CN115655729A - Low-speed simulation method and device for coupling of S-shaped transition section and stator of gas compressor - Google Patents
Low-speed simulation method and device for coupling of S-shaped transition section and stator of gas compressor Download PDFInfo
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Abstract
The invention provides a method and a device for low-speed simulation of coupling of an S-shaped transition section and a stator of a gas compressor, wherein the method for low-speed simulation of coupling of the S-shaped transition section and the stator of the gas compressor comprises the following steps: s1, carrying out low-speed simulation design on a flow channel containing a stator transition section; s2, carrying out low-speed simulation design on a stator two-dimensional blade profile in a stator-containing transition section; s3, after the two-dimensional blade profiles of the stators are stacked, carrying out low-speed analog conversion on a stator midday flow field containing a stator transition section; and S4, adjusting a flow channel of the transition section behind the stator according to the actual flow field behind the stator, and completing the low-speed simulation of the coupling of the S-shaped transition section and the stator of the gas compressor. The low-speed simulation device is prepared after simulation design based on the low-speed simulation method. By adopting the method and the device for low-speed simulation of the coupling of the S-shaped transition section and the stator of the gas compressor, the similarity between the internal flow field of the transition section containing the stator and a high-speed prototype is remarkably improved, so that the flow field characteristics of the high-speed prototype can be better reflected by low-speed simulation, and the simulation accuracy is improved.
Description
Technical Field
The disclosure relates to the technical field of low-speed simulation of a gas compressor, in particular to a method and a device for low-speed simulation of coupling of an S-shaped transition section and a stator of the gas compressor.
Background
The compressor is an important component in an aeroengine, accurate measurement of an internal flow field of the compressor is very important for understanding a flow mechanism in the compressor, and because the real compressor has high rotating speed and small size and is limited by high-speed experimental cost, countries in the world often adopt a low-speed simulation method to measure the internal flow field of the compressor. The compressor transition section is an important component of the compressor for connecting the low-pressure compressor and the high-pressure compressor, the radial fall between the high-pressure compressor and the low-pressure compressor is larger and larger along with the increase of the load of the compressor, and the outlet stage stator of the low-pressure compressor is often placed in a lower pressure flow path at the front part of the transition section.
The low-speed simulation design adopts the same design parameters as the high speed according to design indexes, and the design is carried out again under the low-speed condition. The essence of the low speed analog design is not a design, but rather a similar conversion of the high speed prototype. The method comprises the steps of reducing an internal flow field of the high-speed compressor through a low-speed large-size model compressor, measuring the internal flow field of the low-speed simulation compressor, finding out an internal flow mechanism of the low-speed simulation compressor, improving the low-speed simulation compressor, and improving and designing the high-speed compressor according to corresponding similarity criteria after experimental verification.
In the existing low-speed simulation design method, aiming at the low-speed simulation of the transition section and the stator inside the transition section, the transition section and the stator inside the transition section are often subjected to low-speed simulation conversion independently, and meanwhile, the low-speed simulation design of the transition section often adopts a mode of geometric direct amplification, so that the difference of the flow field inside the high-speed and low-speed transition sections is large, the flow field characteristics in the high-speed transition section cannot be well reflected, and the simulation accuracy is influenced.
Disclosure of Invention
In order to solve the problem that the prior art cannot better reflect the flow field characteristics in a high-speed transition section in the low-speed simulation of the transition section and an internal stator thereof, the disclosure provides a compressor S-shaped transition section and stator coupling low-speed simulation method, which comprises the following steps:
carrying out low-speed simulation design on a flow passage containing a stator transition section;
carrying out low-speed simulation design on a stator two-dimensional blade profile in a stator-containing transition section;
after the two-dimensional blade profiles of the stators are stacked, carrying out low-speed analog conversion on a stator midday flow field containing a stator transition section;
and adjusting a flow channel of the transition section behind the stator according to the actual flow field behind the stator to complete the low-speed simulation of the coupling of the S-shaped transition section of the gas compressor and the stator.
By adopting the method for simulating the low speed of the coupling of the S-shaped transition section and the stator of the compressor, the similarity between the internal flow field of the transition section containing the stator and a high-speed prototype is obviously improved, so that the low speed simulation can better reflect the flow field characteristic of the high-speed prototype, and the simulation accuracy is improved.
