CN113962026A - Method and device for simulating transition state performance of aviation gas turbine - Google Patents
Method and device for simulating transition state performance of aviation gas turbine Download PDFInfo
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Abstract
The application provides a method and a device for simulating transition state performance of an aviation gas turbine, wherein the method comprises the following steps: acquiring a high-temperature working condition characteristic curve of the gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition reference point, and determining a high-temperature working condition parameter of the high-temperature working condition reference point; determining a target moment corresponding to the low-temperature working condition reference point according to the dimensionless moment consistency of the high-temperature and low-temperature working conditions, and determining low-temperature working condition parameters of the low-temperature working condition reference point according to basic reference quantities corresponding to actual physical conditions; determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point; determining the change rate of the parameter at each moment along with the time change under the low-temperature working condition based on the corresponding relation and the characteristic curve of the high-temperature working condition; and generating working condition parameters of the low-temperature working condition at each moment according to the low-temperature working condition parameters and the change rate of the low-temperature working condition datum points.
Description
Technical Field
The application relates to the field of turbine transition state performance research and test, in particular to a method and a device for similarity of transition state performance of an aviation gas turbine.
Background
The turbine is widely applied to the fields of aerospace, vehicle and ship power, power stations and the like, and the pneumatic performance of the turbine is a key factor influencing the working state and the energy conversion efficiency of an engine. Generally, a turbine aerodynamic performance analysis and design system is established based on a steady-state condition, and a relevant research on turbine transient characteristics in a transition state process is still in a starting stage, so that a relevant experiment aiming at a typical transition state process of a turbine needs to be developed to fully and comprehensively grasp the turbine performance in the transition state process.
In the related art, empire university of science has conducted transient turbine tests of a large number of turbochargers to study the effect of time varying inflow conditions on turbine transient state aerodynamic performance. These tests were conducted on a low temperature turbine test rig with a pulse device to provide periodic time varying inlet air conditions. However, similar guidelines adopted by students at the university of empire and science are based on a steady-state method, and do not consider similar scaling problems on a time scale, which results in obvious differences in transient state characteristics, especially hysteresis effects, under high and low temperature conditions. In addition, relevant research of northern engine research institute in china indicates that when characteristic parameters such as incoming flow temperature/pressure and the like periodically change in a sine function, a corresponding relation of time scales in different working environments can be established by combining criterion Number St (Strhouhal Number) reflecting cycle length and working medium propagation rate. However, the common transient processes of aircraft turbines usually do not have a definite periodicity, and this similar method by St number is not applicable.
At present, the research aiming at the similar transition state in the world is still in the stage of just starting, the theory and the result which can be referred to are difficult to find, which is just the pain point for developing the transition state test of the turbine, and the method for refining the similar transition state suitable for the engineering is urgently needed.
Disclosure of Invention
The application aims to provide a method and a device for simulating transition state performance of an aviation gas turbine, which are used for guiding a turbine transition state characteristic experiment under a medium-temperature and medium-pressure condition.
The application provides a method for simulating transition state performance of an aircraft gas turbine, which comprises the following steps: acquiring a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of the transition state process of the high-temperature working condition of the aviation gas turbine; taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition reference point, and determining a high-temperature working condition parameter of the high-temperature working condition reference point; determining a target moment corresponding to a low-temperature working condition datum point according to the dimensionless moment consistency of the high-temperature and low-temperature working conditions, and determining a low-temperature working condition parameter of the low-temperature working condition datum point according to a basic reference quantity corresponding to an actual physical condition; based on a similar method, the target parameter of the low-temperature working condition at the target moment is the same as the target parameter of the high-temperature working condition reference point; determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point; the low-temperature working condition characteristic curve is obtained based on the low-temperature working condition parameters; determining the change rate of the parameter at each moment along with the change of time under the low-temperature working condition based on the corresponding relation and the characteristic curve of the high-temperature working condition; generating working condition parameters of the low-temperature working condition at each moment according to the low-temperature working condition parameters of the low-temperature working condition datum points and the change rate; wherein the basic reference amounts comprise at least one of: a reference dimension, a reference speed, a reference temperature, a reference pressure; the target parameter includes at least one of: expansion ratio, reduced rotational speed, and exit mach number.
Optionally, the operating condition parameter includes at least one of: outlet back pressure, inlet total temperature, inlet airflow angle and rotation speed; the determining the low-temperature working condition parameters of the low-temperature working condition datum points according to the basic reference quantity corresponding to the actual physical conditions comprises the following steps: and determining the total inlet pressure and the rotating speed of the low-temperature working condition reference point according to the total inlet pressure and the outlet back pressure of the low-temperature working condition reference point.
Optionally, the similar method is based on consistency of time-varying solution conditions between the high-temperature condition and the low-temperature condition in a dimensionless manner.
Optionally, the time-varying solution condition comprises at least one of: outlet back pressure, inlet total temperature, inlet airflow angle and rotation speed.
