Turbine shock disturbance modulation method based on array modeling
By setting an array of protrusions and depressions in the trailing edge region of the guide vane, the extended shock wave is weakened and the reflected shock wave is enhanced, which solves the problems of unclear aerodynamic excitation suppression effect and insufficient control stability in the prior art, and improves the reliability and life of the turbine rotor.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AECC HUNAN AVIATION POWERPLANT RES INST
- Filing Date
- 2026-03-13
- Publication Date
- 2026-05-29
AI Technical Summary
Existing shock wave control technologies for aero-engine turbine guide vanes mainly focus on improving aerodynamic performance, while lacking research on aerodynamic excitation suppression. This results in unclear control effects under different operating conditions and uncertain stability of shock wave control. Furthermore, the influence range and control strength of existing methods are insufficient.
An array of protrusions and depressions is set in the trailing edge region of the guide vane. By efficiently modulating the intensity of the shock wave at the trailing edge of the guide vane, the extended shock wave is weakened and the reflected shock wave is enhanced, thereby effectively suppressing the aerodynamic excitation amplitude.
It significantly reduced the first-order excitation amplitude of the rotor, improved the life of the turbine rotor blades and the reliability of the system, and reduced the aerodynamic losses caused by shock waves.
Smart Images
Figure CN122106690A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aero-engine technology, and in particular to a turbine shock wave disturbance modulation method based on array design. Background Technology
[0002] Modern aero-engine turbines often operate under transonic or supersonic conditions. The trailing edge shock wave at the turbine guide vane exit has a complex impact on the unsteady flow within the turbine passage. On the one hand, it causes severe shock wave losses; on the other hand, it periodically sweeps across the rotor blades, causing strong pressure pulsations on the blade surface and increasing the amplitude of unsteady aerodynamic excitation experienced by the rotor. Currently, researchers have proposed a series of shock wave control techniques to address the problem of severe shock wave losses, including adjusting the turbine blade curvature and applying individual bulge disturbances.
[0003] Existing research primarily focuses on improving turbine aerodynamic performance by controlling shock wave intensity, rather than designing for aerodynamic excitation suppression. There is a lack of research on guide vane shock wave control based on aerodynamic excitation suppression. These shock wave control techniques aimed at improving aerodynamic performance still have several key limitations:
[0004] (1) The research objectives and principles of existing methods are not aimed at aerodynamic excitation suppression. Their control effect on aerodynamic excitation under different working conditions is still unclear, and the stability of shock wave control is uncertain.
[0005] (2) Although introducing a single disturbance on the surface of the guide vane can achieve local flow regulation, its influence range is limited and its control strength is insufficient. Summary of the Invention
[0006] This invention provides a turbine shock wave disturbance modulation method based on array design, which effectively suppresses the aerodynamic excitation amplitude by efficiently modulating the intensity of the shock wave at the trailing edge of the guide vane.
[0007] This invention discloses a turbine shock wave perturbation modulation method based on array design, comprising:
[0008] At least one array of protrusions is provided in the trailing edge region in front of the trailing edge point of the suction surface of the guide vane body.
[0009] At least one array of recessed structures is provided in the trailing edge region in front of the trailing edge point of the pressure surface of the guide vane body.
[0010] At least one array of recessed structures is provided on the suction surface of the guide vane body, and in front of the expected reflection point of the inward shock wave from the pressure surface to the suction surface.
[0011] Furthermore, the starting point of the array-type protrusion structure is located at 85% of the axial chord length, and the ending point is located at 96% of the axial chord length.
[0012] The array of recessed structures in the tail edge region of the pressure surface starts at 84% of the axial chord length and ends at 92% of the axial chord length.
[0013] The starting point of the array of recessed structures on the suction surface, located before the expected reflection point, is at 50% of the axial chord length, and the ending point is at 58% of the axial chord length.
[0014] Furthermore, the starting point of the array-type protrusion structure is located at 85% of the axial chord length, and the ending point is located at 96% of the axial chord length.
[0015] Furthermore, the starting point of the array-type recessed structure in the tail edge region of the pressure surface is located at 84% of the axial chord length, and the ending point is located at 92% of the axial chord length.
