CN113032914A - Gas turbine performance calculation and simulation method - Google Patents
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Abstract
The invention provides a method for calculating and simulating performance of a gas turbine, which comprises the following steps: s1, calculating the thermophysical property of the working medium in the gas turbine; s2 calculating the molar composition of the gas turbine fuel; s3, cooling blending calculation; s4, calculating the thermophysical properties of working media at the sections of the inlet and the outlet; s5, calculating entropy change of internal pressure change; and S6, respectively calculating the inlet parameters and the outlet parameters of all parts of the gas turbine to obtain the input and output mapping relation of the thermal physical properties of the inlet working medium and the outlet working medium of all parts of the gas turbine. The invention provides a solution with small calculation amount, flexibility and convenience for solving the problem of overall performance calculation of the gas turbine caused by fuel component change or fuel type change.
Description
Technical Field
The invention relates to the field of overall performance calculation of gas turbines, in particular to a method for calculating and simulating the performance of a gas turbine.
Background
The overall performance of a gas turbine is the most important indicator of a gas turbine. The overall performance calculation of the gas turbine is closely related to the components of the internal working medium and the thermophysical property calculation thereof. Accurately calculating the components of the working medium is a precondition for accurately calculating the thermophysical properties of the working medium. If the component calculation is not accurate enough, the gas turbine performance calculation and simulation will generate large errors. However, in some typical processes (combustion process, cooling-blending process) and changes in environmental conditions (changes in ambient humidity) of a gas turbine, the composition of the working fluid changes significantly. In addition, to meet the operating economy requirements of gas turbines, the fuels used by gas turbines are also becoming increasingly abundant. Considering the bleed air position and the bleed air quantity of the cooling and mixing, the mass ratio of the fuel to the air and the widening of the fuel types can cause the components of the working medium in the gas turbine to obviously change. When the gas turbine is used industrially, in order to match a local industrial production system and maximize economic benefits, it is often required to use unconventional fuels such as coke oven gas, blast furnace gas, and the like. Despite the use of unconventional fuels, due to design costs, the original gas turbine structure is often used or modified based on the original gas turbine structure. If the overall performance of the gas turbine after fuel change can meet the requirements of users according to the traditional overall performance calculation mode, a great deal of experiments are needed, and a great deal of time and cost are consumed.
Because the traditional gas turbine overall performance calculation mode, particularly the performance calculation mode of the downstream of a combustion chamber, can obtain the final convergence result only by carrying out repeated iteration of the oil-gas ratio according to specific fuel, and has strict requirements and limits on the deviation value of the fuel component relative to the standard fuel component. If the fuel type is changed, the empirical curve for the particular fuel needs to be re-run. Chemical components of fuels such as diesel oil, kerosene and natural gas are not fixed, which causes that a traditional working medium thermophysical property calculation method may have larger errors. In addition, because of the economical use of gas turbine fuel, industrial residual gas with unstable component content such as coke oven gas is used in the combustion process of the gas turbine, if each fuel is empirically analyzed according to the conventional calculation method of the thermal physical property of the working fluid, a lot of time and cost are consumed.
Disclosure of Invention
Accordingly, to overcome the above-mentioned shortcomings of the prior art, the present invention provides a gas turbine performance calculation and simulation method to reduce analysis time and calculation cost.
In order to achieve the above object, a method for calculating and simulating the performance of a gas turbine is provided, the gas turbine comprising the following components: the performance calculation and simulation method comprises the following steps:
s1, calculating the thermophysical property of the internal working medium of the gas turbine:
dry air for repartitioning the gas inside the gas turbine is divided into N2, O2, H2O, CO2 and residual gas, and the thermal property of the residual gas is calculated according to the thermal properties of the dry air, N2, O2, H2O and CO 2;
calculating the mass component and the molar component of the gas inside the gas turbine according to the thermal properties of N2, O2, H2O, CO2 and the rest gas;
calculating the thermophysical property of the gas inside the gas turbine according to the mass component and the molar component of the gas inside the gas turbine;
s2 calculating the molar composition of the gas turbine fuel:
calculating the mass components of the working medium burnt completely by the dry air and the mass components of the working medium burnt when the dry air is excessive according to the thermal physical properties of the gas in the gas turbine obtained in the step S1;
s3, cooling blending calculation:
calculating the mass component of the gas inside the gas turbine after mixing according to the mass component of the cooling gas and the mass component of the gas upstream in the cooling and mixing process;
s4, calculating the thermophysical properties of working media at the inlet and outlet sections:
calculating other thermophysical parameters of the inlet and outlet sections according to the total temperature, the total pressure, the axial velocity, the non-axial velocity, the mass flow and the mixed mass components of the gas in the gas turbine;
s5, calculating entropy change of internal pressure change:
calculating the entropy change of the internal pressure change according to the entropy change of the internal temperature and the mass components of the gas turbine through an isentropic process;
and S6, respectively calculating the inlet parameters and the outlet parameters of all parts of the gas turbine to obtain the input and output mapping relation of the thermal physical properties of the inlet working medium and the outlet working medium of all parts of the gas turbine.