The present application further provides an aircraft gas turbine transition state performance similarity device, comprising: the acquiring module is used for extracting working condition parameters of the high-temperature working condition transition state process of the aviation gas turbine and acquiring a high-temperature working condition characteristic curve of the gas turbine; the determining module is used for taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition reference point and determining a high-temperature working condition parameter of the high-temperature working condition reference point; the determining module is further used for determining a target moment corresponding to the low-temperature working condition reference point according to the consistency of the dimensionless moments of the high-temperature and low-temperature working conditions, and determining the low-temperature working condition parameters of the low-temperature working condition reference point according to the basic reference quantity corresponding to the actual physical conditions; based on a similar method, the target parameter of the low-temperature working condition at the target moment is the same as the target parameter of the high-temperature working condition reference point; the determining module is further used for determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point; the low-temperature working condition characteristic curve is obtained based on the low-temperature working condition parameters; the determining module is further used for determining the change rate of the parameter at each moment under the low-temperature working condition along with the change of time based on the corresponding relation and the high-temperature working condition characteristic curve; the generating module is used for generating working condition parameters of the low-temperature working condition at all times according to the low-temperature working condition parameters of the low-temperature working condition datum points and the change rate; wherein the target parameters include at least one of: expansion ratio, reduced rotational speed, and exit mach number.
Optionally, the operating condition parameter includes at least one of: inlet total temperature, outlet back pressure, inlet total pressure and rotating speed; the determining module is specifically configured to determine the total inlet pressure and the rotational speed of the low-temperature working condition reference point according to the total inlet pressure and the outlet backpressure of the low-temperature working condition reference point.
Optionally, the similar method is based on consistency of time-varying solution conditions between the high-temperature condition and the low-temperature condition in a dimensionless manner.
Optionally, the time-varying solution condition comprises at least one of: outlet back pressure, inlet total temperature, inlet airflow angle and rotation speed.
The present application also provides a computer program product comprising computer programs/instructions which, when executed by a processor, perform the steps of the aero gas turbine transition state performance similarity method as any one of the above.
The present application further provides an electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing the steps of the method for similarity of transition state performance of an aircraft gas turbine as described in any of the above when executing the program.
The present application also provides a non-transitory computer readable storage medium having stored thereon a computer program which, when executed by a processor, performs the steps of the aircraft gas turbine transition state performance similarity method as any of the above.
According to the method and the device for simulating the transition state performance of the aviation gas turbine, the problem of similarity of time scales in the transition state process is considered, so that the hysteresis effect and the filling emptying effect in the transition state process of the turbine can be modeled more accurately. Meanwhile, the method can be widely applied to various typical transition state processes of various turbines, the form of the criterion is directly related to the aerodynamic performance of the turbine, and the method has engineering value and can be applied to actual turbine transition state experiments. Moreover, when the transient state process is a periodic variation process or is approximately regarded as a steady state process, the method can also be degenerated to a periodic or steady state similar method, in other words, the periodic/steady state similar method is a special form of the transient state similar method.
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In order to more clearly illustrate the technical solutions in the present application or the prior art, the drawings needed for the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic flow diagram of an aircraft gas turbine transition state performance similarity method provided herein;
FIG. 2 is a schematic diagram of time-varying input parameters under high and low temperature conditions on a dimensional scale;
FIG. 3 is a schematic diagram of time-varying input parameters under high and low temperature conditions on a dimensionless scale;
FIG. 4 is a comparison graph of parameter curves before and after similar modeling in two similar methods provided herein;
FIG. 5 is a comparison graph of similarity accuracy for two similar methods provided herein;
FIG. 6 is a schematic structural view of an aircraft gas turbine transient state performance similarity apparatus provided herein;
fig. 7 is a schematic structural diagram of an electronic device provided in the present application.
Detailed Description
To make the purpose, technical solutions and advantages of the present application clearer, the technical solutions in the present application will be clearly and completely described below with reference to the drawings in the present application, and it is obvious that the described embodiments are some, but not all embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The terms first, second and the like in the description and in the claims of the present application are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It will be appreciated that the data so used may be interchanged under appropriate circumstances such that embodiments of the application may be practiced in sequences other than those illustrated or described herein, and that the terms "first," "second," and the like are generally used herein in a generic sense and do not limit the number of terms, e.g., the first term can be one or more than one. In addition, "and/or" in the specification and claims means at least one of connected objects, a character "/" generally means that a preceding and succeeding related objects are in an "or" relationship.
Turbofan engines are the most central components of an aircraft, and their operating conditions directly determine the stability and safety of the entire aircraft. The performance of the turbofan engine in the transition state directly influences the performance of the airplane such as takeoff, acceleration, maneuvering flight and the like.
Aiming at the condition that similar research of the transition state of the gas turbine does not have available reference research success at present, the technical scheme provided by the embodiment of the application can be used for guiding the characteristic experiment of the transition state of the turbine under the condition of medium temperature and medium pressure.
The method for simulating the transition state performance of the aviation gas turbine provided by the embodiment of the application is described in detail through specific embodiments and application scenarios thereof with reference to the attached drawings.
As shown in fig. 1, an aircraft gas turbine transient state performance similarity method provided by an embodiment of the present application may include the following steps 101 to 105:
Illustratively, the high-temperature operating condition characteristic curve of the gas turbine is an aerodynamic parameter obtained by the gas turbine under the real high-temperature operating condition.