[0016] Furthermore, the starting point of the array of recessed structures on the suction surface, located before the expected reflection point, is at 50% of the axial chord length, and the ending point is at 58% of the axial chord length.
[0017] Furthermore, the endpoint of the array of recessed structures on the suction surface, located before the expected reflection point, is 4% of the axial chord length away from the expected reflection point.
[0018] Furthermore, the height of the array of protruding structures is 1.5 mm, and the depth of the array of recessed structures is 1.5 mm.
[0019] Furthermore, the array-type protrusion structure is composed of its shaped units distributed at intervals along the blade span.
[0020] Furthermore, the styling unit of the array-type protrusion structure is a convex shape or a wedge shape.
[0021] Furthermore, the array-type recessed structure is composed of its shaped units distributed at intervals along the blade span.
[0022] Furthermore, the styling unit of the array-type recessed structure is a pit or groove shape.
[0023] Compared with the prior art, the present invention has the following beneficial effects:
[0024] In the prototype guide vane, the intensity of the outward-extending shock wave is significantly higher than that of the reflected shock wave. Therefore, the aerodynamic excitation caused by the outward-extending shock wave dominates, resulting in a high first-order excitation amplitude on the rotor. In contrast, this invention, by setting a protruding shape in front of the outward-extending shock wave at the guide vane trailing edge, and a concave shape in front of the inward-extending shock wave at the guide vane trailing edge and the reflection point of the guide vane suction surface, effectively weakens the outward-extending shock wave while relatively enhancing the intensity of the reflected shock wave. This reduces the difference in disturbance experienced by the rotor under the action of the two shock waves. This change significantly reduces the first-order excitation amplitude on the rotor, while correspondingly increasing the second-order excitation amplitude. Since high-frequency excitation is generally difficult to induce resonance in rotor blades, the significant reduction in the first-order excitation amplitude helps extend blade life and improve the overall reliability of the system. Attached Figure Description
[0025] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments of the present invention will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0026] Figure 1 This is a flowchart of a turbine shock wave disturbance modulation method according to an embodiment of the present invention;
[0027] Figure 2 This is a schematic diagram of the array shape distribution from the perspective of the turbine S1 flow surface in one embodiment of the present invention;
[0028] Figure 3 This is a schematic diagram of the raised portion in one embodiment of the present invention;
[0029] Figure 4 This is a schematic diagram of the recessed portion in one embodiment of the present invention;
[0030] Figure 5 This is a schematic diagram of the distribution of the recessed portion on the guide vane surface from the perspective of the pressure surface in one embodiment of the present invention;
[0031] Figure 6 This is a schematic diagram showing the distribution of recesses and ridges on the guide vane surface from the perspective of the suction surface in one embodiment of the present invention;
[0032] In the figure, 1-array of protruding structures, 2-array of recessed structures, 3-guide vane body, 4-induced shock wave, 5-outward shock wave, 6-expansion wave, 7-inward shock wave, 8-reflected shock wave, 9-reflection point. Detailed Implementation
[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0034] In one embodiment, such as Figure 1 As shown, a turbine shock wave perturbation modulation method based on array design is provided, including the following steps:
[0035] S1. At least one array of protrusions is provided in the trailing edge region in front of the trailing edge point of the suction surface of the guide vane body.
[0036] In this step, the array of protruding structures is located in the trailing edge region of the guide vane's suction surface, specifically upstream (in front) of the extended shock wave at the guide vane's trailing edge. When the supersonic airflow passes through this array of protruding structures, it experiences a continuous compression disturbance, causing the airflow direction to deflect and thus inducing a weaker induced shock wave upstream of the structure. After passing through this induced shock wave, the airflow velocity decreases, which correspondingly reduces the wavefront Mach number of the subsequent extended shock wave, effectively weakening the intensity of the extended shock wave.
[0037] In some embodiments of this example, the starting point of the array-type protrusion structure is located at 85% of the axial chord length, and the ending point is located at 96% of the axial chord length.
[0038] In some embodiments of this example, the height of the array of protrusions is 1.5 mm.
[0039] In these implementations, by specifically limiting the start point, end point, and height of the array of protrusions, precise disturbance of the shock wave can be achieved, thus improving the disturbance effect.
