heating value of the fuel, h f4 Where h0 is the latent heat of fuel and h0 is the enthalpy reference point, P S Q represents the total power of the gas turbine. m For mechanical loss, h g8 h represents the turbine exhaust enthalpy. a1 h is the enthalpy at the compressor inlet. a3 m is the enthalpy at the compressor outlet. eq h is the equivalent compressor inlet air mass flow rate. g6 This is the equivalent enthalpy value at the turbine inlet;

[0010] The turbine inlet equivalent temperature is T. g6 And through the turbine inlet equivalent enthalpy h g6 It is obtained by calculation using the enthalpy-temperature relationship.

[0011] Preferably, in step one, m in the first and second thermal balance analyses during the performance test... a1 M comb h g8 h a1 h a3 h g6 And T g6 All data were obtained during performance testing and are denoted as m. a1_ref M comb_ref h g8_ref h a1_ref h a3_ref h g6_ref And T g6_ref , of which M comb_ref It is measured by the fuel flow meter during the performance test; in step two, the formula for calculating the turbine denominated flow rate during the performance test is:

[0012]

[0013] In equation (3), R is the turbine deducted flow rate during performance testing. refP is the turbine outlet working gas constant during performance testing. g6_ref This refers to the turbine inlet pressure during performance testing.

[0014] Preferably, in step three, the variation law of the turbine deducted flow rate is as follows:

[0015]

[0016] In equation (4), m a1 M comb T g6 All data are from actual operation, where R is the turbine outlet working gas constant during actual operation, and P... g6 σ represents the turbine inlet pressure during actual operation, and σ is the turbine flow capacity attenuation factor.

[0017] Preferably, the turbine flow capacity attenuation factor σ is:

[0018]

[0019] In equation (5), EOH represents the equivalent operating hours in the gas turbine control system.

[0020] Preferably, in step four, m in the actual operation of heat balance analysis one and heat balance analysis two a1 M comb h g8 h a1 h a3 h g6 And T g6 All data are from actual operation; the formula for calculating the efficiency of a gas turbine is:

[0021]

[0022] Q fuel =M comb *η tc *(LHV+h f4 -h0) (7)

[0023] In equations (6) and (7), η is the efficiency of the gas turbine, and Q fuel M represents the energy brought into the gas turbine unit by the fuel that can be utilized. comb This represents the actual fuel flow rate during operation.

[0024] Preferably, when the fuel components are unavailable, the lower heating value (LHV) of the fuel is assumed.

[0025] Compared with the prior art, the present invention has significant progress:

[0026] The real-time performance evaluation method for gas turbines of this invention is based on the variation law of turbine reduced flow rate during actual operation relative to the turbine reduced flow rate during performance tests. It calculates the fuel flow rate during actual operation and calculates the compressor inlet air mass flow rate, turbine inlet equivalent temperature, and efficiency during actual operation to achieve real-time performance evaluation of the gas turbine. This solves the problem of inaccurate performance evaluation caused by the inaccurate measurement of fuel flow rate during actual operation due to the offset of the fuel flow meter. It enables a more accurate evaluation of the on-site operating performance of the gas turbine even when the fuel flow measurement is inaccurate or components are missing. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of two control bodies in the real-time performance evaluation method for gas turbines according to an embodiment of the present invention.

[0028] Figure 2 This is a schematic diagram illustrating the variation of turbine flow capacity with pressure ratio at different equivalent speeds in the real-time performance evaluation method for gas turbines according to an embodiment of the present invention.

[0029] The reference numerals in the attached figures are explained as follows:

[0030] 1. Air compressor

[0031] 2 Combustion Chamber

[0032] 3 turbine

[0033] A First Control Body

[0034] B Second Control Body Detailed Implementation

[0035] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings. These embodiments are for illustrative purposes only and are not intended to limit the scope of the invention.

[0036] In the description of this invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0037] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0038] Furthermore, in the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0039] like Figure 1 and Figure 2 The illustration shows an embodiment of the real-time performance evaluation method for gas turbines according to the present invention. While the temperature, pressure, and power measurements of a gas turbine unit after long-term operation remain relatively accurate, the main problems are inaccurate fuel quantity measurement and missing fuel components. In such cases, the real-time performance evaluation method of this embodiment can be used to evaluate the on-site operating performance of the gas turbine.

