A method of tailoring turbine blade wake with adjustable trailing edge
By setting an adjustable structure at the trailing edge of the turbine blade, the geometry of the trailing edge can be changed to weaken the wake generation. This solves the problem that existing technologies cannot fundamentally weaken the wake and aerodynamic excitation, and achieves both fine-grained wake control and aerodynamic performance under complex working conditions.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AECC HUNAN AVIATION POWERPLANT RES INST
- Filing Date
- 2026-04-29
- Publication Date
- 2026-06-05
AI Technical Summary
Existing non-uniform design techniques cannot fundamentally reduce the wake and the aerodynamic excitation caused by the wake, and cannot achieve precise and customized wake control under complex working conditions, making aerodynamic excitation problems unpredictable.
An adjustable structure is set at the trailing edge of the turbine blade, and its movement is achieved by a movable connection to change the geometry of the trailing edge, thereby enhancing the interaction between the boundary layer and the mainstream and the wake shear layer, weakening the wake generation process from the source, and realizing refined wake control.
It effectively suppresses aerodynamic excitation, reduces the aerodynamic excitation amplitude at specific frequencies, and has little impact on turbine aerodynamic performance. It also has the capability for customized active wake control and can adapt to complex operating conditions.
Smart Images
Figure CN122148393A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aero-engine technology, and in particular to a method for customizing the wake of turbine blades with adjustable trailing edges. Background Technology
[0002] Existing technologies for solving aerodynamic excitation problems mainly rely on non-uniform guide vane design. The core idea is to slightly alter the turbine blade arrangement (such as pitch and blade geometry) in one or more directions to actively disrupt uniformity, reducing the primary aerodynamic excitation at the cost of acceptable aerodynamic performance loss and improved aerodynamic excitation at other orders. These non-uniform design techniques have achieved widespread application. However, non-uniform design essentially only adjusts the distribution of the total wake energy sensed by the moving blade at different frequencies. That is, non-uniform design achieves a redistribution of wake energy sensed by the moving blade at different frequencies, causing the wake energy sensed by the downstream moving blade to be distributed across more frequencies, thereby reducing vibration energy at specific frequencies. But this design does not change the wake generation process and does not fundamentally weaken the wake and the aerodynamic excitation it causes. Aero-engines operate under highly complex conditions. Non-uniform designs are typically based on design conditions. When the engine operates under complex, non-design conditions, it cannot adjust the wake in real time according to the operating conditions to achieve more precise aerodynamic excitation control. Therefore, existing non-uniform design techniques have shortcomings, such as being unable to fundamentally reduce wakes and the aerodynamic excitation caused by wakes, and being unable to achieve precise and customized wake control for complex operating conditions. These shortcomings may lead to unpredictable and serious aerodynamic excitation problems. Summary of the Invention
[0003] This invention provides a method for customizing the wake of a turbine blade with adjustable trailing edge. By setting an adjustable structure at the trailing edge of the turbine blade, aerodynamic excitation can be effectively suppressed with minimal impact on turbine aerodynamic performance, thus solving the problem that traditional technologies cannot simultaneously achieve low aerodynamic excitation and high aerodynamic performance.
[0004] This invention discloses a method for customizing the wake of a turbine blade with an adjustable trailing edge, the method comprising:
[0005] S1. Obtain a full-ring guide vane, wherein the full-ring guide vane is composed of multiple turbine blades arranged circumferentially;
[0006] The turbine blade includes a blade body and at least one adjustable structure; the adjustable structure is installed in the trailing edge region of the blade body and forms a movable connection with the blade body.
[0007] S2. Select at least one turbine blade from the full-annular guide vanes;
[0008] S3. Drive the adjustable structure on the selected turbine blade to move.
[0009] Furthermore, the adjustable structure is rotatably connected to the blade body via a rotating shaft.
[0010] Furthermore, the adjustable structure is movably connected to the blade body via a slide rail mechanism.
