CN114491417B - CDFS (compact disc library) modal variation performance-based one-dimensional input correction method - Google Patents
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Abstract
The application provides a CDFS (compact disc system) modal variation performance-based one-dimensional input correction method, which comprises the steps of constructing a CDFS one-dimensional characteristic evaluation model containing modal variation, bypass ratio variation and mutation angles; determining the mode of the core machine driving fan, the rotating speeds, corresponding bypass ratio parameters and mutation angles of the core machine driving fan in the mode, and corresponding flow, pressure ratio and efficiency characteristics; determining initial one-dimensional design input parameters including dimensionless rotation speed, angle rule and correction coefficient; constructing a flow, pressure ratio and efficiency relational expression containing a correction coefficient; constructing a relational expression comprising modal mutation parameters, bypass ratio parameters and correction coefficients of mutation angles; and calculating according to the relational expression constructed in the last step, the mode, the adjusting angle and the bypass ratio to be evaluated to obtain each correction coefficient, and predicting the one-dimensional characteristics of the variable cycle compression component with the nonlinear mutation. The method improves the accuracy of performance prediction of the compression component of the variable-cycle engine.
Description
Technical Field
The application relates to the technical field of aerodynamic performance design prediction of aero-engines, in particular to a one-dimensional input correction method based on CDFS modal variation performance.
Background
Compared with the conventional Fan layout, the Core Driven Fan Stage (CDFS) is a Fan Stage that is divided into a front part and a rear part in a double-duct manner, wherein the front part is still Driven by the low-pressure turbine, and the rear part is Driven by the Core, i.e., the high-pressure turbine, so that the Fan Stage that is Driven by the Core is called the Core Driven Fan Stage.
The core compression system with the variable cycle characteristic is characterized in that the core machine drives the fan to work in a strong coupling mode with the mode converter, the inlet guide vane and the duct ejector, and large performance changes can be presented in multiple modes. Through the change of the variable circulation mechanisms, the inlet flow and the outlet flow and the pressure of the core machine driving fan are changed in a large range, so that the variable circulation function of the compression part in a wide working range is realized. However, the variable cycle function is established under conditions of closing/opening of the mode selection valve and large angle change of the guide vane and sudden change of inlet and outlet pressure of the bypass ejector, and the sudden change of the mode creates great challenge for the design/test characteristic prediction of the performance of the compression part.
The traditional method for correcting the characteristics of the core machine driven fan generally corrects the characteristics by direct scaling translation and the like according to the existing test characteristics, corrects the result, and is difficult to reflect the rule that the mode mutation, the bypass ratio and the nonlinear change of the guide vane are far beyond the range of the conventional correction coefficient.
The characteristic correction method of the optimization algorithm or artificial intelligence has the advantages of being fast and wide in adaptation, still being scaling correction of characteristic results, only being capable of providing an optimization coefficient or a neuron black box weight coefficient of the correction results, being difficult to reflect the influence of modal mutation, duct ratio and guide vane nonlinear change rule on the characteristics, and being difficult to provide one-dimensional design input and estimation.
The method is rarely used for correcting the design input of the prediction of the one-dimensional characteristic of the mode change compression component of the variable-cycle engine.
Disclosure of Invention
In view of this, the embodiments of the present application provide a one-dimensional input modification method based on CDFS modal variability, which at least partially solves the problem of inaccurate prediction of the modal variability in the prior art.
The embodiment of the application provides a one-dimensional input correction method based on CDFS modal variation performance, which comprises the following steps:
step one, constructing a CDFS one-dimensional characteristic evaluation model containing modal change, bypass ratio change and mutation angles;
determining a core machine driving fan mode, and each rotating speed, corresponding bypass ratio parameters and mutation angles of the core machine driving fan in the mode, and corresponding flow, pressure ratio and efficiency characteristics;
determining initial one-dimensional design input parameters including dimensionless rotation speed, angle rule and correction coefficient, wherein the correction coefficient comprises flow correction coefficient K G And a correction coefficient K of a falling angle δ The head coefficient K H And efficiency correction factor
；
Step four, taking the flow, the pressure ratio and the efficiency characteristic as target values, and constructing a flow, pressure ratio and efficiency relational expression containing the correction coefficient;
constructing a relational expression of the correction coefficients comprising modal mutation parameters, bypass ratio parameters and mutation angles;
and step six, calculating to obtain each correction coefficient according to the relational expression constructed in the step five and the mode, the adjusting angle and the bypass ratio to be evaluated, and predicting the one-dimensional characteristics of the variable-cycle compression component with the nonlinear mutation in the existing or new state.
