CN113962026B - Method and device for similar transitional state performance of aviation gas turbine - Google Patents
Method and device for similar transitional state performance of aviation gas turbine Download PDFInfo
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Abstract
The application provides a method and a device for similar transitional 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 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 consistency of dimensionless moments of the high-temperature working condition and the low-temperature working condition datum point, 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; determining the corresponding relation 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 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 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 all moments according to the low-temperature working condition parameters and the change rate of the low-temperature working condition datum point.
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 aviation gas turbine transition state performance similarity.
Background
The turbine is widely applied to the fields of aerospace, vehicle and ship power, power stations and the like, and the aerodynamic performance of the turbine is a key factor influencing the working state of an engine and the energy conversion efficiency. Generally, a turbine aerodynamic performance analysis and design system is established under steady-state conditions, and a related study on transient characteristics of a turbine in a transient state process is still in a starting stage, so that a related experiment aiming at a typical transient state process of the turbine needs to be carried out to fully and comprehensively grasp the turbine performance in the transient state process.
In the related field, the empire university has developed a large number of transient turbine tests of turbochargers to study the effect of time-varying incoming flow conditions on the aerodynamic performance of the turbine transition state. These tests were performed on a low temperature turbine test rig with a pulsing arrangement to provide periodic time varying intake conditions. However, the similarity criteria adopted by the students of empire university are based on steady state methods, and do not consider the problem of similar scaling on the time scale, which results in significant differences in transition state characteristics, particularly hysteresis effects, under high and low temperature conditions. In addition, related researches of the northern China engine institute indicate that when characteristic parameters such as incoming flow temperature/pressure and the like periodically change in a sine function, the corresponding relation of time scales under different working environments can be established by combining the standard number St (Strhouhal Number) reflecting the period length and the working medium propagation rate. However, the transition states common to aeroplane turbines generally do not have a definite periodicity, nor does this similar method in terms of St numbers apply.
At present, research on transition state similarity worldwide is still in a just-started stage, and a theory and a result which can be referred are difficult to find, so that the research is just a pain point for developing a turbine transition state test, and a transition state similarity method suitable for refining engineering is needed.
Disclosure of Invention
The application aims to provide a method and a device for similar transition state performance of an aviation gas turbine, which are used for guiding turbine transition state characteristic experiments under medium-temperature and medium-pressure conditions.
The application provides a transition state performance similarity method of an aviation 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 a high-temperature working condition transition state process of the aviation gas turbine; taking any moment of the high-temperature working condition characteristic curve as a high-temperature working condition reference point, and determining 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 consistency of dimensionless moments of the high-temperature working condition and the low-temperature working condition datum point, 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; the target parameters of the low-temperature working condition at the target moment are the same as the target parameters of the high-temperature working condition datum point based on a similar method; determining the corresponding relation 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; determining the change rate of the parameter at each moment along with time change under a low-temperature working condition based on the corresponding relation and the high-temperature working condition characteristic curve; generating working condition parameters of low-temperature working conditions at all moments according to the low-temperature working condition parameters of the low-temperature working condition datum point and the change rate; wherein the base reference quantity comprises at least one of: reference size, reference speed, reference temperature, reference pressure; the target parameters include at least one of: expansion ratio, reduced rotational speed, and exit mach number.
Optionally, the operating condition parameters include at least one of: outlet back pressure, inlet total temperature, inlet air flow angle, and rotation speed; the determining the low-temperature working condition parameters of the low-temperature working condition datum point according to the basic reference quantity corresponding to the actual physical condition comprises the following steps: and determining the total inlet pressure and the rotating speed of the low-temperature working condition datum point according to the total inlet pressure and the outlet back pressure of the low-temperature working condition datum point.
Optionally, the similar method changes the consistency of the solution condition in a dimensionless form according to the high-temperature working condition and the low-temperature working condition.
Optionally, the time-varying solution condition includes at least one of: outlet back pressure, inlet total temperature, inlet air flow angle, and rotation speed.
The application also provides an aviation gas turbine transition state performance similar device, which comprises: the acquisition module is used for extracting working condition parameters of a 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 datum point and determining a high-temperature working condition parameter of the high-temperature working condition datum point; the determining module is also used for determining a target moment corresponding to the low-temperature working condition datum point according to the consistency of the dimensionless moments of the high-temperature working condition and the low-temperature working condition datum point and determining a low-temperature working condition parameter of the low-temperature working condition datum point according to a basic reference quantity corresponding to the actual physical condition; the target parameters of the low-temperature working condition at the target moment are the same as the target parameters of the high-temperature working condition datum point based on a similar method; the determining module is further used for determining the corresponding relation 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 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 also used for 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 high-temperature working condition characteristic curve; the generating module is used for generating working condition parameters of low-temperature working conditions at all moments according to the low-temperature working condition parameters of the low-temperature working condition datum 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 parameters include at least one of: inlet total temperature, outlet back pressure, inlet total pressure, 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 back pressure of the low-temperature working condition reference point.