Further, the inlet parameters comprise inlet total pressure, inlet total temperature, inlet components, inlet mass flow, inlet axial velocity and inlet non-axial velocity;
the outlet parameters comprise outlet total pressure, outlet total temperature, outlet components, outlet mass flow, outlet axial velocity and outlet non-axial velocity.
Further, the thermophysical properties of the internal working medium of the gas turbine comprise: molar mass, gas constant, constant pressure specific heat, specific heat ratio, specific enthalpy and specific entropy.
Further, other thermophysical parameters of the inlet and outlet cross-section include: gas constant, specific enthalpy, static temperature, specific heat ratio, specific entropy, static pressure, density, area and Mach number.
Further, calculating the entropy change of the internal pressure change by an isentropic process based on the entropy changes of the internal temperature and the mass composition of the gas turbine, further comprising calculating the pressure of state 2 based on the temperature and pressure of state 1 of the known isentropic process and the temperature of state 2 of the isentropic process.
Compared with the prior art, the invention provides a solution with small calculation amount, flexibility and convenience for the overall performance calculation problem of the gas turbine caused by the change of fuel components or the change of fuel types. The method can more flexibly deal with the influence caused by the change of components by setting the input parameters of the fuel, the mass flow ratio of the cooling gas and the humidity of the inlet air.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to specific embodiments below.
The invention improves the traditional method for calculating and simulating the performance of the gas turbine. Firstly, in order to flexibly deal with the change of fuel components and working medium components, a new expression mode of the working medium components is provided. Secondly, based on the expression mode of the new working medium components, the calculation of the combustion process and the cooling blending process is improved, and the problems of the change of the working medium components caused by the change of the fuel and the cooling blending are solved. On the basis of a new working medium component expression mode, the thermophysical calculation of the working medium at the section between the parts is converted into the calculation of six basic variables through the correlation of a physical process. Further, a calculation mode of an ideal isentropic process is given. And finally, based on all the improvements, aiming at the input and output mapping relation of the thermophysical properties of inlet and outlet working media of each part (an air inlet channel, an air compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine) of the gas turbine. The cooling blending process is considered a part-to-part process. The invention allows calculation and simulation of the overall performance of any gas turbine that can be built with the above-described components.
1. Working medium component expression mode
The calculation of the thermophysical properties of the working medium in the gas turbine is the basis of the calculation of the overall performance. The components of the working medium in the gas turbine are determined by the components and flow rate of inlet air, the components and flow rate of fuel, the flow rate of a secondary air system and the like.
The gas composition of the working medium inside the gas turbine is determined by the gas composition of the dry air and the combustion products. The main component of the dry air comprises N2，O2，H2O，CO2. If the residual gas other than the above four gases in the dry air is considered as LCDA gas, the thermal properties of the LCDA gas can be determined by the dry air and N2，O2，H2O， CO2The thermophysical properties of the five gases are calculated. In order to facilitate the calculation process of the thermophysical parameters of the working medium, N2，O2， H2O，CO2And LCDA gas numbered 1,2, 3, 4, 5 in that order. The specific calculation is shown in table 1.
TABLE 1 LCDA thermal Property calculation Table
In view of the combustion efficiency of the current combustion chamber close to 100%, the combustion product is H2O，CO2. Thus, the gas component of the working medium inside the gas turbine can be composed of N2，O2，H2O，CO2And LCDA five gases. The mass component of the working fluid of the gas turbine can be represented by the formula MIXx ═ x1,x2,x3,x4,x5]And (4) showing. The molar composition of the working fluid of the gas turbine may be represented by the formula MIXn ═ n1,n2,n3,n4,n5]And (4) showing.