The disclosure provides an exemplary similarity criterion that needs to be guaranteed when a flow channel including a stator transition section is designed for low-speed simulation, including: reynolds number, ratio delta R/L of diameter difference and length in inlet and outlet, ratio Hin/L of inlet height and length, wall dimensionless isentropic velocity ratio V/V1 distribution and hub ratio. Compared with the low-speed transition section which is amplified in geometric proportion in the prior art, the difference of the total pressure loss coefficients of the high-speed transition section and the low-speed transition section is obviously reduced after the low-speed simulation design is carried out by the method provided by the disclosure.
The disclosure exemplarily provides a method for ensuring the similarity of the distribution of the wall surface dimensionless isentropic velocity ratio V/V1, which comprises the following steps: by adjusting the internal area of the low-speed simulation transition section, the dimensionless isentropic velocity ratio V/V1 distribution of the high-speed runner wall surface and the low-speed runner wall surface is the same.
The disclosure provides an exemplary similarity criterion to be ensured when performing a low-speed simulation design on a stator two-dimensional blade profile in a stator-containing transition section, including: consistency, D factor, reynolds number and dimensionless isentropic velocity distribution of the leaf surface. Wherein the Reynolds number is larger than the self-modeling Reynolds number. When the method is adopted, the low-speed blade profile has better similarity with the high-speed blade profile in the states from the design state to the stall state and in the state with smaller negative attack angle, and the low-speed blade profile can not better simulate the flow of the high-speed blade profile in the state with larger negative attack angle. However, in consideration of the actual working condition of the compressor, the working point is mainly between a small negative attack angle and a near stall point, so the low-speed simulation of the disclosure can meet the requirement of actual engineering.
The present disclosure exemplarily provides a condition to be satisfied when two-dimensional stator vane profiles are stacked, including:
1) Important inlet boundary conditions of the high-speed and low-speed transition sections are similar, and the edge strips comprise total pressure distribution, flow distribution and inlet airflow angle distribution of an inlet;
2) After the stacking, the incoming flow attack angle state of each low-speed stator section is checked, and the incoming flow attack angle of each stator section is adjusted to be consistent with that of the high-speed prototype;
3) Adjusting the geometric angle of the outlet of the low-speed stator to make the airflow angle of the outlet of the low-speed stator consistent with that of the high-speed prototype;
4) And adjusting the geometric angle of the inlet of the low-speed stator and the airflow angle of the low-speed incoming flow, so that the D factor is consistent with that of the high-speed prototype under the condition of ensuring that the high-speed stator and the low-speed stator have the same incoming flow attack angle.
By adopting the method, the three-dimensional flow field under the low-speed condition has higher consistency compared with a high-speed prototype, and the accuracy of low-speed simulation is improved.
The present disclosure exemplarily provides an adjusting method for adjusting a flow channel of a transition section after a stator according to an actual flow field after the stator, including: and adjusting the area of the flow channel behind the stator to ensure that the dimensionless isentropic velocity ratio V/V1 distribution of the wall surface of the flow field behind the stator is the same. By adopting the method, the S2 flow field at the outlet of the transition section has higher consistency compared with a high-speed prototype, and the accuracy of low-speed simulation is further improved.
The invention also provides a low-speed simulation device for coupling the S-shaped transition section and the stator of the gas compressor, which is designed and prepared based on the low-speed simulation design method for coupling the S-shaped transition section and the stator of the gas compressor aiming at a high-speed prototype.
The disclosure exemplarily provides a low-speed simulation device for coupling an S-shaped transition section and a stator of a gas compressor, wherein the low-speed simulation device for coupling the S-shaped transition section and the stator of the gas compressor is prepared by adopting a 3D printing technology after a model is designed based on low-speed simulation.
The present disclosure has at least one of the following advantages:
1. by adopting the method for simulating the low speed of the coupling of the S-shaped transition section and the stator of the gas compressor, the similarity degree of the internal flow field of the transition section containing the stator and a high-speed prototype is obviously improved, so that the flow field characteristics of the high-speed prototype can be better reflected by low-speed simulation, and the simulation accuracy is improved.