For example, the high temperature condition reference point may be any time during the transient state of the gas turbine, and in actual operation, for convenience of calculation, the starting point of the transient state process is usually selected as the high temperature condition reference point.
Illustratively, the high temperature condition parameters may include at least one of: outlet back pressure, inlet total temperature, inlet airflow angle, rotation speed, expansion ratio and reduced rotation speed.
For example, to facilitate understanding, the following Table 1 provides parameters for a typical transition state process for certain types of turbine high temperature conditions:
TABLE 1
It should be noted that, in the experimental process, the above parameters can be calculated according to the basic reference amount. The above-mentioned basic reference amounts include at least one of: reference dimension LrefReference speed urefReference temperature TrefReference pressure Pref. The total inlet temperature, the outlet back pressure, the total inlet pressure, the rotating speed, the expansion ratio and the reduced rotating speed can be calculated according to the basic reference quantity. The ref indicates that the parameter is a parameter. The parameters can be selected according to actual needs, but the consistency between high-temperature and low-temperature working conditions needs to be ensured.
And 102, determining a target moment corresponding to the low-temperature working condition reference point according to the dimensionless moment consistency of the high-temperature and low-temperature working conditions, and determining the low-temperature working condition parameters of the low-temperature working condition reference point according to the basic reference quantity.
And based on a similar method, the target parameter of the low-temperature working condition at the target moment is the same as the target parameter of the high-temperature working condition reference point. The base reference quantity comprises at least one of: a reference dimension, a reference speed, a reference temperature, a reference pressure; the target parameter includes at least one of: expansion ratio, reduced rotational speed, and exit mach number.
Illustratively, the similar method relies on the consistency of the time-varying solution conditions between the high-temperature and low-temperature conditions in a dimensionless fashion. The time-varying solution condition includes at least one of: outlet back pressure, inlet total temperature, inlet airflow angle and rotation speed. The establishment of the similar method does not depend on the specific selection mode of the reference point time and the parameters.
Illustratively, the reference point of the low temperature condition is selected according to the limit of the actual test condition, namely the time of any low temperature condition under the limit of the actual test condition. Based on a similar method, the parameters of the expansion ratio, the reduced rotating speed, the outlet Mach number and the like of the high-temperature working condition reference point and the low-temperature working condition reference point are equal.
It should be noted that the similarity criterion (i.e. the above-mentioned similarity method) is also called "similarity parameter", "similarity modulus", "similarity criterion", etc., and is a concept used in judging the similarity between two physical phenomena, and is currently widely applied in modeling experiments. In fluid mechanics, flow field similarity includes geometric similarity, motion similarity and power similarity, wherein the geometric similarity requires that the geometric shapes of the flow fields are the same and the sizes are in proportion; the motion similarity requires that the speed directions of all corresponding points in the flow field are consistent and the sizes are proportional; the dynamic similarity requires that the stress types of all corresponding points in the flow field are the same, the directions are consistent, the magnitudes are proportional, and the stress types can be equivalently converted into the consistency of relevant dimensionless criterion numbers.
In one implementation, a reference pressure and a reference temperature may be selected and based on similar methods, a total inlet temperature and an outlet back pressure for low temperature conditions are determined.
Illustratively, the step 102 may include the following steps 102 a:
and 102a, determining the total inlet pressure and the rotating speed of the low-temperature working condition reference point according to the total inlet pressure and the outlet back pressure of the low-temperature working condition reference point.
Specifically, the inlet airflow angle is equal and geometrically consistent between the high and low temperature working conditions at any moment, the working medium is complete gas with the same molar mass, the specific heat of the working medium is consistent at the same dimensionless moment between the high and low temperature working conditions, the working point is located in a self-molding area, the wall surface is adiabatic, and the dimensionless inlet total temperature and the outlet back pressure of the datum point between the high and low temperature working conditions meet the following requirements under the assumption that the gravity is ignored:
exemplarily, after the total inlet pressure and the outlet back pressure of the low-temperature working condition reference point are obtained, the expansion ratio, the reduced rotation speed and the outlet mach number of the high-temperature working condition reference point are ensured to be equal according to a similar method, namely:
the total inlet pressure and the rotating speed of the low-temperature working condition datum point can be obtained. At this time, all the parameters of the low-temperature condition reference point are acquired.
103, determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point.
And the low-temperature working condition characteristic curve is obtained based on the low-temperature working condition parameters.
Illustratively, after the parameters of the low-temperature working condition datum point are obtained, the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point are selected according to actual conditions, and the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale is determined according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point.
Specifically, the time scale corresponds to the following:
and 104, determining the change rate of the parameter at each moment under the low-temperature working condition along with the change of time based on the corresponding relation and the high-temperature working condition characteristic curve.
Illustratively, on the basis of obtaining the time scale corresponding relation, a characteristic curve of the high-temperature working condition (which can also be called as a dimensionless parameter curve of the high-temperature working condition) is combined, and according to a similar method, the dimensionless outlet back pressure, the expansion ratio, the dimensionless inlet total temperature and the change rate of the reduced rotating speed along with the change of time are determined:
and 105, generating working condition parameters of the low-temperature working condition at each moment according to the low-temperature working condition parameters of the low-temperature working condition datum points and the change rate.