Optionally, the similar method changes the consistency of the solution condition in a dimensionless form according to the high-temperature working condition and the low-temperature working condition.
Optionally, the time-varying solution condition includes at least one of: outlet back pressure, inlet total temperature, inlet air flow angle, and rotation speed.
The application also provides a computer program product comprising computer programs/instructions which, when executed by a processor, implement the steps of a method of transition state performance similarity of an aero gas turbine as described in any of the preceding.
The application also 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 aero gas turbine transition state performance similarity method as described in any of the above when the program is executed.
The present application also provides a non-transitory computer readable storage medium having stored thereon a computer program which, when executed by a processor, implements the steps of the aero gas turbine transition state performance similarity method as described in any of the above.
According to the aviation gas turbine transition state performance similarity method and device, 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 turbine transition state process can be more accurately simulated. 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 turbines, and the method has engineering value and can be applied to actual turbine transition state experiments. And, when the transition state process is a periodic process or an approximation of a steady state process, the method may also be degraded into a periodic or steady state like method, in other words, the periodic/steady state like methods are all special forms of the transition state like method.
Drawings
In order to more clearly illustrate the application or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the application, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow diagram of an aero gas turbine transition state performance similarity method provided by the present application;
FIG. 2 is a schematic diagram of a high-low temperature operating mode time-varying input parameter under a dimensional scale provided by the application;
FIG. 3 is a schematic diagram of a time-varying input parameter of a high-low temperature working condition under dimensionless scale provided by the application;
FIG. 4 is a graph showing the comparison of parameter curves before and after similar modeling for two similar methods provided by the present application;
FIG. 5 is a graph of similar accuracy versus two similar methods provided by the present application;
FIG. 6 is a schematic structural view of an aero gas turbine transition state performance similarity apparatus provided by the present application;
Fig. 7 is a schematic structural diagram of an electronic device provided by the present application.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present application, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
The terms first, second and the like in the description and in the claims, are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged, as appropriate, such that embodiments of the present application may be implemented in sequences other than those illustrated or described herein, and that the objects identified by "first," "second," etc. are generally of a type, and are not limited to the number of objects, such as the first object may be one or more. Furthermore, in the description and claims, "and/or" means at least one of the connected objects, and the character "/", generally means that the associated object is an "or" relationship.
Turbofan engines are the most central component of an aircraft, and their operating conditions directly determine the stability and safety of the entire aircraft. The transition state performance of the turbofan engine directly influences the performance of take-off, acceleration, maneuvering flight and the like of the aircraft.
Aiming at the situation that the research on the transition state similarity of the prior gas turbine is not successful for reference, the technical scheme provided by the embodiment of the application can be used for guiding the turbine transition state characteristic experiment under the medium-temperature and medium-pressure condition.
The method for similar transitional state performance of the aviation gas turbine provided by the embodiment of the application is described in detail below through specific embodiments and application scenes thereof with reference to the accompanying drawings.
As shown in fig. 1, an embodiment of the present application provides a method for similar transitional performance of an aero gas turbine, which may include the following steps 101 to 105:
Step 101, based on the working condition parameters of the high-temperature working condition transition state process of the gas turbine, 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 datum point, and determining the high-temperature working condition parameters of the high-temperature working condition datum point.
The high temperature operating mode characteristic curve of the gas turbine is an aerodynamic parameter obtained by the gas turbine under a real high temperature operating mode.
For example, the high temperature condition reference point may be any time during the transition state of the gas turbine, and in actual operation, for convenience of calculation, a starting point of the transition state process is generally selected as the high temperature condition reference point.
For example, the high temperature operating parameters may include at least one of: outlet back pressure, inlet total temperature, inlet air flow angle, rotation speed, expansion ratio and reduced rotation speed.
For ease of understanding, table 1 below provides exemplary transient process parameters for a high temperature operating condition of a turbine:
TABLE 1
It should be noted that, in the experimental process, the above parameters may be calculated according to the basic reference amounts. The basic reference amounts include at least one of: reference dimension L ref, reference speed u ref, reference temperature T ref, reference pressure P ref. The total inlet temperature, the back pressure of the outlet, the total inlet pressure, the rotating speed, the expansion ratio and the folding rotating speed can be calculated according to the basic reference quantity. Ref above indicates that the parameter is a parameter. The parameters can be selected according to actual needs, but consistency between high and low temperature working conditions is required to be ensured.
