CN112949166A - Method for determining steady-state model coefficient of gas turbine - Google Patents
Method for determining steady-state model coefficient of gas turbine Download PDFInfo
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Abstract
The application belongs to the technical field of steady-state model coefficient determination of gas turbines, and particularly relates to a steady-state model coefficient determination method of a gas turbine, which comprises the following steps: correspondingly calculating to obtain section performance parameters based on the set steady-state model coefficient population of the gas turbine; on the basis of the calculated section performance parameters, correspondingly calculating the fitness between the section performance parameters and the actual section performance parameters; eliminating the gas turbine steady-state model coefficient population corresponding to poor fitness according to the selection probability, performing crossing and variation on the rest gas turbine steady-state model coefficient populations to generate gas turbine steady-state model coefficient sub-populations, and updating the set gas turbine steady-state model coefficient populations by the sub-populations until reaching a genetic algebra; and selecting the steady-state model coefficients of the gas turbines in the rest gas turbine steady-state model coefficient populations.
Description
Technical Field
The application belongs to the technical field of steady-state model coefficient determination of gas turbines, and particularly relates to a steady-state model coefficient determination method of a gas turbine.
Background
The gas turbine is an important power component, steady-state simulation is carried out on the gas turbine, cross-section performance parameters of the gas turbine can be conveniently obtained, and the gas turbine has important guiding significance for design, optimization, debugging and test run of the gas turbine.
The steady-state simulation of the gas turbine is carried out, the accurate setting of the parameters of the gas turbine in the steady-state model, namely the accurate setting of the overall coefficient or the component coefficient of the gas turbine in the steady-state model, is an important guarantee that the simulation steady-state simulation result is effective, at present, when the steady-state simulation of the gas turbine is carried out, the parameters of the gas turbine are mostly calculated in a mode of manually adjusting the parameters, the scheme has low efficiency and depends seriously on experience, the subjective arbitrariness exists, and the calculation precision is difficult to guarantee.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a method of determining steady state model coefficients for a gas turbine that overcomes or mitigates at least one aspect of the technical disadvantages known to exist.
The technical scheme of the application is as follows:
a method of determining steady-state model coefficients for a gas turbine, comprising:
correspondingly calculating to obtain section performance parameters based on the set steady-state model coefficient population of the gas turbine;
on the basis of the calculated section performance parameters, correspondingly calculating the fitness between the section performance parameters and the actual section performance parameters;
eliminating the gas turbine steady-state model coefficient population corresponding to poor fitness according to the selection probability, performing crossing and variation on the rest gas turbine steady-state model coefficient populations to generate gas turbine steady-state model coefficient sub-populations, and updating the set gas turbine steady-state model coefficient populations by the sub-populations until reaching a genetic algebra;
and selecting the steady-state model coefficients of the gas turbines in the rest gas turbine steady-state model coefficient populations.
According to at least one embodiment of the application, in the above method for determining steady-state model coefficients of a gas turbine, the steady-state model coefficients of the gas turbine in the population of steady-state model coefficients of the gas turbine include compressor reduced flow, turbine efficiency, and high-pressure turbine bleed air quantity of the gas turbine.
According to at least one embodiment of the present application, in the above method for determining steady-state model coefficients of a gas turbine, the section performance parameters include rotation speed, total temperature, total pressure, and power of the gas turbine.
According to at least one embodiment of the present application, in the method for determining the steady-state model coefficient of the gas turbine, based on the calculated section performance parameters, the fitness between the calculated section performance parameters and the actual section performance parameters is correspondingly calculated, specifically, the fitness is calculated according to the following formula:
wherein,
j is the fitness between the calculated section performance parameters and the actual section performance parameters;
n is a section performance parameter;
ejthe deviation of the performance parameter of the j-th section and the performance parameter of the actual section is obtained through calculation.
According to at least one embodiment of the present application, in the above method for determining steady-state model coefficients of a gas turbine, the selecting steady-state model coefficients of the gas turbine from the remaining gas turbine steady-state model coefficient populations specifically includes:
and selecting the steady-state model coefficient of the gas turbine in the steady-state model coefficient population corresponding to the optimal fitness.
Drawings
FIG. 1 is a flow chart of a method for determining steady-state model coefficients for a gas turbine provided by an embodiment of the present application;
fig. 2 is a schematic diagram provided by an embodiment of the present application.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
A method of determining steady-state model coefficients for a gas turbine, comprising:
correspondingly calculating to obtain section performance parameters based on the set steady-state model coefficient population of the gas turbine;
on the basis of the calculated section performance parameters, correspondingly calculating the fitness between the section performance parameters and the actual section performance parameters;
eliminating the gas turbine steady-state model coefficient population corresponding to poor fitness according to the selection probability, performing crossing and variation on the rest gas turbine steady-state model coefficient populations to generate gas turbine steady-state model coefficient sub-populations, and updating the set gas turbine steady-state model coefficient populations by the sub-populations until reaching a genetic algebra;
and selecting the steady-state model coefficients of the gas turbines in the rest gas turbine steady-state model coefficient populations.