2. Compared with the low-speed transition section which is amplified in geometric proportion in the prior art, the difference of the total pressure loss coefficients of the high-speed transition section and the low-speed transition section is obviously reduced after the low-speed simulation design is carried out by the method provided by the disclosure.
3. When the method is adopted, the low-speed simulation blade profile has better similarity with the high-speed blade profile from a design state to a stall state and a state with a smaller negative attack angle.
Drawings
Fig. 1 is a flow chart of a low-speed simulation method of the present disclosure.
FIG. 2 is a schematic view of a midday flow surface including stator transition sections.
FIG. 3 is a graph comparing the distribution of the ratio of the area of any point of the high and low speed transition section to the area of the inlet along the flow direction and the geometry of the transition section.
FIG. 4 is a comparison of the total pressure loss coefficients of the high and low speed transition sections.
FIG. 5 is a comparison graph of high and low speed blade profiles.
Fig. 6 is a graph comparing the high and low speed blade profile angle of attack-loss characteristics (left) and angle of attack-drop angle characteristics (right).
Fig. 7 is a diagram of the flow field parameters of the transition section S2 obtained by the low-speed simulation.
Fig. 8 is a diagram comparing a transition section three-dimensional flow field obtained by low-speed simulation with a high-speed prototype.
FIG. 9 is a distribution diagram of the main parameters of the transition section outlet along the spanwise direction obtained by the low-speed simulation.
FIG. 10 is a graph comparing total pressure loss characteristics of a transition section obtained from a low-speed simulation with a high-speed prototype.
FIG. 11 is a comparison diagram of three-dimensional flow fields of stators in a high-low speed transition section under typical working conditions.
FIG. 12 is a schematic drawing of a dimensionless isentropic velocity ratio versus dimensionless axial position for a low-speed-like simulation design and the method of the present disclosure, respectively, using a transition section and a stator.
FIG. 13 is a velocity/inlet velocity-dimensionless axial position diagram for a low-velocity-like simulation design and the method of the present disclosure, respectively, using a transition section and a stator.
Detailed Description
In order to make the technical problems, technical solutions and technical effects to be solved by the present disclosure more clearly and clearly understood, the following technical solutions of the present disclosure are described in detail in a clear and complete manner with reference to the embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the disclosure and are not intended to limit the disclosure.
Example 1
Fig. 2 is a schematic diagram of a transition section including a stator, and the low-speed analog conversion is performed by using the low-speed analog design method for coupling the S-shaped transition section and the stator of the compressor disclosed by the invention shown in fig. 1.
S1, carrying out low-speed simulation design on a flow channel containing a stator transition section.
When the low-speed simulation design in the step S1 is performed, the low-speed simulation design is performed on the runner including the stator transition section in the high-speed prototype by using the existing low-speed simulation conversion method (for example, the low-speed simulation middle-leaf profile maximum thickness modeling research, liu baojie, etc., the low-speed simulation conversion method in the third period of 2021 of engineering thermophysics, and the like), and the similarity criteria required to be ensured during the conversion include: reynolds number, ratio delta R/L of diameter difference and length in inlet and outlet, ratio Hin/L of inlet height and length, wall dimensionless isentropic velocity ratio V/V1 distribution and hub ratio. The similar method for ensuring the distribution of the wall surface dimensionless isentropic velocity ratio V/V1 comprises the following steps: by adjusting the internal area of the low-speed simulation transition section, the dimensionless isentropic velocity ratio V/V1 of the wall surface of the high-speed runner and the wall surface of the low-speed runner is distributed identically.
When a high-speed prototype is converted into a low-speed simulation based on the similarity criterion of the present disclosure, the distribution of the ratio of the area of any point of the high-speed transition section to the area of the inlet along the flow direction and the comparison of the geometry of the high-speed transition section and the low-speed transition section can be obtained, as shown in fig. 3. Because the transition section of the high-speed prototype is expanded in the first half section, the transition section of the high-speed prototype can be expanded more at low speed to compensate the influence caused by different compressibility; and the transition section of the high-speed prototype is contracted in the second half section, so that the transition section is more contracted at low speed to compensate the influence caused by the difference of compressibility.