Step 102, determining a target moment corresponding to a low-temperature working condition datum point according to the consistency of dimensionless moments of the high-temperature working condition and the low-temperature working condition datum point, and determining a low-temperature working condition parameter of the low-temperature working condition datum point according to a basic reference quantity.
The target parameters of the low-temperature working condition at the target moment are the same as the target parameters of the high-temperature working condition datum point based on a similar method. The basic reference quantity includes at least one of: reference size, reference speed, reference temperature, reference pressure; the target parameters include at least one of: expansion ratio, reduced rotational speed, and exit mach number.
Illustratively, the similar method relies on consistency of the variable solution conditions in dimensionless form between the high temperature operating condition and the low temperature operating condition. The time-varying solution conditions include at least one of: outlet back pressure, inlet total temperature, inlet air flow angle, and rotation speed. The establishment of the similar method does not depend on the reference point moment and the specific selection mode of parameters.
The reference point of the low-temperature working condition is selected according to the limitation of the actual test condition, namely, the moment of any low-temperature working condition under the limitation of the actual test condition. But based on a similar method, parameters such as expansion ratio, reduced rotation speed, exit Mach number and the like of the high-temperature working condition datum point and the low-temperature working condition datum 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", and the like, which are concepts used in determining the similarity between two physical phenomena, and are widely used in modeling experiments at present. In fluid mechanics, flow field similarity includes geometric similarity, motion similarity, dynamic similarity, wherein geometric similarity requires that the flow fields have the same geometric shape and are proportional in size; the motion similarity requires that the speed and the direction of each corresponding point in the flow field are consistent, and the sizes are proportional; the power similarity requires that the stress types of all corresponding points in the flow field are the same, the directions are consistent, the sizes are proportional, and the stress types can be equivalently converted into the consistency of related dimensionless criterion numbers.
In one implementation, the reference pressure and reference temperature may be selected and based on a similar method, the total inlet and outlet backpressure for low temperature conditions may be determined.
Illustratively, the step 102 described above may include the following step 102a:
102a, determining the total inlet pressure and the rotating speed of the low-temperature working condition datum point according to the total inlet pressure and the outlet back pressure of the low-temperature working condition datum point.
Specifically, the inlet air flow angles are equal between high and low temperature working conditions at any moment, the geometric consistency is ensured, working media are complete gases with the same molar mass, specific heat of the working media is consistent at the same dimensionless moment between the high and low temperature working conditions, the working points are positioned in a self-molding area, the wall surface is insulated and under the assumption of neglecting gravity, and the total sum of the dimensionless inlet back pressure and the outlet back pressure of datum points between the high and low temperature working conditions are satisfied:
Illustratively, after the total inlet and outlet back pressures of the low-temperature working condition datum points are obtained, according to a similar method, the expansion ratio, the reduced rotation speed and the outlet Mach number of the high-temperature working condition datum points are ensured to be equal, namely:
The total inlet pressure and the rotating speed of the datum point of the low-temperature working condition can be obtained. At this time, the parameters of the reference point of the low-temperature working condition are all obtained.
And 103, determining the corresponding relation 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 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 method includes the steps of obtaining parameters of a low-temperature working condition datum point, selecting a reference temperature of a high-temperature working condition datum point and a reference temperature of the low-temperature working condition datum point according to actual conditions, and determining a corresponding relation 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 datum point and the reference temperature of the low-temperature working condition datum point.
Specifically, the correspondence of the time scales is as follows:
and 104, determining the change rate of the parameter at each moment along with time change under the low-temperature working condition based on the corresponding relation and the high-temperature working condition characteristic curve.
On the basis of the time scale corresponding relation, a high-temperature working condition characteristic curve (also called a high-temperature working condition dimensionless parameter curve) is combined, and the change rate of the low-temperature working condition dimensionless outlet back pressure, the expansion ratio, the dimensionless inlet total temperature and the change of the reduced rotating speed along with time is determined according to a similar method:
and 105, generating working condition parameters of the low-temperature working condition at all moments according to the low-temperature working condition parameters of the low-temperature working condition datum point and the change rate.
Illustratively, after the above-mentioned change rate is obtained, the parameters of each moment of the low-temperature working condition are obtained by combining the low-temperature working condition parameters of the low-temperature working condition reference point and the following formulas. The parameters of each moment under the low-temperature working condition comprise: pneumatic parameters at various moments under low-temperature working conditions.