For the method for determining the steady-state model coefficient of the gas turbine disclosed in the above embodiment, it can be understood by those skilled in the art that the method is implemented based on a genetic algorithm, and through multiple iterations, a population of the steady-state model coefficient of the gas turbine corresponding to the operation of the gas turbine is quickly searched, and the gas turbine coefficient is selected to perform steady-state simulation on the gas turbine, so that the method has higher accuracy.
For the method for determining the steady-state model coefficient of the gas turbine disclosed in the above embodiments, it can be further understood by those skilled in the art that the method can be implemented based on a MATLAB platform, and the fitness function definition is completed on the SIMULINK platform, so that the method has higher efficiency.
For the method for determining the steady-state model coefficients of the gas turbine disclosed in the above embodiments, it can be understood by those skilled in the art that the number of the set steady-state model coefficient populations of the gas turbine, the selection probability, the cross probability, the variation probability, and the genetic algebra can be determined by those skilled in the art according to the actual situation when applying the present application.
In some optional embodiments, in the above method for determining steady-state model coefficients of a gas turbine, the steady-state model coefficients of the gas turbine in the population of steady-state model coefficients of the gas turbine include a compressor reduced flow rate, a turbine efficiency, and a bleed air quantity of a high-pressure turbine of the gas turbine.
In some optional embodiments, in the above method for determining steady-state model coefficients of a gas turbine, the section performance parameters are the rotation speed, total temperature, total pressure, and power of the gas turbine.
In some optional embodiments, in the above method for determining coefficients of a steady-state model of a gas turbine, the fitness with the actual section performance parameter is correspondingly calculated based on the calculated section performance parameter, specifically, the fitness is calculated according to the following formula:
wherein,
j is the fitness between the calculated section performance parameters and the actual section performance parameters;
n is a section performance parameter;
ejthe deviation of the performance parameter of the j-th section and the performance parameter of the actual section is obtained through calculation.
For the method for determining the steady-state model coefficient of the gas turbine disclosed in the above embodiment, it can be further understood by those skilled in the art that the calculated fitness J between the cross-section performance parameter and the actual cross-section performance parameter indicates that the steady-state simulation of the gas turbine is performed by using the steady-state model coefficient of the gas turbine in the steady-state model coefficient population of the gas turbine, and the smaller the numerical value of the fitness J is, the higher the fitness is, so as to correspond to the steady-state simulation of the gas turbine by using the steady-state model coefficient of the gas turbine in the steady-state model coefficient population of the gas turbine, and the higher the validity of the obtained result is.
In some optional embodiments, in the above method for determining steady-state model coefficients of a gas turbine, the selecting steady-state model coefficients of gas turbines in the remaining gas turbine steady-state model coefficient populations specifically includes:
and selecting the steady-state model coefficient of the gas turbine in the steady-state model coefficient population corresponding to the optimal fitness.
In one embodiment, the variation of the coefficient determination in the steady state model of the gas turbine according to the above method for determining the coefficient of the steady state model of the gas turbine is shown in FIG. 2.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (5)
1. A method for determining steady-state model coefficients for a gas turbine, comprising:
correspondingly calculating to obtain section performance parameters based on the set steady-state model coefficient population of the gas turbine;
on the basis of the calculated section performance parameters, correspondingly calculating the fitness between the section performance parameters and the actual section performance parameters;
eliminating the gas turbine steady-state model coefficient population corresponding to poor fitness according to the selection probability, performing crossing and variation on the rest gas turbine steady-state model coefficient populations to generate gas turbine steady-state model coefficient sub-populations, and updating the set gas turbine steady-state model coefficient populations by the sub-populations until reaching a genetic algebra;
and selecting the steady-state model coefficients of the gas turbines in the rest gas turbine steady-state model coefficient populations.
2. The gas turbine steady-state model coefficient determination method as set forth in claim 1,
and the steady-state model coefficients of the gas turbine in the steady-state model coefficient population of the gas turbine comprise the converted flow of a gas compressor of the gas turbine, the turbine efficiency and the air entraining quantity of the high-pressure turbine.
3. The gas turbine steady-state model coefficient determination method as set forth in claim 1,
the performance parameters of the section are the rotating speed, the total temperature, the total pressure and the power of the gas turbine.
4. The gas turbine steady-state model coefficient determination method as set forth in claim 1,
the fitness between the calculated section performance parameters and the actual section performance parameters is correspondingly calculated based on the calculated section performance parameters, and specifically, the fitness is calculated according to the following formula:
wherein,
j is the fitness between the calculated section performance parameters and the actual section performance parameters;
n is a section performance parameter;
ejthe deviation of the performance parameter of the j-th section and the performance parameter of the actual section is obtained through calculation.
5. The gas turbine steady-state model coefficient determination method as set forth in claim 1,
selecting the gas turbine steady-state model coefficients in the rest gas turbine steady-state model coefficient populations specifically comprises the following steps:
and selecting the steady-state model coefficient of the gas turbine in the steady-state model coefficient population corresponding to the optimal fitness.
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