Fig. 4 shows a comparison of the total pressure loss coefficients at the inlet and outlet of the transition section in the case of low speed simulation, geometric scale-up simulation and high speed prototype. It can be seen from fig. 4 that, with respect to the low-speed transition section of geometric scale-up simulation, by using the low-speed simulation design method of the present disclosure, the error value of the total pressure loss coefficient compared with the high-speed prototype is reduced from 10.9% by geometric scale-up to 2.7% by using the present disclosure. The error value calculation method comprises the following steps: w = [1-W1/W0 ]. 100%, where W is the error value, W1 is the total pressure loss coefficient during simulation, and WO is the total pressure loss coefficient of the high-speed prototype. Therefore, compared with the existing geometric scale-up simulation method, the low-speed simulation design method disclosed by the invention can enable the simulation value to be closer to a high-speed prototype, so that the simulation accuracy is improved.
And S2, carrying out low-speed simulation design on the stator two-dimensional blade profile in the stator-containing transition section.
When the low-speed simulation design is carried out in the step S2, the low-speed simulation design is carried out on the stator two-dimensional blade profile in the stator transition section in the high-speed prototype by adopting the existing low-speed simulation conversion method, and the similarity criteria required to be ensured during conversion comprise: consistency, D factor, reynolds number and dimensionless isentropic velocity distribution of the leaf surface. Wherein the Reynolds number is larger than the self-modeling Reynolds number. The self-modeling Reynolds number is a set value, such as: 200000, when the Reynolds number is larger than the self-molding Reynolds number, the self-molding zone is entered.
Fig. 5 shows the blade profile comparison results (using chord length as a dimensionless measure) of the low-speed simulated blade profile and the high-speed prototype, and it can be seen from fig. 5 that the inlet airflow angle of the low-speed simulated blade profile is increased compared with that of the high-speed blade profile under the condition of ensuring that the outlet airflow angle is not changed. Compared with the high-speed blade profile prototype, the blade profile parameters of the low-speed blade profile relative to the high-speed blade profile are changed mainly by the following points: (1) the radius of the leading edge becomes larger; (2) the maximum thickness of the blade profile is slightly increased; and (3) the blade profile bending angle is increased. In addition to this, the loading pattern of the blade is also changed — the loading is slightly advanced.
FIG. 6 shows a comparison of the angle of attack-loss characteristics and angle of attack-drop clearance characteristics of a high speed airfoil and a low speed simulated airfoil. The analysis of the attack angle-loss characteristics shows that the total pressure loss of the high-speed blade profile and the low-speed blade profile is basically equivalent and the available attack angle range of the positive attack angle is basically the same in the state of the positive attack angle; in the negative attack angle state, the usable attack angle range of the low-speed blade profile is obviously larger than that of the high-speed blade profile, because the blade profile does not have the problem of blockage when the Mach number is low, and the negative attack angle state is not easy to separate, so that the negative attack angle range is larger. Therefore, the low-speed simulation blade profile has better similarity with the high-speed blade profile from a design state to a stall state and a state with a smaller negative attack angle, and the low-speed blade profile cannot better simulate the flow of the high-speed blade profile at a larger negative attack angle. This problem can also be explained in terms of angle of attack-loss characteristics. However, in consideration of the actual working condition of the compressor, the working point is mainly between a small negative attack angle and a near stall point, so the low-speed simulation can meet the requirements of actual engineering.
S3, after the stator two-dimensional blade profiles are stacked, low-speed analog conversion is carried out on a stator midday flow field containing a stator transition section.
When the stator two-dimensional blade profiles are stacked, the following conditions are met: 1) Important inlet boundary conditions of the high-speed and low-speed transition sections are similar, and the edge strips comprise total pressure distribution, flow distribution and inlet airflow angle distribution of an inlet; 2) After stacking, checking the incoming flow attack angle state of each low-speed stator section, and adjusting the incoming flow attack angle of each stator section to be consistent with that of the high-speed prototype; 3) Adjusting the geometric angle of the outlet of the low-speed stator to make the airflow angle of the outlet of the low-speed stator consistent with that of the high-speed prototype; 4) And adjusting the geometric angle of the inlet of the low-speed stator and the airflow angle of the low-speed incoming flow, so that the D factor is consistent with that of the high-speed prototype under the condition of ensuring that the high-speed stator and the low-speed stator have the same incoming flow attack angle.