Illustratively, table 2 below is a comparison of aerodynamic parameters for the starting and ending points of the high and low temperature operating conditions obtained:
TABLE 2
Illustratively, by a similar approach, aerodynamic parameter curves for low temperature conditions have been obtained. Fig. 2 and 3 are respectively the aerodynamic parameter curves of the high-low temperature working condition with dimension and without dimension.
Illustratively, to verify the transition state similarity method of the present invention, taking a typical transition state process of a certain turbine as an example, a commercial numerical simulation software ANSYS CFX is used to solve URANS equation sets, and the similarity accuracy of different similarity methods is analyzed.
In the numerical simulation calculation, the turbulence model adopts an SST k-omega model, the space dispersion adopts a second-order windward format, and the time dispersion adopts a second-order Euler post-difference format.
In the high-temperature working condition transition state numerical simulation process, the given inlet total temperature, inlet total pressure and rotating speed show periodic changes along with time, so that the average result of the corresponding phases of a plurality of periods can be conveniently obtained, and the similarity precision is improved. The average value of the periodic variation of each parameter is consistent with the parameter of the design point, so that the working range of the transition state is ensured to be basically positioned in the actual turbine working envelope.
And respectively adopting a transition state similarity method and a steady state similarity method to obtain time-varying strake parameters corresponding to the low-temperature working condition. Based on the above, 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 similar method and the low-temperature transition state process obtained by modeling by adopting a steady-state similar method is completed, and the similar precision of the two methods is analyzed by comparing the parameter curves of the three transition state processes.
The comparison of the low temperature condition transition state parameter curve and the high temperature condition parameter curve obtained by adopting the two similar modeling methods is shown in fig. 4. Therefore, the fitting degree of the low-temperature working condition folding work, the airflow angle and the relative Mach number curve obtained by the transition state similarity method and the high-temperature working condition curve are far higher than those of the steady-state method, and the accuracy of the transition state similarity method is proved.
In order to more intuitively compare the similarity precision of two similar methods, a definition formula of the maximum difference and the average difference between the aerodynamic parameters of each high-temperature working condition and each low-temperature working condition is given below.
Maximum deviation of reduced work/relative Mach number:
Average power fold/relative mach number deviation:
Maximum deviation of air flow angle:
MaxDiff(α)＝maxT|αtest-αori|
Average deviation of air flow angle:
Fig. 5 shows the maximum deviation and the average deviation of the transition state and steady state similarity method, and it can be seen that the similarity accuracy of the transition state similarity method is improved by an order of magnitude compared with the steady state method, which demonstrates the advantages of the transition state similarity method.
Of course, the similar method is not limited to a single type turbine or a single transition state process, and the proposed transition state similarity relationship can be widely applied to typical transition state processes of various turbines, and the connection between a prototype transition state and a medium-temperature and medium-pressure condition transition state turbine experiment is established through the similar method.
Optionally, the functional relationship between the parameters of the dimensionless form of the time-varying solution condition under the high-low temperature working condition comprises:
Dimensionless outlet back pressure:
total pressure of dimensionless inlet:
Total temperature of dimensionless inlet:
inlet airflow angle:
Dimensionless rotational speed:
n *(t*)|ori＝n*(t*)|test formula six
Wherein ori represents a parameter under a high-temperature working condition, and test represents a parameter under a low-temperature working condition; * Representing dimensionless parameters, t representing dimensionless time; p 2 is the outlet back pressure, P 1t is the inlet total pressure, T 1t is the inlet total temperature, alpha xy and alpha xz are the inlet air flow angle, and n is the rotational speed.
Optionally, the functional relationship of the dimensionless outlet back pressure is converted into by reducing the dimensionality equivalent:
Wherein P ref represents a reference pressure.
Optionally, the functional relation of the dimensionless inlet total pressure is converted into by reducing the dimensionality equivalence:
according to the formula seven, the formula eight is equivalently converted into the following formula nine:
Wherein pi t＝P1t/P2t is the total expansion ratio of the turbine;
The calculation formula of the outlet Mach number is as follows:
the result of the equation ten is equal to the ratio of the outlet static pressure to the total pressure.
Optionally, the functional relation of the total temperature of the dimensionless inlet is converted into the following equivalent by reduction dimension:
wherein T ref identifies a reference temperature.