Illustratively, after the change rate is obtained, the parameters of the low-temperature working condition at each moment are obtained by combining the low-temperature working condition parameters of the low-temperature working condition datum points and the following formula. Wherein, the parameter of each moment under the low temperature operating mode includes: and aerodynamic parameters at various moments under low-temperature working conditions.
Illustratively, the following table 2 is a comparison of the obtained aerodynamic parameters for the start and end points of the high and low temperature conditions:
TABLE 2
Illustratively, by a similar approach, a pneumatic parameter profile for low temperature conditions has been obtained. Fig. 2 and 3 are pneumatic parameter curves of high and low temperature working conditions with dimension and non-dimension respectively.
Illustratively, in order to verify the transition state similarity method, a typical transition state process of a certain type of turbine is taken as an example, a URANS equation set is solved by using commercial numerical simulation software ANSYS CFX, and the similarity precision of different similarity methods is analyzed.
In the numerical simulation calculation, an SST k-omega model is adopted as a turbulence model, a second-order windward format is adopted for space dispersion, and a second-order Euler posterior difference format is adopted for time dispersion.
In the process of high-temperature working condition transition state numerical simulation, the total inlet temperature, the total inlet pressure and the set rotating speed are periodically changed along with time, so that the average result of corresponding phases of a plurality of periods can be conveniently obtained to improve the similarity precision. The average value of the periodic variation of each parameter is consistent with the parameter of the design point, and the working range of the transition state is ensured to be basically positioned in the working envelope of the actual turbine.
And respectively adopting a transition state similarity method and a steady state similarity method to obtain time-varying edge strip parameters corresponding to the low-temperature working condition. Based on the method, the transition state numerical simulation of the high-temperature transition state process, the low-temperature transition state process obtained by modeling by adopting a transition state similarity method and the low-temperature transition state process obtained by modeling by adopting a steady-state similarity method is completed, and the similarity precision of the two methods is analyzed by comparing the parameter curves of the three transition state processes.
The comparison of the low-temperature working condition transition state parameter curve and the high-temperature working condition parameter curve obtained by two similar modeling methods is shown in FIG. 4. Therefore, the low-temperature working condition reduced power, the fitting degree of the airflow angle and relative Mach number curve and the high-temperature working condition curve obtained by the transition state similarity method are far higher than those obtained by the steady-state method, and the accuracy of the transition state similarity method is proved.
In order to compare the similar accuracy of the two similar methods more intuitively, the following definition formulas of the maximum difference and the average difference between the pneumatic parameters under the high-temperature and low-temperature working conditions are given.
Maximum deviation of reduced work/relative mach number:
reduced work/relative mach number average deviation:
maximum deviation of airflow angle:
MaxDiff(α)＝maxT|αtest-αori|
average deviation of airflow angle:
fig. 5 shows the maximum deviation and the average deviation of the transient state and the steady state similar method, and it can be seen that the similarity precision of the transient state similar method is improved by one order of magnitude compared with that of the steady state method, which proves the advantages of the transient state similar method.
Of course, the similarity method is not limited to a single model turbine or a single transition state process, the proposed transition state similarity relation can be generally applied to typical transition state processes of various turbines, and the relation between the prototype transition state and the intermediate-temperature and intermediate-pressure condition transition state turbine experiment is established through the similarity method.
Optionally, the non-dimensional form of the time-varying solution condition includes a functional relationship between parameters under high and low temperature conditions, including:
dimensionless outlet back pressure:
dimensionless inlet total pressure:
dimensionless total inlet temperature:
inlet airflow angle:
dimensionless rotational speed:
n*(t*)|ori＝n*(t*)|testformula six
Wherein ori represents a parameter under a high-temperature working condition, and test represents a parameter under a low-temperature working condition; denotes a dimensionless parameter, t denotes a dimensionless time; p2For outlet back pressure, P1tIs the total inlet pressure, T1tIs the total inlet temperature, alphaxyAnd alphaxzIs the inlet flow angle and n is the rotational speed.
Optionally, the functional relationship of the dimensionless outlet back pressure is converted by reducing the dimensional equivalence into:
wherein, PrefThe reference pressure is indicated.
Optionally, the functional relationship of the dimensionless inlet total pressure is converted into:
according to the formula seven, equivalently converting the formula eight into the following formula nine:
wherein, pit＝P1t/P2tIs the total expansion ratio of the turbine;
the calculation formula of the outlet mach number is the following formula ten:
the result of the equation ten is equal to the ratio of the exit static pressure to the total pressure.
Optionally, the functional relationship of the dimensionless import total temperature is converted into:
wherein, TrefA reference temperature is identified.