[0040] In some embodiments of this example, the array-type protrusion structure is composed of its shaped units distributed at intervals along the blade span.
[0041] In these embodiments, the array of protrusions is discretized in the spanwise direction to form a row of distributed arrays, which helps to minimize the losses caused by induced shock waves, thereby reducing the aerodynamic losses caused by induced shock waves as much as possible.
[0042] In some embodiments of this example, the styling unit of the array-type protrusion structure is a convex shape or a wedge shape.
[0043] S2. At least one array of recessed structures is provided in the trailing edge region in front of the trailing edge point of the pressure surface of the guide vane body.
[0044] In this step, the array-type recessed structure is located in the trailing edge region of the guide vane body pressure surface, specifically upstream (in front) of the inward-extending shock wave at the trailing edge of the guide vane. When the supersonic airflow passes through this array-type recessed structure, it will be subjected to an expansion disturbance, causing a change in the airflow direction and inducing the formation of an expansion wave. The degree of airflow expansion increases, leading to an increase in the wavefront Mach number of the inward-extending shock wave, thereby enhancing the intensity of the inward-extending shock wave.
[0045] In some embodiments of this example, the starting point of the array-like recessed structure in the tail edge region of the pressure surface is located at 84% of the axial chord length, and the ending point is located at 92% of the axial chord length.
[0046] In some embodiments of this example, the depth of the array-type recessed structure recessed into the blade body is 1.5 mm.
[0047] In some embodiments of this example, the array-type recessed structure is composed of its shaping units distributed at intervals along the blade span.
[0048] In some embodiments of this example, the styling unit of the array-type recessed structure is a pit or groove.
[0049] S3. On the suction surface of the guide vane body, and before the expected reflection point of the inward shock wave from the pressure surface to the suction surface, at least one array-type recessed structure is provided.
[0050] In this step, another array-type recessed structure is set on the suction surface of the guide vane body, upstream (in front of) the inward shock wave reflection point. This array-type recessed structure is used to premodulate the shock wave that is about to reach the reflection point. It applies an expansion disturbance to the supersonic airflow flowing through this area, forming an expansion wave that induces the airflow to change direction. At the same time, it increases the local airflow Mach number in front of the reflection point, thereby enhancing the intensity of the subsequent reflected shock wave.
[0051] In some embodiments of this example, the starting point of the array of recessed structures on the suction surface prior to the expected reflection point is located at 50% axial chord length, and the ending point is located at 58% axial chord length.
[0052] In some embodiments of this example, the recess depth of the array-type recessed structure is 1.5 mm.
[0053] In some embodiments of this example, the endpoint of the array-shaped recessed structure on the suction surface, located before the expected reflection point, is 4% of the axial chord length away from the expected reflection point. This distance ensures that the array-shaped recessed structure is stably located upstream of the foremost reflection point under all target operating conditions, thereby achieving reliable shock wave control.
[0054] In some embodiments of this example, the array-type recessed structure is composed of its shaping units distributed at intervals along the blade span.
[0055] In some embodiments of this example, the styling unit of the array-type recessed structure is a pit or groove.
[0056] This embodiment effectively weakens the outward-extending shock wave by setting an array of protruding structures at the trailing edge of the guide vane's suction surface and array of recessed structures at the trailing edge of the pressure surface and in front of the shock wave reflection point of the suction surface, while relatively enhancing the inward-extending shock wave and its reflected shock wave, thus achieving differentiated modulation of the trailing edge shock wave.
[0057] When the guide vane trailing edge shock wave periodically sweeps across the downstream rotor blades, the induced weak shock wave does not cause high pressure pulsation on the rotor surface; however, the weakened outward shock wave and the enhanced reflected shock wave cause pressure pulsation on the rotor blade surface twice. Compared to the traditional guide vane, where the outward shock wave is much stronger than the reflected shock wave, resulting in the excitation caused by the outward shock wave (first-order excitation) dominating, this embodiment significantly reduces the difference in disturbance intensity experienced by the rotor under the action of the two shock waves through the above modulation, resulting in a significant reduction in the amplitude of the first-order excitation experienced by the rotor, while the amplitude of the higher-frequency second-order excitation increases accordingly. Since high-frequency excitation is unlikely to induce rotor blade resonance, the significant reduction in the amplitude of the first-order excitation is very beneficial to improving the fatigue life of the turbine rotor blades and the operational reliability of the entire rotor system.