The molar fraction and the mass fraction can be converted from the formulae (1-1) and (1-2).
The calculation of the thermophysical properties of the gas turbine working fluid can be found in table 2.
TABLE 2 working medium thermophysical property calculation table
2. Combustion process calculation
The most important parameters for a fuel, whether it be a gaseous fuel (coke oven gas, natural gas, etc.) or a liquid fuel (kerosene, etc.), are the molar composition of the fuel and the lower calorific value of the fuel. Molar constituent of fuel available molecular formula
And (4) showing. The reaction formula of combustion can be represented by formula 2-1.
The molar composition of air can be represented by MIXnair＝[n1,n2,n3,n4,n5]And (4) showing. The amount of substance of air required for 1mol of fuel can be represented by formula 2-2.
The amount of material that is the product of a 1mol fuel just complete combustion process can be represented by table 3.
TABLE 31 formula for calculating burnup product when mol fuel is just completely combusted
Normalization of the moles of each component of the combustion products in Table 3 gave 1mol
The molar composition at the very time of complete combustion can be represented by formulas 2-3.
According to the formulas 1-1 and 1-2, the mass component of the working medium which is just completely combusted can be represented by MIXxproducts＝[x1,gas,x2,gas,x3,gas,x4,gas,x5,gas]And (4) showing.
Mass L of oxidant per unit mass (1kg) of fuel required for combustion0Calculated from equations 2-4.
The mass components of the working medium in the excess air combustion process can be calculated by the formulas 2-5, 2-6 and 2-7.
3. Calculation of cooling blend
Suppose the mass component of the cooling gas is mix ═ x1,x2,x3,x4,x5]Mass composition of gas upstream of cooling blending process is MIXxf＝[x1,f,x2,f,x3,f,x4,f,x5,f]Then, the mass component of the blended gas can be calculated from the formula (3-1).
xi,fc＝(1-yc)xi+ycxi,f,i＝1,2,3,4,5 (3-1)
4. Calculation of thermophysical properties of working medium at inlet and outlet sections of part
The thermophysical parameters corresponding to the inlet and outlet sections of the component include total temperature tT, total pressure tp, static temperature sT, static pressure sp, axial velocity u, non-axial velocity v, mass flow G, Mach number Ma, and gas mass component X [ X ]1,x2,x3,x4,x5]Gas constant RgGas specific heat ratio γ, density ρ, area a, specific enthalpy h and specific entropy s.
In order to determine these parameters, the necessary parameters are: total temperature tT, total pressure tp, axial velocity u, non-axial velocity v, mass flow G, and gas mass component X ═ X1,x2,x3,x4,x5]. Based on these six basic parameters, other thermophysical parameters of the cross section can be obtained from table 4.
TABLE 4 calculation Table of thermophysical parameters of cross section
5. Isentropic process calculation
The ideal process occurring within a component compressor is an isentropic compression process and the ideal process occurring within a component turbine is an isentropic expansion process. The accurate calculation of the isentropic process has important significance on the correctness of the model. The entropy value (isobaric process, component-containing entropy, no pressure-variable entropy) calculation of the mixed gas has been calculated in the above discussion. Since the isentropic process is accompanied by the change of pressure, in the calculation process of the entropy value, we should consider the change of entropy value caused by the change of pressure, and the calculation formula of the specific entropy change is given as formula 5-1 below.
In the above formula, p1And p2Pressure, R, representing State 1 and State 2g,MIXRepresents the molar mass of the mixed gas. Entropy changes due to temperature and composition changes have been discussed in the above process. Therefore, on this basis, the entropy change caused by the pressure change needs to be supplemented. Based on the above formula, the isentropic process can be regarded as Δ s1→2＝0。
The composition of the mixed gas is not considered to change during compressor compression or turbo expansion, and therefore, equation 5-2 can be obtained.
The left side of the equation is the specific entropy change related to the temperature calculated by us in the previous description, and the right side of the equation is the change of the specific entropy caused by the pressure change. If states 1 to 2 are isentropic processes, their pressure ratio and temperature should satisfy the above equation.