[0011] Furthermore, the adjustable structure is a deformable portion protruding from the trailing edge surface, a deformable portion recessed from the trailing edge surface, an additional spoiler, an additional airfoil section, or a movable section formed by a portion of the trailing edge.
[0012] Furthermore, the inherent structural features include one or more of the following: type of adjustable structure, inherent shape, installation position, direction of movement, maximum adjustable angle, and size.
[0013] Further, selecting at least one turbine blade from the full-annular guide vanes includes:
[0014] At least one turbine blade in the full-ring guide vanes is selected asymmetrically.
[0015] Furthermore, the number of turbine blades selected and the motion parameters of the adjustable structure are determined based on the operating conditions of the turbine engine to which the full-ring guide vane belongs.
[0016] Furthermore, among the selected turbine blades, the kinematic parameters of the adjustable structures on at least two turbine blades are different from each other.
[0017] Furthermore, the adjustable structural motion on the selected turbine blades includes:
[0018] Drive the adjustable structure to rotate or translate.
[0019] Furthermore, in the full-ring guide vane, the adjustable structures on at least two turbine blades are distinguished in at least one of their inherent structural features.
[0020] Compared with the prior art, the present invention has the following beneficial effects:
[0021] Existing technologies typically employ non-uniform design or trailing edge geometry treatment. Non-uniform design can only reduce aerodynamic excitation at a specific frequency by redistributing the total energy of the full-circle wake at that frequency. Furthermore, non-uniform design disrupts the symmetry of the original turbine blade geometry, significantly impacting the flow field structure and turbine performance. Trailing edge geometry treatments, such as serrated trailing edges, can only weaken the wake by strengthening the boundary layer and the interaction between the wake and the mainstream.
[0022] This invention can fully leverage the advantages of non-uniform design and trailing edge geometry treatment. It can reduce aerodynamic excitation at specific frequencies and weaken the trail by utilizing the interaction between the boundary layer, trail, and mainstream, while also possessing strong customized active trail control capabilities. Attached Figure Description
[0023] 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.
[0024] Figure 1 This is a flowchart of a turbine blade wake customization method according to an embodiment of the present invention;
[0025] Figure 2 This is a first schematic diagram of an adjustable structure on a turbine blade in one embodiment of the present invention;
[0026] Figure 3 This is a second schematic diagram of an adjustable structure on a turbine blade in one embodiment of the present invention;
[0027] Figure 4 This is a third schematic diagram of an adjustable structure on a turbine blade in one embodiment of the present invention;
[0028] Figure 5 This is a fourth schematic diagram of an adjustable structure on a turbine blade in one embodiment of the present invention;
[0029] Figure 6 This is a fifth schematic diagram of an adjustable structure on a turbine blade in one embodiment of the present invention;
[0030] Figure 7 This is a schematic diagram of a full-ring guide vane in one embodiment of the present invention;
[0031] In the diagram, 1-blade body, 2-adjustable structure, 3-full ring guide vane. Detailed Implementation
[0032] 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.
[0033] In one embodiment, a method for customizing the wake of turbine blades with adjustable trailing edges is provided, such as... Figure 1 As shown, the method includes steps S1 to S3.
[0034] S1. Obtain the full-ring guide vane 3, which is composed of multiple turbine blades arranged circumferentially.
[0035] The turbine blade includes a blade body 1 and at least one adjustable structure 2; the adjustable structure 2 is installed in the trailing edge region of the blade body 1 and forms a movable connection with the blade body 1.
[0036] In this embodiment, an adjustable structure 2 is provided in the trailing edge region of the turbine blade via a movable connection, making the geometry of the turbine blade trailing edge adjustable. When the adjustable structure 2 is driven to move, it directly changes the local geometry of the trailing edge, thereby enhancing the interaction between the trailing edge boundary layer and the mainstream, as well as the interaction between the wake shear layer and the mainstream. This physically intervenes in and weakens the wake generation process, achieving the effect of reducing the aerodynamic excitation caused by the wake from the source.