Optionally, the functional relationship of the dimensionless rotational speed is converted into:
wherein n isrefFor reference speed, defined as:
wherein u isrefDenotes a reference speed, LrefDenotes a reference length, γrefRepresents a reference specific heat; k is a radical ofuRepresenting the speed coefficient, representing the rotor tangential speed and the reference speed urefThe ratio of (A) to (B); k is a radical ofLIs a length coefficient representing the mean revolution of the rotor and a referenceLength LrefThe ratio of (A) to (B);
according to the above relation, the function relation of the dimensionless rotation speed can be equivalently converted into:
namely, it is
According to the function relation formula eleven of the dimensionless inlet total temperature, the formula sixteen can be equivalently converted into:
optionally, the parameter is a pneumatic parameter, and the change rate is a change rate of the pneumatic parameter;
the corresponding relation of the physical time scale between the high-temperature working condition and the low-temperature working condition meets the following requirements:
wherein t is physical time, and t is dimensionless time;
at the same time, for any dimensionless time, the time-varying aerodynamic parameters
At any time teTime can be written about a reference time tsExpression of aerodynamic parameters and rate of change of aerodynamic parameters:
optionally, when the inlet airflow angle is equal under the high-temperature and low-temperature working conditions at any moment, the working medium is completely gas, the working point is located in the self-molding area, and the dimensionless criterion number can be equivalently converted into the following values under the assumption that the wall surface is insulated and the gravity is ignored:
optionally, under the assumption that the added high-low temperature working condition is the same working medium with the same specific heat at the corresponding dimensionless time scale, and the scale ratio is 1, the dimensionless criterion number can be equivalently converted into:
according to the method for simulating the transition state performance of the aviation gas turbine, the problem of similarity of time scales in the transition state process is considered, so that the hysteresis effect and the filling emptying effect in the transition state process of the turbine can be modeled more accurately. Meanwhile, the method can be widely applied to various typical transition state processes of various turbines, the form of the criterion is directly related to the aerodynamic performance of the turbine, and the method has engineering value and can be applied to actual turbine transition state experiments. Moreover, when the transient state process is a periodic variation process or is approximately regarded as a steady state process, the method can also be degenerated to a periodic or steady state similar method, in other words, the periodic/steady state similar method is a special form of the transient state similar method.
It should be noted that, in the aircraft gas turbine transient state performance similarity method provided by the embodiment of the present application, the execution subject may be an aircraft gas turbine transient state performance similarity device, or a control module in the aircraft gas turbine transient state performance similarity device, for executing the aircraft gas turbine transient state performance similarity method. In the embodiment of the present application, an aircraft gas turbine transition state performance similarity method executed by an aircraft gas turbine transition state performance similarity device is taken as an example, and the aircraft gas turbine transition state performance similarity device provided by the embodiment of the present application is described.
It should be noted that, in the embodiments of the present application, the methods for simulating the transient state performance of the aircraft gas turbine shown in the above-mentioned method drawings are exemplarily described by combining one drawing in the embodiments of the present application. In specific implementation, the methods for simulating the transition state performance of the aviation gas turbine shown in the above method drawings can also be implemented by combining any other drawings which can be combined and are illustrated in the above embodiments, and are not described herein again.
As provided herein below, the methods described below and similar to the aero gas turbine transition state performance described above may be referenced in correspondence with one another.
Fig. 6 is a schematic structural diagram of a device similar to the aircraft gas turbine in the transition state performance provided in an embodiment of the present application, and as shown in fig. 6, the device specifically includes:
the obtaining module 601 is used for obtaining a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of the high-temperature working condition transition state process of the aviation gas turbine; a determining module 602, configured to use any time in the high-temperature operating condition characteristic curve as a high-temperature operating condition reference point, and determine a high-temperature operating condition parameter of the high-temperature operating condition reference point; the high-temperature working condition characteristic curve is obtained based on working condition parameters of a high-temperature working condition transition state process of the gas turbine; the determining module 602 is further configured to determine a target time corresponding to the low-temperature working condition reference point according to the consistency of the dimensionless times of the high-temperature and low-temperature working conditions, and determine a low-temperature working condition parameter of the low-temperature working condition reference point according to a basic reference amount corresponding to an actual physical condition; based on a similar method, the target parameter of the low-temperature working condition at the target moment is the same as the target parameter of the high-temperature working condition reference point; the determining module 602 is further configured to determine a corresponding relationship between the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on a time scale according to the reference temperature of the high-temperature working condition reference point and the reference temperature of the low-temperature working condition reference point; the low-temperature working condition characteristic curve is obtained based on the low-temperature working condition parameters; the determining module 602 is further configured to determine a change rate of the parameter at each time under the low-temperature working condition along with the change of time based on the corresponding relationship and the characteristic curve of the high-temperature working condition; a generating module 603, configured to generate a working condition parameter at each time of the low-temperature working condition according to the low-temperature working condition parameter of the low-temperature working condition reference point and the change rate; wherein the target parameters include at least one of: expansion ratio, reduced rotational speed, and exit mach number.
Optionally, the operating condition parameter includes at least one of: outlet back pressure, inlet total temperature, inlet airflow angle and rotation speed; the determining module is specifically configured to determine the total inlet pressure and the rotational speed of the low-temperature working condition reference point according to the total inlet pressure and the outlet backpressure of the low-temperature working condition reference point.
Optionally, the similar method is based on consistency of time-varying solution conditions between the high-temperature condition and the low-temperature condition in a dimensionless manner.
Optionally, the time-varying solution condition comprises at least one of: outlet back pressure, inlet total temperature, inlet airflow angle and rotation speed.