[0058] like Figure 2 As shown, the turbine guide vane formed according to the method of this embodiment includes a guide vane body 3, an array of protruding structures and two arrays of recessed structures. A schematic diagram of the array of protruding structures 1 is shown below. Figure 3 As shown in the figure, the structural schematic diagram of the array-type recessed structure 2 is as follows: Figure 4 As shown, Figure 3 and Figure 4 In this context, Ma represents the Mach number. The array of protruding structures is disposed on the trailing edge region of the suction surface of the guide vane body; one array of recessed structures is disposed on the trailing edge region of the pressure surface of the guide vane body; and another array of recessed structures is disposed on the suction surface of the guide vane body, located before the expected reflection point of the inwardly extending shock wave at the trailing edge of the pressure surface of the guide vane body.
[0059] Figure 5 The distribution of the array of recessed structures 2 on the guide vane surface is shown from the perspective of the pressure surface. Figure 6The diagram shows the positional distribution of the arrayed protrusion structure 1 and arrayed recessed structure 2 on the guide vane surface from the suction surface perspective. In this embodiment, the guide vane surface is provided with the arrayed protrusion structure 1 and arrayed recessed structure 2, which effectively weakens the outward shock wave 5 and relatively enhances the intensity of the reflected shock wave 8, thereby reducing the difference in disturbance experienced by the rotor under the action of the two shock waves. Through efficient modulation of the shock wave intensity at the guide vane trailing edge, effective suppression of the aerodynamic excitation amplitude is achieved.
[0060] It should be understood that the sequence number of each step in the above embodiments does not imply the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present invention.
[0061] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the above-described division of functional units and modules is used as an example. In practical applications, the above functions can be assigned to different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above.
[0062] The above-described embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be included within the protection scope of the present invention.
Claims
1. A turbine shock wave perturbation modulation method based on array design, characterized in that, include: At least one array of protrusions is provided in the trailing edge region in front of the trailing edge point of the suction surface of the guide vane body. At least one array of recessed structures is provided in the trailing edge region in front of the trailing edge point of the pressure surface of the guide vane body. At least one array of recessed structures is provided on the suction surface of the guide vane body, and in front of the expected reflection point of the inward shock wave from the pressure surface to the suction surface.
2. The turbine shock wave perturbation modulation method based on array design according to claim 1, characterized in that, The starting point of the array-type protrusion structure is located at 85% of the axial chord length, and the ending point is located at 96% of the axial chord length.
3. The turbine shock wave perturbation modulation method based on array design according to claim 1, characterized in that, The array of recessed structures in the tail edge region of the pressure surface starts at 84% of the axial chord length and ends at 92% of the axial chord length.
4. The turbine shock wave perturbation modulation method based on array design according to claim 1, characterized in that, The starting point of the array of recessed structures on the suction surface, located before the expected reflection point, is at 50% of the axial chord length, and the ending point is at 58% of the axial chord length.
5. The turbine shock wave perturbation modulation method based on array design according to claim 4, characterized in that, The endpoint of the array of recessed structures on the suction surface, located before the expected reflection point, is 4% of the axial chord length from the expected reflection point.
6. The turbine shock wave perturbation modulation method based on array design according to claim 1, characterized in that, The raised height of the array-type protrusion structure is 1.5 mm, and the recessed depth of the array-type recessed structure is 1.5 mm.
7. The turbine shock wave perturbation modulation method based on array design according to claim 1, characterized in that, The array-type protrusion structure is composed of its shaped units distributed at intervals along the blade span.
8. The turbine shock wave perturbation modulation method based on array design according to claim 7, characterized in that, The styling unit of the array-type protrusion structure is a convex shape or a wedge shape.
9. The turbine shock wave perturbation modulation method based on array design according to claim 1, characterized in that, The array-type recessed structure is composed of its shaped units distributed at intervals along the blade span.
10. A turbine shock wave perturbation modulation method based on array design according to claim 9, characterized in that, The styling unit of the array-type recessed structure is a pit or groove.