[0037] In this embodiment, the adjustable structure 2 on each turbine blade of the full-ring guide vane 3 can be independently adjusted and moved. By finely adjusting the geometry of the trailing edge, the flow interaction can be enhanced, and the wake can be directly weakened from the source.
[0038] S2. Select at least one turbine blade from the full-ring guide vanes 3.
[0039] S3. Drive the movement of the adjustable structure 2 on the selected turbine blade.
[0040] The method in this embodiment adjusts the geometry of the trailing edge of some of the guide vanes in the full-ring guide vane 3, thereby adjusting the direction of part of the wake. This eliminates the periodicity of the aerodynamic excitation of the wake on the downstream moving blades, thus reducing the excitation amplitude at a specific frequency. On the other hand, by fine-tuning the geometry of the trailing edge, the interaction between the trailing edge boundary layer and the mainstream, as well as the interaction between the wake shear layer and the mainstream, are enhanced, thereby weakening the wake intensity and the aerodynamic excitation it causes.
[0041] Existing methods can only reduce the aerodynamic excitation amplitude to a limited extent from one perspective. However, the method in this embodiment can not only reduce the aerodynamic excitation of the wake on the blade at a specific frequency through the non-uniform frequency shifting method of the wake, but also directly weaken the wake at its source, thereby reducing the aerodynamic excitation generated by the wake on the downstream blade.
[0042] In some embodiments of this example, the adjustable structure 2 is rotatably connected to the blade body 1 via a rotating shaft; or, the adjustable structure 2 is translatably connected to the blade body 1 via a slide rail mechanism.
[0043] When a rotating shaft is used for connection, the adjustable structure 2 can rotate around the rotating shaft at a certain angle, thereby continuously and precisely changing the local profile or exhaust angle of the trailing edge, and the formation process of the trail can be controlled in real time.
[0044] When a slide rail mechanism is used for connection, the adjustable structure 2 can change its position relative to the main blade body through linear motion (e.g., extend the adjustable structure 2 or retract the adjustable structure 2), thereby changing the equivalent thickness or profile of the trailing edge and providing an adjustment degree of freedom for wake control.
[0045] In some implementations of this embodiment, such as Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown, the adjustable structure 2 is a protruding deformation part, a recessed deformation part, an additional spoiler, an additional airfoil section, or a movable section consisting of a part of the trailing edge.
[0046] The protruding deformation portion is a deformation portion that protrudes outward from the trailing edge surface, and the recessed deformation portion is a deformation portion that is recessed inward from the trailing edge surface.
[0047] In some embodiments of this example, the inherent structural features include one or more of the following: type of adjustable structure 2, inherent shape, installation position, direction of movement, maximum adjustable angle, and size.
[0048] In some embodiments of this example, selecting at least one turbine blade from the full-ring guide vanes 3 includes: asymmetrically selecting at least one turbine blade from the full-ring guide vanes 3.
[0049] The method in this embodiment can asymmetrically select a portion of the turbine blades for adjustment of the adjustable structure 2, which can be equivalent to a non-uniform guide vane pitch wake, thereby reducing the aerodynamic excitation of the downstream moving blades at a specific frequency. Moreover, since the adjustable trailing edge causes very little geometric change to the turbine blades, its impact on aerodynamic performance is far less than that of the non-uniform pitch design.
[0050] In some embodiments of this example, the number of turbine blades selected and the motion parameters of the adjustable structure 2 are determined according to the operating conditions of the turbine engine to which the full-ring guide vane 3 belongs.