Optionally, the non-dimensional form of the time-varying solution condition includes a functional relationship between parameters under high and low temperature conditions, including:
dimensionless outlet back pressure:
dimensionless inlet total pressure:
dimensionless total inlet temperature:
inlet airflow angle:
αxy(t*)|ori＝αxy(t*)|testformula four
αxz(t*)|ori＝αxz(t*)|testFormula five
Dimensionless rotational speed:
n*(t*)|ori＝n*(t*)|testformula six
Wherein ori represents a parameter under a high-temperature working condition, and test represents a parameter under a low-temperature working condition; denotes a dimensionless parameter, t denotes a dimensionless time; p2For outlet back pressure, P1tIs the total inlet pressure, T1tIs the total inlet temperature, alphaxyAnd alphaxzIs the inlet flow angle and n is the rotational speed.
Optionally, the functional relationship of the dimensionless outlet back pressure is converted by reducing the dimensional equivalence into:
wherein, PrefThe reference pressure is indicated.
Optionally, the functional relationship of the dimensionless inlet total pressure is converted into:
according to the formula seven, equivalently converting the formula eight into the following formula nine:
wherein, pit＝P1t/P2tIs the total expansion ratio of the turbine;
the calculation formula of the outlet mach number is the following formula ten:
the result of the equation ten is equal to the ratio of the exit static pressure to the total pressure.
Optionally, the functional relationship of the dimensionless import total temperature is converted into:
wherein, TrefA reference temperature is identified.
Optionally, the functional relationship of the dimensionless rotational speed is converted into:
wherein n isrefFor reference speed, defined as:
wherein u isrefDenotes a reference speed, LrefDenotes a reference length, γrefRepresents a reference specific heat; k is a radical ofuRepresenting speed coefficient, representing rotor sectionVelocity of the direction and reference velocity urefThe ratio of (A) to (B); k is a radical ofLIs a length coefficient representing the mean revolution circumference of the rotor and a reference length LrefThe ratio of (A) to (B);
according to the above relation, the function relation of the dimensionless rotation speed can be equivalently converted into:
namely, it is
According to the function relation formula eleven of the dimensionless inlet total temperature, the formula sixteen can be equivalently converted into:
optionally, the parameter is a pneumatic parameter, and the change rate is a change rate of the pneumatic parameter;
the corresponding relation of the physical time scale between the high-temperature working condition and the low-temperature working condition meets the following requirements:
wherein t is physical time, and t is dimensionless time;
at the same time, for any dimensionless time, the time-varying aerodynamic parameters
At any time teTime can be written about a reference time tsExpression of aerodynamic parameters and rate of change of aerodynamic parameters:
optionally, when the inlet airflow angle is equal under the high-temperature and low-temperature working conditions at any moment, the working medium is completely gas, the working point is located in the self-molding area, and the dimensionless criterion number can be equivalently converted into the following values under the assumption that the wall surface is insulated and the gravity is ignored:
optionally, under the assumption that the added high-low temperature working condition is the same working medium with the same specific heat at the corresponding dimensionless time scale, and the scale ratio is 1, the dimensionless criterion number can be equivalently converted into:
the aviation gas turbine transition state performance similarity device provided by the application considers the similarity problem of time scale in the transition state process, so that the hysteresis effect and the filling emptying effect in the turbine transition state process can be modeled more accurately. Meanwhile, the method can be widely applied to various typical transition state processes of various turbines, the form of the criterion is directly related to the aerodynamic performance of the turbine, and the method has engineering value and can be applied to actual turbine transition state experiments. Moreover, when the transient state process is a periodic variation process or is approximately regarded as a steady state process, the method can also be degenerated to a periodic or steady state similar method, in other words, the periodic/steady state similar method is a special form of the transient state similar method.
Fig. 7 illustrates a physical structure diagram of an electronic device, and as shown in fig. 7, the electronic device may include: a processor (processor)510, a communication Interface (Communications Interface)520, a memory (memory)430 and a communication bus 540, wherein the processor 510, the communication Interface 520 and the memory 530 are communicated with each other via the communication bus 540. Processor 510 may invoke logic instructions in memory 530 to perform an aircraft gas turbine transition state performance similarity method comprising: acquiring a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of the transition state process of the high-temperature working condition of the aviation gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition reference point, and determining the high-temperature working condition parameters of the high-temperature working condition reference point; determining a target moment corresponding to a low-temperature working condition datum point according to the dimensionless moment consistency of the high-temperature and low-temperature working conditions, and determining a low-temperature working condition parameter of the low-temperature working condition datum point according to a basic reference quantity corresponding to an actual physical condition; based on a similar method, the target parameter of the low-temperature working condition at the target moment is the same as the target parameter of the high-temperature working condition reference point; determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point; the low-temperature working condition characteristic curve is obtained based on the low-temperature working condition parameters; determining the change rate of the parameter at each moment along with the change of time under the low-temperature working condition based on the corresponding relation and the characteristic curve of the high-temperature working condition; generating working condition parameters of the low-temperature working condition at each moment according to the low-temperature working condition parameters of the low-temperature working condition datum points and the change rate; wherein the basic reference amounts comprise at least one of: a reference dimension, a reference speed, a reference temperature, a reference pressure; the target parameter includes at least one of: expansion ratio, reduced rotational speed, and exit mach number.