Optionally, the functional relation of the dimensionless rotation speed is converted into by reducing dimensionality equivalence:
wherein n ref is the reference rotation speed, defined as:
Where u ref denotes a reference speed, L ref denotes a reference length, and γ ref denotes a reference specific heat; k u represents a speed coefficient representing the ratio of the tangential speed of the rotor to the reference speed u ref; k L is a length coefficient representing the ratio of the average rotor revolution circumference to the reference length L ref;
according to the above relation, the functional relation of the dimensionless rotation speed can be equivalently converted into:
I.e.
According to a functional relation formula eleven of the total temperature of the dimensionless inlet, 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 satisfies the following conditions:
wherein t is physical time, and t is dimensionless time;
At the same time, for time-varying aerodynamic parameters at any dimensionless moment At any time t e, an expression for the aerodynamic parameters and the rate of change of the aerodynamic parameters at reference time t s can be written:
Optionally, the inlet air flow angle is equal between the high-low temperature working conditions at any moment, the working medium is complete gas, the working point is positioned in the self-molding area, the wall surface is insulated and the gravity is ignored, and the dimensionless criterion number can be equivalently converted into:
/>
optionally, under the premise that the high-low temperature working condition is added as the same working medium with the same specific heat at the corresponding dimensionless moment and the reduction ratio is 1, the dimensionless criterion number can be equivalently converted into:
According to the aviation gas turbine transition state performance similarity method provided by the application, the similar problem of time scale in the transition state process is considered, so that the hysteresis effect and the filling and emptying effect in the turbine transition state process can be more accurately simulated. 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 turbines, and the method has engineering value and can be applied to actual turbine transition state experiments. And, when the transition state process is a periodic process or an approximation of a steady state process, the method may also be degraded into a periodic or steady state like method, in other words, the periodic/steady state like methods are all special forms of the transition state like method.
It should be noted that, in the method for similar transitional state performance of an aero-gas turbine provided by the embodiment of the present application, the execution body may be an aero-gas turbine transitional state performance similar device, or a control module in the aero-gas turbine transitional state performance similar device for executing the method for similar transitional state performance of an aero-gas turbine. In the embodiment of the application, an aviation gas turbine transition state performance similar device is taken as an example to execute an aviation gas turbine transition state performance similar method, and the aviation gas turbine transition state performance similar device provided by the embodiment of the application is described.
It should be noted that, in the embodiments of the present application, the transition state performance similar methods of the aero gas turbine shown in the above respective method drawings are all exemplified by the accompanying drawings in combination with the embodiment of the present application. In specific implementation, the transition state performance similar method of the aero gas turbine shown in the above method drawings may also be implemented in combination with any other drawing that may be combined and is illustrated in the above embodiment, and will not be repeated here.
In the following description of the application, reference is made to the following description of methods similar to those described above for transition state performance of an aero gas turbine.
FIG. 6 is a schematic structural diagram of an apparatus for transition state performance similarity of an aero-gas turbine according to an embodiment of the present application, as shown in FIG. 6, specifically including:
The acquisition module 601 is configured to acquire a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of a high-temperature working condition transition state process of the aviation gas turbine; the determining module 602 is configured to take any moment in the high-temperature working condition characteristic curve as a high-temperature working condition reference point, and determine a high-temperature working condition parameter of the high-temperature working 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 a low-temperature working condition reference point according to consistency of dimensionless time of the high-temperature working condition and the low-temperature working condition reference point, and determine a low-temperature working condition parameter of the low-temperature working condition reference point according to a basic reference quantity corresponding to an actual physical condition; the target parameters of the low-temperature working condition at the target moment are the same as the target parameters of the high-temperature working condition datum point based on a similar method; the determining module 602 is further configured to determine a corresponding relationship between the high temperature operating condition characteristic curve and the low temperature operating condition characteristic curve on a time scale according to the reference temperature of the high temperature operating condition reference point and the reference temperature of the low temperature operating 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 rate of change of the parameter at each moment in time under the low-temperature working condition according to the correspondence and the high-temperature working condition characteristic curve; the generating module 603 is configured to generate working condition parameters of each moment 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 parameters include at least one of: outlet back pressure, inlet total temperature, inlet air flow 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 back pressure of the low-temperature working condition reference point.
Optionally, the similar method changes the consistency of the solution condition in a dimensionless form according to the high-temperature working condition and the low-temperature working condition.
Optionally, the time-varying solution condition includes at least one of: outlet back pressure, inlet total temperature, inlet air flow angle, and rotation speed.