If the temperature T of state 1 of the isentropic process is known1State 1 and state 2, then the temperature of state 2 can be found. Conversely, if the temperature T of state 1 of the isentropic process is known1And pressure p1Temperature T of State 22Then pressure p of state 22Can be found. Namely, the relationship of the formula 5-3.
6. Component input output calculation
Since only the above six parameters are required for determining the thermal physical property parameter of the cross section, the component input/output calculation only needs to consider the mapping relationship of the six parameters.
The inlet is insulated except for the inlet and outlet of the inlet; taking into account the total pressure loss of the inlet duct, the total pressure loss coefficient sigmainletWill be used for the calculation; the inlet duct does not have mass exchange with the outside except for the inlet and outlet.
The inlet and outlet of the inlet channel can be obtained from the relationship in table 5.
TABLE 5 mapping relationship of inlet and outlet key parameters of air inlet
The compressor is adiabatic except for the inlet and the outlet of the compressor; the mass exchange between the compressor and the outside is not performed except for an inlet and an outlet of the compressor; the ideal internal process of the compressor is an isentropic process, and the actual process is a process with constant pressure ratio and isentropic efficiency.
The compressor pressure ratio is compressor _ tp _ ratio, and is defined as equation 6-1.
Isentropic efficiency ηs,compressorIs defined as formula 6-2.
In formula 6-2: the compressor _ out _ ideal.h is the ideal enthalpy value of the outlet of the isentropic process under the condition that the pressure ratio is not changed. According to the assumption that the relation of the formula 6-3 and the formula 6-4 is provided.
compressor_out.G＝compressor_in.G (6-3)
compressor_out.X＝compressor_in.X (6-4)
The isentropic relation of an ideal process in the isentropic process calculation is used, and the relation has an equation 6-5.
From the total outlet temperature compressor _ out _ ideal.tT of the ideal process, the ideal outlet specific enthalpy compressor _ out _ ideal.h can be found, as in equation 6-6.
According to the isentropic efficiency etas,compressorThe actual outlet specific enthalpy, compressor _ out.h, can be derived as
And 6-7.
After the actual outlet specific enthalpy compressor _ out.h is determined, the actual outlet total temperature compressor _ out.tT can be obtained. As shown in formulas 6-8.
compressor_out.tT＝h-1(compressor_out.h,compressor_out.X) (6-8)
The compressor inlet and outlet can be obtained from the relationship in table 6.
TABLE 6 compressor Inlet and outlet Key parameter mapping relationship
Combustion chamber (Combustion Chamber)ber, abbreviated as CC). The combustion chamber is insulated except for the inlet and outlet of the combustion chamber; the combustion process is considered to be complete combustion of the fuel (in practice the combustion efficiency is high, this can be considered); the C element in the fuel generates CO2All H elements form H2The elements O and N are both generated into N2(ii) a Total pressure recovery coefficient of combustion is σCC。
Introducing a parameter oil-gas ratio or fuel-air ratio f as shown in the formula 6-9.
In formulas 6 to 8, GfuelRepresenting the mass flow of fuel. The chemical formula of the fuel can be regarded as
From the combustion calculation with the gas-oil ratio, i.e. equations 2-5, 2-6, 2-7, the composition of the combustion products, i.e. CC out.
The combustion chamber outlet flow CC _ out.G can be calculated according to the oil-gas ratio f, as shown in the formula 6-10.
CC_out.G＝(1+f)·CC_in.G (6-10)
Total pressure recovery coefficient of combustion is σCCIs defined as formula 6-11.
From this, the total combustor exit pressure can be calculated. According to the conservation of energy, there is a relationship of the formula 6-12.
L0·ho(Tref)+1·(LHVfuel+hfuel)＝(1+L0)hp(Tref) (6-12)
In formulas 6-11, LHVfuelIs the chemical energy, h, released per unit mass of fuel burnedfuelIs the enthalpy value of the fuel. From equations 6-11, the specific combustion chamber outlet enthalpy CC _ out.h can be derived. Such as 6-13.
h(CC-in.X，cc_in.tT)-h(CC_inX，Tref)+f[hfuel(Tfuel)-hfuel(Tref)+LHVfuel·ηcc]＝ (1+f)[h(CCout.X，CCout.tT)-h(CCout.X，Tref)] (6-13)
Wherein eta isCCThe combustion efficiency of the combustion chamber.