[0051] The method in this embodiment can modify the number of turbine blades and the corresponding motion parameters of the adjustable structure 2 according to the actual operating conditions of the turbine engine. This allows the adjustment of the wake to no longer be limited to fixed design conditions, enabling real-time, adaptive, and precise adjustment in the face of complex and variable operating conditions of the aero-engine. This ensures that the aerodynamic excitation of the wake on the downstream blades can be effectively reduced under different operating conditions. Figure 7 As shown in the figure, the red part represents the turbine blades selected for adjustable structure adjustment, and the yellow part represents the turbine blades not subject to adjustable structure adjustment.
[0052] In some embodiments of this example, the motion parameters of the adjustable structures between the selected turbine blades may be different. For example, the motion parameters of the adjustable structures on at least two turbine blades may be different from each other.
[0053] In some embodiments of this example, driving the adjustable structure 2 on the selected turbine blade to move includes driving the adjustable structure 2 to rotate or translate.
[0054] In some embodiments of this example, the adjustable structures 2 on at least two turbine blades of the full-ring guide vane 3 are distinct in at least one inherent structural feature. The differences in the adjustable structures 2 on at least two turbine blades of the full-ring guide vane 3 in this example allow for the disruption of the periodic distribution of the wake by adjusting part or all of the guide vane trailing edges, thereby generating a non-uniform wake field. This eliminates the periodicity of the wake's aerodynamic excitation on the downstream blades, thus reducing the excitation amplitude at a specific frequency.
[0055] In this embodiment, the full-ring guide vane 3 achieves synergistic reduction of source and non-uniform frequency misalignment through the combination of adjustable structure 2 and differentiated design, thereby having a better excitation reduction capability.
[0056] 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 method for customizing the wake of a turbine blade with adjustable trailing edge, characterized in that, The method includes: S1. Obtain a full-ring guide vane, wherein the full-ring guide vane is composed of multiple turbine blades arranged circumferentially; The turbine blade includes a blade body and at least one adjustable structure; the adjustable structure is installed in the trailing edge region of the blade body and forms a movable connection with the blade body. S2. Select at least one turbine blade from the full-annular guide vanes; S3. Drive the adjustable structure on the selected turbine blade to move.
2. The method for customizing the wake of an adjustable turbine blade according to claim 1, characterized in that, The adjustable structure is rotatably connected to the blade body via a rotating shaft.
3. The method for customizing the wake of an adjustable turbine blade according to claim 1, characterized in that, The adjustable structure is movably connected to the blade body via a slide rail mechanism.
4. The method for customizing the wake of an adjustable turbine blade according to claim 1, characterized in that, The adjustable structure is a deformable portion protruding from the trailing edge surface, a deformable portion recessed from the trailing edge surface, an additional spoiler, an additional airfoil section, or a movable section consisting of a portion of the trailing edge.
5. The method for customizing the wake of an adjustable turbine blade according to claim 1, characterized in that, The inherent structural features include one or more of the following: type of adjustable structure, inherent shape, installation location, direction of movement, maximum adjustable angle, and size.
6. The method for customizing the wake of an adjustable turbine blade according to claim 1, characterized in that, Selecting at least one turbine blade from the full-ring guide vanes, including: At least one turbine blade in the full-ring guide vanes is selected asymmetrically.
7. The method for customizing the wake of an adjustable turbine blade according to claim 1, characterized in that, The number of turbine blades selected and the motion parameters of the adjustable structure are determined based on the operating conditions of the turbine engine to which the full-ring guide vane belongs.
8. The method for customizing the wake of an adjustable turbine blade according to claim 7, characterized in that, Among the selected turbine blades, the kinematic parameters of the adjustable structures on at least two turbine blades are different from each other.
9. The method for customizing the wake of an adjustable turbine blade according to claim 1, characterized in that, Driven by adjustable structural motion on the selected turbine blades, including: Drive the adjustable structure to rotate or translate.
10. The method for customizing the wake of an adjustable turbine blade according to claim 1, characterized in that, In the full-ring guide vane, the adjustable structures on at least two turbine blades are distinguished by at least one inherent structural feature.