[0040] See Figure 1 The real-time performance evaluation method for gas turbines in this embodiment is based on ISO 2314 (Acceptance Test Standard for Gas Turbines). The compressor 1, combustion chamber 2 and turbine 3 are collectively regarded as the first control body A. Thermal balance analysis one is performed on the first control body A, and the compressor inlet air mass flow rate is calculated from the thermal balance analysis one. Combustion chamber 2 is regarded as the second control body B, and thermal balance analysis two is performed on the second control body B, and the turbine inlet equivalent temperature is calculated from the thermal balance analysis two.

[0041] The calculation formula for heat balance analysis one is as follows:

[0042]

[0043] The calculation formula for heat balance analysis II is as follows:

[0044]

[0045] In equations (1) and (2):

[0046] m a1 This represents the mass flow rate of air at the compressor inlet, expressed in kg / s.

[0047] M comb Fuel flow rate, in kg / s;

[0048] η tc For fuel combustion efficiency, η tc These are empirical parameters;

[0049] LHV is the lower heating value of fuel, measured in kJ / kg. LHV is a measured value that can be obtained by a testing agency.

[0050] h f4 Latent heat of fuel, expressed in kJ / kg, h f4 It can be calculated based on fuel composition;

[0051] h0 is the enthalpy reference point, which is the enthalpy value of the fuel at 0℃, and the unit is kJ / kg;

[0052] P S The total power of the gas turbine is expressed in kW (P). S These are measured values, which can be obtained through measurement.

[0053] Q m Mechanical losses, in kW, Q m These are empirical parameters;

[0054] h g8 The value represents the turbine exhaust enthalpy, expressed in kJ / kg / h. g8 The turbine exhaust temperature is obtained by calculation using the enthalpy-temperature relationship, and the turbine exhaust temperature is obtained by measurement.

[0055] h a1 This is the enthalpy at the compressor inlet, expressed in kJ / kg / h. a1 The compressor inlet temperature is obtained by calculation using the enthalpy-temperature relationship formula, and the compressor inlet temperature is obtained by measurement.

[0056] h a3 This is the compressor outlet enthalpy, expressed in kJ / kg / h. a3 The compressor outlet temperature is obtained by calculation using the enthalpy-temperature relationship formula, and the compressor outlet temperature is obtained by measurement.

[0057] m eq The equivalent compressor inlet air mass flow rate is expressed in kg / s. It refers to the compressor inlet air mass flow rate under conditions where there is no cooling air extraction but the power consumption is the same as that of an actual compressor. (m³) eq It can be obtained based on empirical calculations;

[0058] h g6 The value represents the equivalent enthalpy at the turbine inlet, expressed in kJ / kg, h. g6 For a specific definition, please refer to ISO 2314.

[0059] Through the equivalent enthalpy h at the turbine inlet g6 The equivalent turbine inlet temperature, T, is obtained by calculating the enthalpy-temperature relationship. g6 T g6 The unit is K.

[0060] The enthalpy-temperature relationship is common knowledge. The enthalpy h is a function of temperature T, and can be found in the following formula:

[0061]

[0062] In equations (1) and (2), η tc LHV, h f4 h0, P S Q m m eq These are definite parameter values ​​that can be known and obtained by those skilled in the art based on experience parameters and relevant measurements, and these parameter values ​​remain consistent during gas turbine performance testing and actual operation.

[0063] The real-time performance evaluation method for gas turbines in this embodiment includes the following steps in sequence.