The total outlet temperature of the combustion chamber can be determined from the specific enthalpy of the combustion chamber outlet CC _ out.h and the gas component CC _ out.x. Such as 6-14.
CC_out.tT＝h-1(CC_out.h，CC_out.X) (6-14)
The combustor inlet outlet can be derived from the relationship in table 7.
TABLE 7 Combustion chamber inlet outlet key parameter mapping relation table
Assuming that each blending process occurs between the speeds of the two components, i.e., the cooling blending process occurs before entering the downstream component, the change in working fluid composition can be calculated by equation 3-1.
Assumptions about a constant pressure ratio turbine (power turbine) are: the inlet duct is insulated, except for the inlet and outlet of the turbine; the turbine has no mass exchange with the outside except for an inlet and an outlet; the ideal turbine internal process is an isentropic process, and the actual process is a process with constant pressure ratio and isentropic efficiency.
The turbine pressure ratio is turbo _ tp _ ratio, defined as equation 6-15.
Isentropic efficiency eta of constant pressure ratio turbines,turbineThe definitions of (1) are 6 to 16.
In the formulas 6 to 16, the turbine _ out _ ideal.h is the ideal enthalpy value of the outlet in the isentropic process under the condition that the pressure ratio is not changed.
The pressure ratio is defined by the formulas 6 to 17.
The isentropic relation of an ideal process in the isentropic process calculation is utilized, and the relation has a formula 6-18.
According to the total outlet temperature turbo _ out _ ideal.tT in the ideal process, the ideal outlet specific enthalpy turbo _ out _ ideal.h can be found, as shown in the formulas 6-19.
turbine_out_ideal.h＝h(turbine_out_ideal.tT,turbine_out.X) (6-19)
According to the isentropic efficiency etas,turbineThe actual outlet specific enthalpy turbo out.h can be derived, as in equations 6-20.
After the actual outlet specific enthalpy turbine _ out.h is determined, the actual outlet total temperature turbine _ out.tT can be obtained, as shown in the formula 6-21.
turbine_out.tT＝h-1(turbine_out.h,turbine_out.X) (6-21)
The turbine inlet-outlet of the constant pressure ratio can be obtained from the relation in table 8.
TABLE 8 mapping relation table of key parameters of turbine inlet and outlet with constant pressure ratio
Regarding the speed of the turbine (high-pressure turbine) with constant power output, is provided: the inlet duct is insulated, except for the inlet and outlet of the turbine; the turbine has no mass exchange with the outside except for an inlet and an outlet; the ideal turbine internal process is an isentropic process; work W of the turbineturbineAnd (4) determining.
According to the conservation of energy, the output work W of the turbineturbineThe following relational expressions 6 to 22 are satisfied.
Therefore, the specific enthalpy value turbo _ out.h of the turbine outlet can be obtained from equations 6 to 23.
Isentropic efficiency ηs,turbineIs defined as formula 6-24.
The desired specific enthalpy value turbo _ ideal _ out.h for the turbine outlet can be derived from equations 6-25.
After the actual outlet specific enthalpy turbine _ out.h is determined, the actual outlet total temperature turbine _ out.tT can be obtained, as shown in the formula 6-26.
turbine_out.tT＝h-1(turbine_out.h,turbine_out.X) (6-26)
The isentropic relation of an ideal process in the isentropic process calculation is utilized, and the function relation of the equation 6-27 is obtained.
Thus, the turbine outlet total pressure turbo out tp can be calculated by equations 6-28.
The turbine inlet and outlet with constant power output can be obtained from the relation in table 9.