Furthermore, the logic instructions in the memory 530 may be implemented in the form of software functional units and stored in a computer readable storage medium when the software functional units are sold or used as independent products. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
In another aspect, the present application also provides a computer program product comprising a computer program stored on a non-transitory computer readable storage medium, the computer program comprising program instructions which, when executed by a computer, enable the computer to perform a method for similarity of transition states of an aircraft gas turbine provided by the above methods, the method comprising: acquiring a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of the transition state process of the high-temperature working condition of the aviation gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition reference point, and determining the high-temperature working condition parameters of the high-temperature working condition reference point; determining a target moment corresponding to a low-temperature working condition datum point according to the dimensionless moment consistency of the high-temperature and low-temperature working conditions, and determining a low-temperature working condition parameter of the low-temperature working condition datum point according to a basic reference quantity corresponding to an actual physical condition; based on a similar method, the target parameter of the low-temperature working condition at the target moment is the same as the target parameter of the high-temperature working condition reference point; determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point; the low-temperature working condition characteristic curve is obtained based on the low-temperature working condition parameters; determining the change rate of the parameter at each moment along with the change of time under the low-temperature working condition based on the corresponding relation and the characteristic curve of the high-temperature working condition; generating working condition parameters of the low-temperature working condition at each moment according to the low-temperature working condition parameters of the low-temperature working condition datum points and the change rate; wherein the basic reference amounts comprise at least one of: a reference dimension, a reference speed, a reference temperature, a reference pressure; the target parameter includes at least one of: expansion ratio, reduced rotational speed, and exit mach number.
In yet another aspect, the present application also provides a non-transitory computer readable storage medium having stored thereon a computer program that, when executed by a processor, is implemented to perform the method of providing an aircraft gas turbine transient state performance similarity as described above, the method comprising: acquiring a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of the transition state process of the high-temperature working condition of the aviation gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition reference point, and determining the high-temperature working condition parameters of the high-temperature working condition reference point; determining a target moment corresponding to a low-temperature working condition datum point according to the dimensionless moment consistency of the high-temperature and low-temperature working conditions, and determining a low-temperature working condition parameter of the low-temperature working condition datum point according to a basic reference quantity corresponding to an actual physical condition; based on a similar method, the target parameter of the low-temperature working condition at the target moment is the same as the target parameter of the high-temperature working condition reference point; determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point; the low-temperature working condition characteristic curve is obtained based on the low-temperature working condition parameters; determining the change rate of the parameter at each moment along with the change of time under the low-temperature working condition based on the corresponding relation and the characteristic curve of the high-temperature working condition; generating working condition parameters of the low-temperature working condition at each moment according to the low-temperature working condition parameters of the low-temperature working condition datum points and the change rate; wherein the basic reference amounts comprise at least one of: a reference dimension, a reference speed, a reference temperature, a reference pressure; the target parameter includes at least one of: expansion ratio, reduced rotational speed, and exit mach number.
The above-described embodiments of the apparatus are merely illustrative, and the units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware. With this understanding in mind, the above-described technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium such as ROM/RAM, magnetic disk, optical disk, etc., and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods described in the embodiments or some parts of the embodiments.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions in the embodiments of the present application.
Claims (14)
1. A method of transition state performance similarity for an aircraft gas turbine, comprising:
acquiring a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of the transition state process of the high-temperature working condition of the aviation gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition reference point, and determining the high-temperature working condition parameters of the high-temperature working condition reference point;
determining a target moment corresponding to a low-temperature working condition datum point according to the dimensionless moment consistency of the high-temperature and low-temperature working conditions, and determining a low-temperature working condition parameter of the low-temperature working condition datum point according to a basic reference quantity corresponding to an actual physical condition; based on a similar method, the target parameter of the low-temperature working condition at the target moment is the same as the target parameter of the high-temperature working condition reference point;
determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point; the low-temperature working condition characteristic curve is obtained based on the low-temperature working condition parameters;
determining the change rate of the parameter at each moment along with the change of time under the low-temperature working condition based on the corresponding relation and the characteristic curve of the high-temperature working condition;
generating working condition parameters of the low-temperature working condition at each moment according to the low-temperature working condition parameters of the low-temperature working condition datum points and the change rate;
wherein the basic reference amounts comprise at least one of: a reference dimension, a reference speed, a reference temperature, a reference pressure; the target parameter includes at least one of: expansion ratio, reduced rotational speed, and exit mach number.
2. The method of claim 1, wherein the operating condition parameters include at least one of: outlet back pressure, inlet total temperature, inlet airflow angle and rotation speed;
the determining the low-temperature working condition parameters of the low-temperature working condition datum points according to the basic reference quantity corresponding to the actual physical conditions comprises the following steps:
and determining the total inlet pressure and the rotating speed of the low-temperature working condition reference point according to the total inlet pressure and the outlet back pressure of the low-temperature working condition reference point.
3. The method of claim 1, wherein the similarity method is based on consistency of time-varying solution conditions between the high-temperature condition and the low-temperature condition in a dimensionless manner.