Optionally, the functional relationship between the parameters of the dimensionless form of the time-varying solution condition under the high-low temperature working condition comprises:
Dimensionless outlet back pressure:
total pressure of dimensionless inlet:
Total temperature of dimensionless inlet:
inlet airflow angle:
alpha xy(t*)|ori＝αxy(t*)|test formula four
Alpha xz(t*)|ori＝αxz(t*)|test formula five
Dimensionless rotational speed:
n *(t*)|ori＝n*(t*)|test formula six
Wherein ori represents a parameter under a high-temperature working condition, and test represents a parameter under a low-temperature working condition; * Representing dimensionless parameters, t representing dimensionless time; p 2 is the outlet back pressure, P 1t is the inlet total pressure, T 1t is the inlet total temperature, alpha xy and alpha xz are the inlet air flow angle, and n is the rotational speed.
Optionally, the functional relationship of the dimensionless outlet back pressure is converted into by reducing the dimensionality equivalent:
Wherein P ref represents a reference pressure.
Optionally, the functional relation of the dimensionless inlet total pressure is converted into by reducing the dimensionality equivalence:
according to the formula seven, the formula eight is equivalently converted into the following formula nine:
Wherein pi t＝P1t/P2t is the total expansion ratio of the turbine;
The calculation formula of the outlet Mach number is as follows:
the result of the equation ten is equal to the ratio of the outlet static pressure to the total pressure.
Optionally, the functional relation of the total temperature of the dimensionless inlet is converted into the following equivalent by reduction dimension:
wherein T ref identifies a reference temperature.
Optionally, the functional relation of the dimensionless rotation speed is converted into by reducing dimensionality equivalence:
/>
wherein n ref is the reference rotation speed, defined as:
Where u ref denotes a reference speed, L ref denotes a reference length, and γ ref denotes a reference specific heat; k u represents a speed coefficient representing the ratio of the tangential speed of the rotor to the reference speed u ref; k L is a length coefficient representing the ratio of the average rotor revolution circumference to the reference length L ref;
according to the above relation, the functional relation of the dimensionless rotation speed can be equivalently converted into:
I.e.
According to a functional relation formula eleven of the total temperature of the dimensionless inlet, 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 satisfies the following conditions:
wherein t is physical time, and t is dimensionless time;
At the same time, for time-varying aerodynamic parameters at any dimensionless moment At any time t e, an expression for the aerodynamic parameters and the rate of change of the aerodynamic parameters at reference time t s can be written:
Optionally, the inlet air flow angle is equal between the high-low temperature working conditions at any moment, the working medium is complete gas, the working point is positioned in the self-molding area, the wall surface is insulated and the gravity is ignored, and the dimensionless criterion number can be equivalently converted into:
/>
optionally, under the premise that the high-low temperature working condition is added as the same working medium with the same specific heat at the corresponding dimensionless moment and the reduction ratio is 1, the dimensionless criterion number can be equivalently converted into:
/>
The aviation gas turbine transition state performance similar device provided by the application considers the similar problem of time scale in the transition state process, so that the hysteresis effect and the filling and emptying effect in the turbine transition state process can be more accurately simulated. 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 turbines, and the method has engineering value and can be applied to actual turbine transition state experiments. And, when the transition state process is a periodic process or an approximation of a steady state process, the method may also be degraded into a periodic or steady state like method, in other words, the periodic/steady state like methods are all special forms of the transition state like method.
Fig. 7 illustrates a physical schematic diagram of an electronic device, as shown in fig. 7, which may include: processor 510, communication interface (Communications Interface) 520, memory 430, and communication bus 540, wherein processor 510, communication interface 520, and memory 530 communicate with each other via communication bus 540. Processor 510 may invoke logic instructions in memory 530 to perform an aero 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 a high-temperature working condition transition state process of the aviation gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition datum point, and determining the high-temperature working condition parameters of the high-temperature working condition datum point; determining a target moment corresponding to a low-temperature working condition datum point according to the consistency of dimensionless moments of the high-temperature working condition and the low-temperature working condition datum point, 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; the target parameters of the low-temperature working condition at the target moment are the same as the target parameters of the high-temperature working condition datum point based on a similar method; determining the corresponding relation 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; determining the change rate of the parameter at each moment along with time change under a low-temperature working condition based on the corresponding relation and the high-temperature working condition characteristic curve; generating working condition parameters of low-temperature working conditions at all moments according to the low-temperature working condition parameters of the low-temperature working condition datum point and the change rate; wherein the base reference quantity comprises at least one of: reference size, reference speed, reference temperature, reference pressure; the target parameters include at least one of: expansion ratio, reduced rotational speed, and exit mach number.