After the above adjustment, fig. 7 shows the basic parameters for measuring the stator performance as: comparing the distribution of the factor D, the total pressure loss coefficient and the density-flow ratio in the spanwise direction with the high-speed prototype, it can be seen that the above parameters are well overlapped with the result of the high-speed prototype, and therefore, the result of the three-dimensional flow field obtained at the low speed is also consistent with the result of the high-speed prototype, as shown in fig. 8.
And S4, adjusting a flow channel of the transition section behind the stator according to the actual flow field behind the stator, and completing the low-speed simulation of the coupling of the S-shaped transition section and the stator of the gas compressor. The adjusting method comprises the following steps: by adjusting the area of the stator rear flow channel, the dimensionless isentropic velocity ratio V/V1 distribution of the wall surface of the stator rear flow field is the same.
Comparison of the spanwise distribution of the major parameters of the transition section outlet obtained by the final adjustment with the high-speed prototype is shown in fig. 9, and it can be seen that the S2 flow field of the transition section outlet obtained thereby also remains highly similar to the high-speed prototype.
The total pressure loss of the stator-containing transition section obtained by the final low-speed simulation is compared with that of the high-speed prototype in the variation of the flow angle of the incoming flow as shown in fig. 10. As can be seen from fig. 10, the stator loss obtained by the low-speed simulation is substantially the same as that of the high-speed prototype in the trend of the development with the angle of attack, except that it is slightly larger than that of the high-speed prototype in the state of the small angle of attack; the loss from the stator outlet to the transition section outlet obtained by low-speed simulation is basically consistent with that of a high-speed prototype under various working conditions; the development trend of total loss of the low-speed simulation transition section is consistent with that of the high-speed prototype. Fig. 11 shows a comparison of three-dimensional flow fields of stators in the high-low speed transition section under typical conditions, and it can be seen from fig. 11 that there is good similarity in the high-low speed flow fields.
In addition, fig. 10 also shows the variation of the total pressure loss coefficient of each part with the flow angle of the incoming flow, which is obtained by performing low-speed simulation on the stator but not performing any adjustment on the flow passage of the transition section. As can be seen from fig. 10, in this case, since the flow path of the transition section is not subjected to low-speed conversion, the total pressure loss coefficient from the stator outlet to the transition section outlet deviates greatly from the high-speed prototype; moreover, although the stator characteristic is not much different from the result of the low-speed simulation near the design point, the characteristic of the stator in a large attack angle state is deviated, which is mainly caused by the potential action of a rear flow field; the resulting overall loss characteristics of the transition section are also significantly different from the high speed prototype. This can result in: when the low-speed simulation design of the transition section with the stator blades is carried out, the low-speed simulation conversion of the flow channel of the transition section is necessary, and the low-speed simulation design of the flow channel and the low-speed simulation design of the stator blades are considered at the same time, so that the low-speed flow field is similar to the high-speed flow field.
Example 2
Fig. 2 is a schematic diagram of a transition section including a stator, in which the transition section is separately designed for low-speed simulation and the stator is separately designed for simulation. As shown in fig. 12 and 13, in the prior art, the transition section and the stator are usually subjected to low-speed simulation respectively and then fitted to obtain a low-speed simulation model including the stator transition section, and compared with the prior art, the method disclosed by the invention has the advantages that the similarity of the flow field behind the stator is greatly improved, and the simulation accuracy of the low-speed simulation model can be obviously improved.
Example 3
A low-speed simulation device for coupling an S-shaped transition section and a stator of a gas compressor is characterized in that a model is designed based on the S-shaped transition section and stator coupling low-speed simulation design method of the gas compressor aiming at a high-speed prototype, and then the model is prepared by adopting a 3D printing technology. The device has higher simulation accuracy, the difference of the total pressure loss coefficients of the high-speed and low-speed transition sections is smaller, and the similarity between the low-speed simulation blade profile in a design state to a stall state and a smaller negative attack angle state and the high-speed blade profile is high, so that the low-speed simulation blade profile can be used as a low-speed model to accurately simulate the flow field state of a high-speed prototype.