According to a specific implementation manner of the embodiment of the present application, a flow calculation formula required in the CDFS one-dimensional characteristic evaluation model is as follows:
wherein the content of the first and second substances,
，m i for inlet flow, p i * And T i * Respectively stagnation pressure and temperature on the inlet characteristic section, q (lambda) i ) Is a flow function over a characteristic cross-section of the inlet, Ai being the area of the characteristic cross-section of the inlet through which the gas flows, alpha i Is the included angle between the airflow and the axial direction, R is the gas constant 287.023J/(Kg.K), K is the gas specific heat ratio, and K is the gas specific heat ratio m Abbreviated as a function of gas specific heat ratio and gas constant;
the pressure ratio calculation formula required in the CDFS one-dimensional characteristic evaluation model is as follows:
wherein, pi * st,1 Compression ratio of n stages of compression elements, H Z1 Is the total enthalpy;
the required efficiency calculation formula in the CDFS one-dimensional characteristic evaluation model is as follows:
wherein eta * ad,k Adiabatic efficiency for n-stage compression element, L ad,k Actual required rim work for n stages of compression elements, L u Is the rim work per unit mass of gas, L ad,i Actual required rim work to compress the parts, L u,i For actual consumption of rim work, C P Is the isobaric specific heat of the gas, T * 1,i Total inlet temperature of the i-th stage compressor, eta * st,i Efficiency of the i-th stage, T 1 * For the total inlet temperature of the compression element, pi * st To compress the component pressure ratio,. pi * st,i Is the compression unit ith stage pressure ratio.
According to a specific implementation manner of the embodiment of the application, the pressure head correction coefficient K H Is defined as the load factor
The expression of the reduction coefficient is:
the expression of the efficiency correction coefficient is:
，
wherein eta * ad,max Maximum adiabatic efficiency of stage (eta) * ad,max ) kyon At the maximum adiabatic efficiency of the theoretical stage,
is the theoretical load factor.
According to a specific implementation manner of the embodiment of the present application, the flow rate M including the correction coefficient in step 4 i Pressure ratio of pi * st,1 Efficiency eta * ad,k The relation is as follows:
M i ,n=K G *m i ;
π * st1 ,n=K H *π * st,1 ；
K δ ,n=K δ *f(δ)；
in the formula, M i N is corrected inlet flow, pi * st1 N is the corrected compression ratio of the n stages of compression parts,
for corrected adiabatic efficiency of n-stage compression elements, K δ N is the corrected drop angle, and f (delta) is a drop angle correction function.
According to a specific implementation manner of the embodiment of the present application, the relationship including the modal sudden change parameter, the bypass ratio parameter, and the correction coefficient of the sudden change angle in step five includes:
head correction factor K H =f 1 (α 1 *Md,α 2 *BPR,α 3 *δ)；
Flow correction factor K G =f 2 (β 1 *Md,β 2 *BPR,β 3 *δ);
Coefficient of efficiency correction
=f 3 (γ 1 *Md,γ 2 *BPR,γ 3 *δ)；
Wherein Md is a modal mutation parameter, BPR is a bypass ratio parameter, delta is a mutation angle, f represents a functional relation, and alpha, beta and gamma are fitting weight coefficients.
Advantageous effects
Compared with the traditional method only for correcting the characteristic result, the CDFS modal variation performance-based one-dimensional input correction method constructs a two-step correction method for the characteristic result and the input parameter associated with the modal variation, the guide vane rule and the bypass ratio variation parameter, can predict the one-dimensional design performance of the CDFS with the modal variation, the guide vane rule and the bypass ejector back pressure variation, can flexibly correct the one-dimensional input parameter according to the special configuration characteristic rule, and can be used for predicting the design performance of the one-dimensional characteristic which is not limited to the nonlinear variation of a compression component in a variable cycle engine.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only 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 diagram of a core engine driven fan variable circulation system according to an embodiment of the present invention;
FIG. 2 is a flow diagram of a one-dimensional input modification method based on CDFS modal variability performance, according to an embodiment of the present invention;
fig. 3 is a schematic diagram illustrating a change of a CDFS modal characteristics according to an embodiment of the invention.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
The following embodiments of the present application are described by specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure of the present application. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and/or changes in various respects, all without departing from the spirit of the present application. It should be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to or other than one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present application, and the drawings only show the components related to the present application rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The configuration of the CDFS modal variation constructed in the present application is illustrated as the configuration of the core driven fan variable cycle system shown in fig. 1. The operating characteristics of the core machine driving fan are influenced by the working state of the core machine driving fan, and strong coupling correlation generated by modal change, a guide vane rule and a duct ratio change generated by a modal converter, an inlet guide vane and a duct ejector, so that a characteristic correction method comprising three parameters of the modal change, the guide vane rule and the duct ratio change is required to be established, and the characteristics after the CDFS modal change can be accurately estimated.