Further, the logic instructions in the memory 530 described above may be implemented in the form of software functional units and may be stored in a computer-readable storage medium when sold or used as a stand-alone product. Based on this understanding, the technical solution of the present application may be embodied essentially or in a part contributing to the prior art or in a part of the technical solution, in the form of a software product stored in a storage medium, comprising several instructions for causing a computer device (which may be a personal computer, a server, a network device, etc.) to perform all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: a usb disk, a removable hard disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk, or an optical disk, or 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, are capable of performing the aero gas turbine transition state performance similarity method provided by the methods described above, the method comprising: acquiring a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of a high-temperature working condition transition state process of the aviation gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition datum point, and determining the high-temperature working condition parameters of the high-temperature working condition datum point; determining a target moment corresponding to a low-temperature working condition datum point according to the consistency of dimensionless moments of the high-temperature working condition and the low-temperature working condition datum point, 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; the target parameters of the low-temperature working condition at the target moment are the same as the target parameters of the high-temperature working condition datum point based on a similar method; determining the corresponding relation 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; determining the change rate of the parameter at each moment along with time change under a low-temperature working condition based on the corresponding relation and the high-temperature working condition characteristic curve; generating working condition parameters of low-temperature working conditions at all moments according to the low-temperature working condition parameters of the low-temperature working condition datum point and the change rate; wherein the base reference quantity comprises at least one of: reference size, reference speed, reference temperature, reference pressure; the target parameters include 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 which, when executed by a processor, is implemented to perform the aero gas turbine transition state performance similarity methods provided above, the method comprising: acquiring a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of a high-temperature working condition transition state process of the aviation gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition datum point, and determining the high-temperature working condition parameters of the high-temperature working condition datum point; determining a target moment corresponding to a low-temperature working condition datum point according to the consistency of dimensionless moments of the high-temperature working condition and the low-temperature working condition datum point, 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; the target parameters of the low-temperature working condition at the target moment are the same as the target parameters of the high-temperature working condition datum point based on a similar method; determining the corresponding relation 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; determining the change rate of the parameter at each moment along with time change under a low-temperature working condition based on the corresponding relation and the high-temperature working condition characteristic curve; generating working condition parameters of low-temperature working conditions at all moments according to the low-temperature working condition parameters of the low-temperature working condition datum point and the change rate; wherein the base reference quantity comprises at least one of: reference size, reference speed, reference temperature, reference pressure; the target parameters include at least one of: expansion ratio, reduced rotational speed, and exit mach number.
The apparatus embodiments described above are merely illustrative, wherein the elements illustrated as separate elements may or may not be physically separate, and the elements shown as elements may or may not be physical elements, may be located in one place, or may be distributed over a plurality of network elements. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art will understand and implement the present invention without undue burden.
From the above description of the embodiments, it will be apparent to those skilled in the art that the embodiments may be implemented by means of software plus necessary general hardware platforms, or of course may be implemented by means of hardware. Based on this understanding, the foregoing technical solution may be embodied essentially or in a part contributing to the prior art in the form of a software product, which may be stored in a computer readable storage medium, such as ROM/RAM, a magnetic disk, an optical disk, etc., including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the method described in the respective embodiments or some parts of the embodiments.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present application, and are not limiting; although the application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present application.
Claims (10)
1. 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 a high-temperature working condition transition state process of the aviation gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition datum point, and determining the high-temperature working condition parameters of the high-temperature working condition datum point;
Determining a target moment corresponding to a low-temperature working condition datum point according to the consistency of dimensionless moments of the high-temperature working condition and the low-temperature working condition datum point, 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; the target parameters of the low-temperature working condition at the target moment are the same as the target parameters of the high-temperature working condition datum point based on a similar method;
determining the corresponding relation 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;
Determining the change rate of the parameter at each moment along with time change under a low-temperature working condition based on the corresponding relation and the high-temperature working condition characteristic curve;
generating working condition parameters of low-temperature working conditions at all moments according to the low-temperature working condition parameters of the low-temperature working condition datum point and the change rate;
Wherein the base reference quantity comprises at least one of: reference size, reference speed, reference temperature, reference pressure; the target parameters include at least one of: expansion ratio, reduced rotational speed, and exit mach number; the operating condition parameters include at least one of the following: outlet back pressure, inlet total temperature, inlet air flow angle, and rotation speed; the similar method is based on the consistency of the variable solution conditions in a dimensionless form between the high-temperature working condition and the low-temperature working condition;
The determining the low-temperature working condition parameters of the low-temperature working condition datum point according to the basic reference quantity corresponding to the actual physical condition comprises the following steps:
And determining the total inlet pressure and the rotating speed of the low-temperature working condition datum point according to the total inlet pressure and the outlet back pressure of the low-temperature working condition datum point.