4. The method of claim 3, wherein the time-varying solution condition comprises at least one of: outlet back pressure, inlet total temperature, inlet airflow angle and rotation speed.
5. The method of claim 4, wherein the non-dimensional form of the time-varying solution condition is a functional relationship between parameters under high and low temperature conditions, and comprises:
dimensionless outlet back pressure:
dimensionless inlet total pressure:
dimensionless total inlet temperature:
inlet airflow angle:
αxy(t*)|ori＝αxy(t*)|testformula four
αxz(t*)|ori＝αxz(t*)|testFormula five
Dimensionless rotational speed:
n*(t*)|ori＝n*(t*)|testformula six
Wherein ori represents a parameter under a high-temperature working condition, and test represents a parameter under a low-temperature working condition; denotes a dimensionless parameter, t denotes a dimensionless time; p is a radical of2For outlet back pressure, p1tIs the total inlet pressure, T1tIs the total inlet temperature, alphaxyAnd alphaxzIs the inlet flow angle and n is the rotational speed.
6. The method of claim 5, wherein the first functional equation for the dimensionless outlet back pressure is converted by reducing the dimensional equivalence to:
wherein p isrefThe reference pressure is indicated.
7. The method of claim 6, wherein the functional formula for the dimensionless inlet total pressure is converted by reducing the dimensional equivalence to:
according to the formula seven, equivalently converting the formula eight into the following formula nine:
wherein, pit＝p1t/p2tIs the total expansion ratio of the turbine;
the calculation formula of the outlet mach number is the following formula ten:
the result of the equation ten is equal to the ratio of the exit static pressure to the total pressure.
8. The method of claim 5, wherein the non-dimensional inlet total temperature functional equation translates through a reduction dimension equivalent to:
wherein, TrefIndicating the reference temperature.
9. The method of claim 8, wherein the non-dimensional functional equation of rotational speed is converted to:
wherein n isrefFor reference speed, defined as:
wherein u isrefDenotes a reference speed, LrefDenotes a reference length, γrefRepresents a reference specific heat; k is a radical ofuRepresenting the speed coefficient, representing the rotor tangential speed and the reference speed urefThe ratio of (A) to (B); k is a radical ofLIs a length coefficient representing the mean revolution circumference of the rotor and a reference length LrefThe ratio of (A) to (B); according to the similarity relation, the speed coefficient and the length coefficient are consistent between the working conditions which are similar to each other.
According to the above relation, the functional relation formula of the dimensionless rotating speed is transformed into:
namely, it is
According to the function relation formula eleven of the dimensionless inlet total temperature, the formula sixteen can be equivalently converted into:
10. the method of claim 5, wherein the parameter is a pneumatic parameter and the rate of change is a rate of change of the pneumatic parameter;
the corresponding relation of the physical time scale between the high-temperature working condition and the low-temperature working condition meets the following requirements:
wherein t is physical time, and t is dimensionless time;
at the same time, for any dimensionless moment, the time-varying aerodynamic parameter
At any one of teTime can be written about a reference time tsExpression of aerodynamic parameters and rate of change of aerodynamic parameters:
11. the method as claimed in any one of claims 5 to 10, wherein, in the case of ensuring equal inlet gas flow angles between the high and low temperature operating conditions at any one time, the working fluid is a complete gas, the operating point is located in the self-mode region, the wall surface is insulated and the gravity is ignored, and dimensionless criterion numbers can be equivalently converted into:
12. the method according to claim 11, wherein under the assumption that the added high and low temperature working conditions are the same working media with the same specific heat at the corresponding dimensionless time, and the scale ratio is 1, the dimensionless criterion number can be equivalently converted into:
13. the method of claim 11, wherein the similarity method is performed independent of the reference time and the specific selection of the basic reference.
14. An aircraft gas turbine transient state performance similarity apparatus, the apparatus comprising:
the acquiring module is used for acquiring a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of the transition state process of the high-temperature working condition of the aviation gas turbine;
the determining module is used for taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition reference point and determining a high-temperature working condition parameter of the high-temperature working condition reference point;
the determining module is further used for determining a target moment corresponding to the low-temperature working condition reference point according to the consistency of the dimensionless moments of the high-temperature and low-temperature working conditions, and determining the low-temperature working condition parameters of the low-temperature working condition reference point according to the basic reference quantity corresponding to the actual physical conditions; based on a similar method, the target parameters of the low-temperature working condition datum point and the high-temperature working condition datum point are the same;
the determining module is further used for determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point; the low-temperature working condition characteristic curve is obtained based on the low-temperature working condition parameters;
the determining module is further used for determining the change rate of the parameter at each moment under the low-temperature working condition along with the change of time based on the corresponding relation and the high-temperature working condition characteristic curve;
the generating module is used for generating working condition parameters of the low-temperature working condition at all times according to the low-temperature working condition parameters of the low-temperature working condition datum points and the change rate;
wherein the basic reference amounts comprise at least one of: a reference dimension, a reference speed, a reference temperature, a reference pressure; the target parameter includes at least one of: expansion ratio, reduced rotational speed, and exit mach number.
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