[0064] Step 1: Based on the performance test data of the new gas turbine, obtain the compressor inlet air mass flow rate and turbine inlet equivalent temperature during the performance test through heat balance analysis one and heat balance analysis two. In this embodiment, m in heat balance analysis one and heat balance analysis two during the performance test... a1 M comb h g8 h a1 h a3 h g6 And T g6 All data were obtained during performance testing and are denoted as m. a1_ref (Compressor inlet air mass flow rate during performance testing), M comb_ref (fuel flow rate during performance testing), h g8_ref (Turbine exhaust enthalpy during performance testing), h a1_ref (Compressor inlet enthalpy during performance testing), h a3_ref (Compressor outlet enthalpy during performance testing), h g6_ref (Equivalent enthalpy at the turbine inlet during performance testing) and T g6_ref (Equivalent turbine inlet temperature during performance testing). Wherein, M... comb_ref The flow rate is measured by the fuel flow meter during performance testing, and the measurement result from the fuel flow meter is accurate at this time. g8_ref h a1_ref and h a3_ref It is calculated using the corresponding temperature values ​​measured during performance testing, m a1_ref and h g6_ref It is M comb_ref h g8_ref h a1_ref and h a3_ref Substituting into equations (1) and (2), we obtain T.g6_ref Through h g6_ref Obtained through calculation.

[0065] Step 2: Based on the compressor inlet air mass flow rate (m) during the performance test. a1_ref And turbine inlet equivalent temperature T g6_ref The turbine's deferred flow rate during the performance test is calculated. The turbine's deferred flow rate represents its flow capacity. In this embodiment, the formula for calculating the turbine's deferred flow rate during the performance test is:

[0066]

[0067] In formula (3):

[0068] The turbine's equivalent flow rate during performance testing is expressed in kg / s.

[0069] m a1_ref +M comb_ref It represents the sum of the compressor inlet air mass flow rate and fuel flow rate during performance testing, and indicates the turbine outlet flow rate, in kg / s.

[0070] R ref R is the turbine outlet working gas constant during performance testing, expressed in J / kg / K. ref The parameters are known.

[0071] P g6_ref P is the turbine inlet pressure during performance testing, expressed in Pa. g6_ref Obtained through measurements during performance testing.

[0072] Step 3: Determine the variation law of the turbine's reduced flow rate during actual operation relative to the turbine's reduced flow rate during performance testing. During actual operation, the turbine's reduced flow rate exhibits a certain variation law as the gas turbine's operating conditions change, such as... Figure 2 As shown, under turbine blockage conditions, the equivalent rotational speed remains unchanged over a wide range of pressure ratio variations, and the equivalent turbine flow rate remains constant. That is, under turbine blockage conditions, the turbine's flow capacity remains constant when the gas turbine unit experiences large pressure ratio variations. With the increase in gas turbine operating hours, the turbine's flow capacity decreases to some extent. The influence of turbine performance degradation factors on turbine performance is shown in Table 1 below:

[0073] Table 1. Effects of Turbine Performance Degradation Factors on Turbine Performance

[0074] 1 Increased tip clearance of turbine blades -3％ -1.8％ 2 Turbine blade wear / corrosion +6％ -2％ 3 Scaling on turbine blades -6％ -2％

[0075] Among the factors causing turbine performance degradation, the effects of turbine blade fouling and turbine blade wear / corrosion on turbine flow capacity cancel each other out, while the increase in turbine blade tip clearance has a relatively small impact on turbine flow capacity. Therefore, it is reasonable to infer that the turbine flow capacity degradation is not significant during gas turbine unit operation. Based on this, in this embodiment, the variation law of turbine equivalent flow rate is as follows:

[0076]

[0077] In equation (4):

[0078] m a1 M comb T g6 All data are from actual operation, specifically the actual compressor inlet air mass flow rate (m³). a1 Actual fuel flow rate M during operation comb The turbine inlet equivalent temperature T during actual operation g6 Because the fuel flow meter deviates as the gas turbine unit operates, it cannot accurately measure the actual fuel flow rate during operation. Therefore, the actual fuel flow rate M during operation will be inaccurate. comb This is an unknown value to be calculated. The actual compressor inlet air mass flow rate (m³) during operation. a1 The turbine inlet equivalent temperature T during actual operation g6 It is also an unknown value to be calculated.

[0079] R is the turbine outlet working gas constant during actual operation, with units of J / kg / K. R is a known parameter, and R = R ref .

[0080] P g6 The turbine inlet pressure during actual operation, in Pa. g6 Obtained through measurements during actual runtime.