2. The method of claim 1, wherein the time-varying solution conditions comprise at least one of: outlet back pressure, inlet total temperature, inlet air flow angle, and rotation speed.
3. The method of claim 2, wherein the dimensionless representation of the time-varying solution condition is a functional relationship between parameters under high and low temperature conditions, comprising:
Dimensionless outlet back pressure:
total pressure of dimensionless inlet:
Total temperature of dimensionless inlet:
inlet airflow angle:
Alpha xy(t*)|ori＝αxy(t*)|test formula four
Alpha xz(t*)|ori＝αxz(t*)|test formula five
Dimensionless rotational speed:
n *(t*)|ori＝n*(t*)|test formula six
Wherein ori represents a parameter under a high-temperature working condition, and test represents a parameter under a low-temperature working condition; * Representing dimensionless parameters, t representing dimensionless time; p 2 is the outlet backpressure, p 1t is the inlet total pressure, T 1t is the inlet total temperature, alpha xy and alpha xz are the inlet airflow angle, and n is the rotational speed.
4. A method according to claim 3, characterized in that the functional relation formula of the dimensionless outlet back pressure-is converted into by reducing the dimensionality equivalent:
Wherein p ref represents the reference pressure.
5. The method of claim 4, wherein the functional relationship formula of the dimensionless total inlet pressure is converted by reducing the dimensionality equivalent to:
according to the formula seven, the formula eight is equivalently converted into the following formula nine:
Wherein pi t＝p1t/p2t is the total expansion ratio of the turbine;
the calculation formula of the outlet mach number Ma 2 is the following formula ten:
the result of the formula ten is equal to the ratio of the outlet static pressure to the total pressure, γ being the specific heat.
6. A method according to claim 3, wherein the functional relation formula of the total temperature of the dimensionless inlet is converted by reducing the dimensionality equivalent to:
Wherein T ref represents a reference temperature.
7. The method of claim 5, wherein the functional relationship formula six of the dimensionless number of revolutions is converted into by reducing the dimensionality equivalent:
wherein n ref is the reference rotation speed, defined as:
Where u ref denotes a reference speed, L ref denotes a reference length, and γ ref denotes a reference specific heat; k u represents a speed coefficient representing the ratio of the tangential speed of the rotor to the reference speed u ref; k L is a length coefficient representing the ratio of the average rotor revolution circumference to the reference length L ref; according to the similarity relationship, the speed coefficient and the length coefficient between the working conditions which are similar to each other are consistent;
according to the above relation, the functional relation formula twelve of the dimensionless rotation speed can be equivalently converted into:
I.e.
According to a functional relation formula eleven of the total temperature of the dimensionless inlet, the formula sixteen can be equivalently converted into:
8. The method of claim 7, 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 satisfies the following conditions:
wherein t is physical time, and t is dimensionless time;
at the same time, for time-varying aerodynamic parameters at any dimensionless moment At any time t e, an expression for the aerodynamic parameters and the rate of change of the aerodynamic parameters at reference time t s can be written:
9. the method of claim 1, wherein the establishment of the similar method is independent of the reference point moment and the specific selection of the basic reference quantity.
10. An aero gas turbine transition state performance similarity apparatus, the apparatus comprising:
The acquisition module is used for acquiring a high-temperature working condition characteristic curve of the gas turbine based on working condition parameters of a high-temperature working condition transition state process 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 datum point and determining a high-temperature working condition parameter of the high-temperature working condition datum point;
the determining module is also used for determining a target moment corresponding to the low-temperature working condition datum point according to the consistency of the dimensionless moments of the high-temperature working condition and the low-temperature working condition datum point and determining a low-temperature working condition parameter of the low-temperature working condition datum point according to a basic reference quantity corresponding to the actual physical condition; the low-temperature working condition datum point and the high-temperature working condition datum point are the same in target parameters based on a similar method;
The determining module is further used for determining the corresponding relation 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 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 also used for 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 high-temperature working condition characteristic curve;
the generating module is used for generating working condition parameters of low-temperature working conditions at all moments according to the low-temperature working condition parameters of the low-temperature working condition datum point and the change rate;
Wherein the base reference quantity comprises at least one of: reference size, reference speed, reference temperature, reference pressure; the target parameters include at least one of: expansion ratio, reduced rotational speed, and exit mach number; the operating condition parameters include at least one of the following: outlet back pressure, inlet total temperature, inlet air flow angle, and rotation speed; the similar method is based on the consistency of the variable solution conditions in a dimensionless form between the high-temperature working condition and the low-temperature working condition;
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 back pressure of the low-temperature working condition reference point.
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