Therefore, the present application provides a one-dimensional input correction method based on CDFS modal variability performance, which is described in detail below with reference to fig. 2 to 3, and specifically includes the following steps:
step one, constructing a CDFS one-dimensional characteristic evaluation model containing modal change, bypass ratio change and mutation angle (angle change), wherein a flow calculation formula required for establishing the CDFS one-dimensional characteristic evaluation model is as follows:
wherein the content of the first and second substances,
，m i for inlet flow, p i * And T i * Respectively stagnation pressure and temperature on the inlet characteristic section, q (lambda) i ) Is a flow function over the characteristic cross-section of the inlet, Ai being the area of the characteristic cross-section of the inlet through which the air flows, alpha i Is the included angle between the airflow and the axial direction, R is a gas constant which is equal to 287.023J/(Kg.K), K is the ratio of specific heat of the gas, and K is m Abbreviated as a function of gas specific heat ratio and gas constant;
the pressure ratio calculation formula required in the CDFS one-dimensional characteristic evaluation model is established as follows:
wherein, pi * st,1 Compression ratio of n stages of compression parts, H Z1 Is the total enthalpy;
the efficiency calculation formula required in the CDFS one-dimensional characteristic evaluation model is established as follows:
wherein eta * ad,k Adiabatic efficiency for n-stage compression element, L ad,k The actual required rim work for the n-stage compression unit, L u Is the rim work per unit mass of gas, L ad,i Wheels actually required for compressing partsYuan Gong, L u,i For actually consuming rim work, C P Is the isobaric specific heat of the gas, T * 1,i Total inlet temperature of the i-th stage compressor, eta * st,i Efficiency of the i-th stage, T 1 * For the total inlet temperature of the compression element, pi * st To compress the component pressure ratio,. pi * st,i Is the compression unit ith stage pressure ratio.
And step two, determining the mode of the core machine driving fan, the rotating speed of the core machine driving fan in the mode, corresponding bypass ratio parameters, corresponding mutation angles (corresponding to the change parameter rules of the adjustment angle and the reference angle), and corresponding flow, pressure ratio and efficiency characteristics, and taking the parameters as input parameters required by the one-dimensional pre-estimation model, wherein the bypass ratio parameters are defined as BPR, the mode mutation parameters are defined as Md, and the mutation angles are defined as delta.
Determining initial one-dimensional design input parameters including dimensionless rotation speed, angle rule and correction coefficient, wherein the correction coefficient comprises flow correction coefficient K G And a correction coefficient K of a falling angle δ The head coefficient K H And efficiency correction factor
。
Specifically, the indenter correction coefficient K H Defined as the load factor
The expression of the reduction coefficient is:
；
the expression of the efficiency correction coefficient is as follows:
wherein η * ad,max Maximum adiabatic efficiency of stage (eta) * ad,max ) kyon At the maximum adiabatic efficiency of the theoretical stage,
is the theoretical load factor.
And step four, taking the flow rate, the pressure ratio and the efficiency characteristic as target values, and constructing a flow rate, pressure ratio and efficiency relational expression containing the correction coefficient.
Specifically, the flow rate M including the correction coefficient i Pressure ratio of pi * st,1 Efficiency eta * ad,k The relations are respectively:
M i ,n=K G *m i ;
π * st1 ,n=K H *π * st,1 ；
K δ ,n=K δ *f(δ)；
in the formula, M i N is the corrected inlet flow, pi * st1 N is the corrected compression ratio of the n stages of compression parts,
for corrected adiabatic efficiency of n-stage compression elements, K δ N is a corrected drop angle, and f (δ) is a drop angle correction function.
And step five, constructing a relational expression of the correction coefficients comprising modal mutation parameters, bypass ratio parameters and adjustment rule mutation angles before and after modal change. The specific relation is as follows:
head correction factor K H =f 1 (α 1 *Md,α 2 *BPR,α 3 *δ)；
Flow correction factor K G =f 2 (β 1 *Md,β 2 *BPR,β 3 *δ);
Coefficient of efficiency correction
=f 3 (γ 1 *Md,γ 2 *BPR,γ 3 *δ)；
Wherein Md is a modal mutation parameter, BPR is a bypass ratio parameter, delta is a mutation angle, f represents a functional relation, and alpha, beta and gamma are fitting weight coefficients.
And step six, calculating according to the modal mutation, the bypass ratio and the mutation angle change rule relation constructed in the step five and the modal, the adjusting angle and the bypass ratio to be evaluated to obtain each correction coefficient, predicting the one-dimensional characteristics of the variable cycle compression component with the nonlinear mutation in the existing or new state, and referring to the figure 3 for the characteristics after modal change.
The correction method provided by the invention not only corrects the characteristic result, but also performs associated correction on the one-dimensional design input, realizes the prediction of the one-dimensional design performance of the CDFS with mode mutation, guide vane rule and duct ratio mutation, can more flexibly correct the input parameters, is used for predicting the design performance of the one-dimensional characteristic of the variable-cycle compression component with nonlinear mutation, and provides quick and accurate prediction for the performance prediction of the variable-cycle engine compression component.