[0081] σ is the turbine flow capacity attenuation factor, and σ is an empirical parameter.

[0082] Preferably, the turbine flow capacity attenuation factor σ is:

[0083]

[0084] In equation (5), EOH represents the equivalent operating hours in the gas turbine control system.

[0085] Step 4: Based on the actual operating data of the gas turbine, the compressor inlet air mass flow rate m is calculated using the heat balance analysis formula (1), the heat balance analysis formula (2), and the turbine reduced flow rate variation formula (4). a1The turbine inlet equivalent temperature T during actual operation g6 And the actual fuel flow rate M during operation comb The m in the actual operation heat balance analysis one and heat balance analysis two a1 M comb h g8 h a1 h a3 h g6 And T g6 All data are from actual runtime.

[0086] Based on the actual fuel flow rate M during operation comb The efficiency of the gas turbine is calculated. The formula for calculating the efficiency of a gas turbine is:

[0087]

[0088] Q fuel =M comb *η tc *(LHV+h f4 -h0) (7)

[0089] In equations (6) and (7):

[0090] η is the efficiency of the gas turbine;

[0091] Q fuel The energy brought into the gas turbine unit by fuel that can be utilized is expressed in kJ / s.

[0092] M comb This represents the actual fuel flow rate during operation, expressed in kg / s.

[0093] P S η tc LHV, h f4 h0 is P in equations (1) and (2). S η tc LHV, h f4 、h0.

[0094] Preferably, in the real-time performance evaluation method for gas turbines of this embodiment, when fuel composition is unavailable, the lower heating value (LHV) of the fuel can be assumed. This assumed value is not limited and is related to fluctuations in fuel composition, and can be given based on practical experience in engineering. Since the LHV of the fuel is related to the fuel flow rate M... comb The components are complementary, and the product represents the fuel energy. Therefore, the assumed LHV value does not affect the overall efficiency.

[0095] Therefore, the real-time performance evaluation method for gas turbines in this embodiment is based on the variation law of the turbine reduced flow rate during actual operation relative to the turbine reduced flow rate during performance tests, and calculates the fuel flow rate M during actual operation. comb And the compressor inlet air mass flow rate m during actual operation. a1 Turbine inlet equivalent temperature T g6 The system calculates efficiency η to achieve real-time performance evaluation of gas turbines. This solves the problem of inaccurate performance evaluation caused by the inaccurate measurement of fuel flow during actual operation due to the deviation of the fuel flow meter. It enables a more accurate evaluation of the on-site operating performance of gas turbines even when fuel flow measurement is inaccurate or components are missing.

[0096] To verify the reliability of the real-time performance evaluation method for gas turbines in this embodiment, after a gas turbine unit had been running for a period of time, the fuel flow meter was calibrated, fuel samples were collected, and sent to a qualified testing institution for testing. Performance tests were conducted, and data analysis was performed based on ISO 2314. The efficiency, turbine inlet equivalent temperature, and compressor inlet air mass flow rate were compared with the calculated values ​​(estimated values) obtained using the real-time performance evaluation method for gas turbines in this embodiment. The comparison results are shown in Table 2 below:

[0097] Table 2 Comparison of Measured Values ​​and Estimated Values

[0098] Measured value 35.26 1080.53 527.3 Forecast 35.45 1082.3 515.2 deviation 0.54％ 0.16％ 2.29％

[0099] As can be seen, the prediction errors for efficiency and turbine inlet equivalent temperature are within 0.6%, and the prediction error for compressor inlet air mass flow rate is within 3%. The real-time performance evaluation method for gas turbines in this embodiment can achieve relatively accurate on-site performance evaluation of gas turbines.

[0100] For gas turbine units with performance monitoring systems based on artificial neural networks, the real-time performance evaluation method of the gas turbine in this embodiment can be used to improve the calculation measurement points of the whole machine and provide more effective data.

[0101] For gas turbine manufacturers, before conducting formal third-party verification performance tests on new machines, they can supplement and improve the operating data based on the real-time performance evaluation method of gas turbines in this embodiment, thereby achieving the goal of estimating the overall machine performance without incurring additional testing costs.