Although embodiments of the present disclosure have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the disclosure, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The low-speed simulation method for coupling of the S-shaped transition section and the stator of the gas compressor is characterized by comprising the following steps of:
carrying out low-speed simulation design on a flow passage containing a stator transition section;
carrying out low-speed simulation design on a stator two-dimensional blade profile in a stator-containing transition section;
after the stator two-dimensional blade profiles are stacked, carrying out low-speed analog conversion on a stator midday flow field containing a stator transition section;
and adjusting a flow channel of the transition section behind the stator according to the actual flow field behind the stator to complete the low-speed simulation of the coupling of the S-shaped transition section of the gas compressor and the stator.
2. The compressor S-shaped transition section and stator coupling low-speed simulation design method as claimed in claim 1, wherein the similarity criteria to be ensured when performing low-speed simulation design on the flow channel containing the stator transition section include: reynolds number, ratio delta R/L of diameter difference and length in inlet and outlet, ratio Hin/L of inlet height and length, wall dimensionless isentropic velocity ratio V/V1 distribution and hub ratio.
3. The compressor S-shaped transition section and stator coupling low-speed simulation design method as claimed in claim 2, wherein the method for ensuring similarity of distribution of wall surface dimensionless isentropic velocity ratio V/V1 is as follows: by adjusting the internal area of the low-speed simulation transition section, the dimensionless isentropic velocity ratio V/V1 distribution of the high-speed runner wall surface and the low-speed runner wall surface is the same.
4. The compressor S-shaped transition section and stator coupling low-speed simulation design method as claimed in claim 1, wherein the similarity criteria to be ensured when performing low-speed simulation design on the stator two-dimensional blade profile in the stator-containing transition section include: and (3) carrying out dimensionless isentropic velocity distribution on the consistency, the D factor, the Reynolds number and the leaf surface, wherein the Reynolds number is greater than the self-modeling Reynolds number.
5. The compressor S-shaped transition section and stator coupling low-speed simulation design method as claimed in claim 1, wherein when the stator two-dimensional blade profiles are stacked, the following conditions are satisfied:
important inlet boundary conditions of the high-speed and low-speed transition sections are similar, and the edge strips comprise total pressure distribution, flow distribution and inlet airflow angle distribution of an inlet;
after the stacking, the incoming flow attack angle state of each low-speed stator section is checked, and the incoming flow attack angle of each stator section is adjusted to be consistent with that of the high-speed prototype;
adjusting the geometric angle of the outlet of the low-speed stator to make the airflow angle of the outlet of the low-speed stator consistent with that of the high-speed prototype;
and adjusting the geometric angle of the inlet of the low-speed stator and the airflow angle of the low-speed incoming flow, so that the D factor is consistent with that of the high-speed prototype under the condition of ensuring that the high-speed stator and the low-speed stator have the same incoming flow attack angle.
6. The compressor S-shaped transition section and stator coupling low-speed simulation design method as claimed in claim 1, wherein when the flow channel of the stator rear transition section is adjusted according to the actual flow field behind the stator, the adjustment method is as follows: and adjusting the area of the flow channel behind the stator to ensure that the dimensionless isentropic velocity ratio V/V1 distribution of the wall surface of the flow field behind the stator is the same.
7. A compressor S-shaped transition section and stator coupling low-speed simulation device is characterized in that the compressor S-shaped transition section and stator coupling low-speed simulation device is designed and manufactured based on the compressor S-shaped transition section and stator coupling low-speed simulation design method of any one of claims 1-6 aiming at a high-speed prototype.
8. The compressor S-shaped transition section and stator coupling low-speed simulation device of claim 7 is characterized in that after a model designed based on low-speed simulation is prepared, the compressor S-shaped transition section and stator coupling low-speed simulation device is prepared by a 3D printing technology.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117556553A (en) * | 2023-06-09 | 2024-02-13 | 中国空气动力研究与发展中心空天技术研究所 | Low-speed simulated blade profile camber line design method based on small disturbance theory |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117556553A (en) * | 2023-06-09 | 2024-02-13 | 中国空气动力研究与发展中心空天技术研究所 | Low-speed simulated blade profile camber line design method based on small disturbance theory |
| CN117556553B (en) * | 2023-06-09 | 2024-03-19 | 中国空气动力研究与发展中心空天技术研究所 | Low-speed simulated blade profile camber line design method based on small disturbance theory |
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