The method is used for constructing a two-step correction method for characteristic results and input parameters associated with parameters including modal change, guide vane regularity and bypass ratio change, and the application field is not limited to CDFS (compact disc sizing system) and includes protection of one-dimensional correction methods for characteristics of other aero-engine compression components including modal change characteristics.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (1)
1. A one-dimensional input correction method based on CDFS modal variability performance is characterized by comprising the following steps:
step one, constructing a CDFS one-dimensional characteristic evaluation model containing modal change, bypass ratio change and mutation angle, wherein a flow calculation formula required in the CDFS one-dimensional characteristic evaluation model is as follows:
wherein the content of the first and second substances,
，m i for inlet flow, p i * And T i * Respectively stagnation pressure and temperature on the inlet characteristic section, q (lambda) i ) Is a flow function over the characteristic cross-section of the inlet, Ai being the area of the characteristic cross-section of the inlet through which the air flows, alpha i Is the included angle between the airflow and the axial direction, R is the gas constant 287.023J/(Kg.K), K is the gas specific heat ratio, K is the gas specific heat ratio m Abbreviated as a function of gas specific heat ratio and gas constant;
the pressure ratio calculation formula required in the CDFS one-dimensional characteristic evaluation model is as follows:
wherein, pi * st,1 Compression ratio of n stages of compression parts, H Z1 Is the total enthalpy;
the required efficiency calculation formula in the CDFS one-dimensional characteristic evaluation model is as follows:
wherein eta is * ad,k Adiabatic efficiency for n-stage compression elements, L ad,k Actual required rim work for n stages of compression elements, L u Is the rim work per unit mass of gas, L ad,i The actual required rim work to compress the parts, L u,i For actually consuming rim work, C P Is the isobaric specific heat of the gas, T * 1,i Total inlet temperature, eta, of the i-th stage compressor * st,i Of the i-th orderEfficiency, T 1 * For the total inlet temperature of the compression element, pi * st To compress the component pressure ratio,. pi * st,i The compression component is in the ith stage pressure ratio;
determining a mode of the core machine driving fan, and each rotating speed, corresponding bypass ratio parameters and mutation angles of the core machine driving fan in the mode, and corresponding flow, pressure ratio and efficiency characteristics;
determining initial one-dimensional design input parameters including dimensionless rotation speed, angle rule and correction coefficient, wherein the correction coefficient comprises flow correction coefficient K G And a correction coefficient K of a falling angle δ The head coefficient K H And efficiency correction factor
Said indenter correction factor K H Is defined as the load factor
The expression of the reduction coefficient of (c) is:
the expression of the efficiency correction coefficient is:
wherein η * ad,max Maximum adiabatic efficiency of order (η) * ad,max ) kyon For the maximum adiabatic efficiency of a theoretical stage,
is a theoretical load factor;
step four, taking the flow, the pressure ratio and the efficiency characteristic as target values, constructing a flow, pressure ratio and efficiency relational expression containing the correction coefficient, wherein the flow M containing the correction coefficient i Pressure ratio of pi * st,1 Efficiency eta * ad,k The relation is as follows:
M i ,n=K G *m i ;
π * st1 ,n=K H *π * st,1 ；
K δ ,n=K δ *f(δ)；
in the formula, M i N is corrected inlet flow, pi * st1 N is the corrected compression ratio of the n stages of compression parts,
for corrected adiabatic efficiency of the compression element of n stages, K δ N is the corrected drop relief angle, and f (delta) is a drop relief angle correction function;
step five, constructing a relational expression of the correction coefficients comprising modal mutation parameters, bypass ratio parameters and mutation angles,
pressure head correction coefficient K containing modal abrupt change parameter, bypass ratio parameter and abrupt change angle H ’=f 1 (α 1 *Md,α 2 *BPR,α 3 *δ)；
Flow correction coefficient K containing modal sudden change parameter, bypass ratio parameter and sudden change angle G ’=f 2 (β 1 *Md,β 2 *BPR,β 3 *δ);
Efficiency correction coefficient containing modal sudden change parameter, bypass ratio parameter and sudden change angle
=f 3 (γ 1 *Md,γ 2 *BPR,γ 3 *δ),
Wherein Md is a modal mutation parameter, BPR is a bypass ratio parameter, δ is a mutation angle, f represents a functional relation, and α, β and γ are fitting weight coefficients;
and step six, calculating to obtain each correction coefficient according to the relational expression constructed in the step five and the mode, the adjusting angle and the bypass ratio to be evaluated, and predicting the one-dimensional characteristics of the variable-cycle compression component with the nonlinear mutation in the existing or new state.
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