[0102] For power plants lacking an online monitoring system for gas turbine performance, the real-time performance evaluation method for gas turbines based on this embodiment, which relies on EXCEL iterative equation solving, can accurately obtain key performance parameters such as gas turbine efficiency, turbine inlet equivalent temperature, and compressor inlet air mass flow rate.

[0103] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present invention, and these improvements and substitutions should also be considered within the scope of protection of the present invention.

Claims

1. A method for real-time performance evaluation of a gas turbine, characterized in that, The compressor, combustion chamber, and turbine are collectively considered as the first control unit. The compressor inlet air mass flow rate is calculated by performing a thermal balance analysis on the first control unit. Using the combustion chamber as a second control unit, the equivalent turbine inlet temperature is calculated through thermal balance analysis of the second control unit; the real-time performance evaluation method for the gas turbine includes the following steps in sequence: Step 1: Based on the performance test data of the new gas turbine, obtain the compressor inlet air mass flow rate and turbine inlet equivalent temperature during the performance test through heat balance analysis one and heat balance analysis two. Step 2: Calculate the turbine equivalent flow rate during the performance test based on the compressor inlet air mass flow rate and turbine inlet equivalent temperature during the performance test. Step 3: Determine the variation pattern of the turbine deducted flow rate during actual operation of the gas turbine relative to the turbine deducted flow rate during the performance test; Step 4: Based on the actual operating data of the gas turbine, calculate the compressor inlet air mass flow rate, turbine inlet equivalent temperature, and fuel flow rate during actual operation by using the heat balance analysis I and heat balance analysis II during actual operation and the variation law of turbine equivalent flow rate. Calculate the gas turbine efficiency based on the fuel flow rate during actual operation. The calculation formula for the first heat balance analysis is as follows: The calculation formula for the second heat balance analysis is as follows: In equations (1) and (2), This refers to the mass flow rate of the air at the compressor inlet. For fuel flow rate, For fuel combustion efficiency, For fuel with low heating value, Latent heat of fuel, As the enthalpy reference point, This refers to the total power of the gas turbine. For mechanical loss, The enthalpy of turbine exhaust gas. This is the enthalpy at the compressor inlet. This is the enthalpy value at the compressor outlet. This represents the equivalent compressor inlet air mass flow rate. This is the equivalent enthalpy value at the turbine inlet; The turbine inlet equivalent temperature is And through the turbine inlet equivalent enthalpy value It is obtained by calculation using the enthalpy-temperature relationship; In step one, the thermal balance analysis one and thermal balance analysis two during the performance test , , , , , as well as All data were obtained during performance testing and are denoted as follows: , , , , , as well as ,in, It was measured by the fuel flow meter during performance testing; In step two, the formula for calculating the turbine's deducted flow rate during the performance test is as follows: In equation (3), This refers to the turbine's deducted flow rate during performance testing. This is the turbine outlet working gas constant during performance testing. This refers to the turbine inlet pressure during performance testing.

2. The real-time performance evaluation method for gas turbines according to claim 1, characterized in that, In step three, the variation law of the turbine deducted flow rate is as follows: In equation (4), , , All data are from actual runtime. This is the turbine outlet working gas constant during actual operation. This refers to the turbine inlet pressure during actual operation. This is the turbine flow capacity attenuation factor.

3. The real-time performance evaluation method for gas turbines according to claim 2, characterized in that, The turbine flow capacity attenuation factor for: In equation (5), This refers to the equivalent operating hours in the gas turbine control system.

4. The real-time performance evaluation method for gas turbines according to claim 2, characterized in that, In step four, the heat balance analysis in the actual operation is performed in two phases: one in phase one and the other in phase two. , , , , , as well as All data are from actual operation; the formula for calculating the efficiency of a gas turbine is: In equations (6) and (7), For the efficiency of the gas turbine, The energy brought into the gas turbine unit by the fuel can be utilized. This represents the actual fuel flow rate during operation.

5. The real-time performance evaluation method for gas turbines according to claim 4, characterized in that, When fuel components are unavailable, the lower heating value of the fuel Use assumed values.

Images