TABLE 9 constant pressure ratio turbine inlet and outlet critical parameter mapping relationship
Description of the symbols:
1. corner mark description
air (with humidity)
i, j gas number
1,2,3,4 CO2,H2O,N2,O2
5, removing CO from LCDA dry air2,H2O,N2,O2External mixed gas
c cooling the gas
Number of k gas species
dryair
Combustion products at f fuel-air ratio f
fc cooled blended component
fuel
Combustion products of gas just completely burning
products of combustion
MIX gas mixtures or working substances
C, H
N, O, N, O
2. Description of variables
A (t) empirical fitting coefficient, t 1,2
cpSpecific heat at constant pressure, J.kg-1·K-1
f oil-gas ratio
h specific enthalpy, J.kg-1
L0Theoretical air demand of fuel, kg.kg-1
m&Mass flow rate, kg.s-1
M molar mass, kg. mol-1
Molar component formula of MIXn mixed gas
Mass component formula of MIXx mixed gas
Molar composition of n working substances or of fuel elements
Number of moles, mol of N gas
NneedMolar gas requirement for just complete combustion
R is general gas constant, R is 8.3144J. mol-1·K-1
RgGas constant, J.kg-1·K-1
s specific entropy, J.kg-1·K-1
Entropy of S, J.K-1
T temperature, K
x mass fraction
Mass fraction of cooling gas in cooled blended gas
Specific heat ratio of gamma gas
Claims (5)
1. A method of gas turbine performance calculation and simulation, the gas turbine comprising the following components: air inlet, compressor, combustion chamber, high-pressure turbine, low-pressure turbine, its characterized in that: the performance calculation and simulation method comprises the following steps:
s1, calculating the thermophysical property of the internal working medium of the gas turbine:
dry air for repartitioning the gas inside the gas turbine is divided into N2, O2, H2O, CO2 and residual gas, and the thermal property of the residual gas is calculated according to the thermal properties of the dry air, N2, O2, H2O and CO 2;
calculating the mass component and the molar component of the gas inside the gas turbine according to the thermal properties of N2, O2, H2O, CO2 and the rest gas;
calculating the thermophysical property of the gas inside the gas turbine according to the mass component and the molar component of the gas inside the gas turbine;
s2 calculating the molar composition of the gas turbine fuel:
calculating the mass components of the working medium burnt completely by the dry air and the mass components of the working medium burnt when the dry air is excessive according to the thermal physical properties of the gas in the gas turbine obtained in the step S1;
s3, cooling blending calculation:
calculating the mass component of the gas inside the gas turbine after mixing according to the mass component of the cooling gas and the mass component of the gas upstream in the cooling and mixing process;
s4, calculating the thermophysical properties of working media at the inlet and outlet sections:
calculating other thermophysical parameters of the inlet and outlet sections according to the total temperature, the total pressure, the axial velocity, the non-axial velocity, the mass flow and the mixed mass components of the gas in the gas turbine;
s5, calculating entropy change of internal pressure change:
calculating the entropy change of the internal pressure change according to the entropy change of the internal temperature and the mass components of the gas turbine through an isentropic process;
and S6, respectively calculating the inlet parameters and the outlet parameters of all parts of the gas turbine to obtain the input and output mapping relation of the thermal physical properties of the inlet working medium and the outlet working medium of all parts of the gas turbine.
2. The method of claim 1,
the inlet parameters comprise inlet total pressure, inlet total temperature, inlet components, inlet mass flow, inlet axial velocity and inlet non-axial velocity;
the outlet parameters comprise outlet total pressure, outlet total temperature, outlet components, outlet mass flow, outlet axial velocity and outlet non-axial velocity.
3. The method of claim 1, wherein said gas turbine internal working fluid thermophysical properties comprise: molar mass, gas constant, constant pressure specific heat, specific heat ratio, specific enthalpy and specific entropy.
4. The method of claim 1, wherein the other thermophysical parameters of the access port cross-section include: gas constant, specific enthalpy, static temperature, specific heat ratio, specific entropy, static pressure, density, area and Mach number.
5. The method of claim 1, wherein the entropy change of the internal pressure change is calculated by an isentropic process based on the entropy changes of the gas turbine internal temperature and the mass composition of the gas, further comprising calculating the state 2 pressure based on the temperature and pressure of state 1 of the known isentropic process and the temperature of state 2 of the isentropic process.
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| CN109858129A (en) * | 2019-01-23 | 2019-06-07 | 清华大学 | A kind of gas turbine dynamic emulation method about combined supply system |
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| CN108304678A (en) * | 2018-03-06 | 2018-07-20 | 中国船舶重工集团公司第七0三研究所 | The method for being directed to different fuel calculation gas turbine performance based on emulation platform |
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