CN112523809A - Method for inhibiting unsteady airflow excitation force of turbine rotor blade - Google Patents
Method for inhibiting unsteady airflow excitation force of turbine rotor blade Download PDFInfo
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- CN112523809A CN112523809A CN202011381166.4A CN202011381166A CN112523809A CN 112523809 A CN112523809 A CN 112523809A CN 202011381166 A CN202011381166 A CN 202011381166A CN 112523809 A CN112523809 A CN 112523809A
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- blade
- trailing edge
- turbine
- sawtooth
- blades
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
Abstract
The invention relates to a method for inhibiting the excitation force of unsteady airflow of a turbine rotor blade, and belongs to the technical field of turbine blade aerodynamic design. According to the actual flow condition in the turbine, the saw tooth structures are arranged in the range of partial or all blade heights of the tail edge of the guide blade aiming at all or part of blades of the blade row to form the saw tooth tail edge guide blade. The invention utilizes the sawtooth structure of the trailing edge of the guide vane to destroy the spanwise consistency of the trailing edge vortex, weaken the trailing edge strength and reduce the pressure pulsation of the trailing edge area, thereby reducing the unsteady airflow exciting force borne by the downstream turbine rotor vane, ensuring the safe and reliable work of the turbine part and reducing the risk of high-cycle fatigue fracture of the turbine part. The sawtooth tail edge has the characteristics of simple structural form, few control parameters, easiness in processing and the like, and is easy to popularize and apply in the engineering field.
Description
Technical Field
The invention belongs to the technical field of turbine blade aerodynamic design, and particularly relates to a method for inhibiting excitation force of unsteady airflow of a turbine rotor blade.
Background
Turbines are key components that affect the performance, life, and reliability of aircraft gas turbine engines. The internal flow of the turbine is three-dimensional, viscous and unusual in nature, and is accompanied by flow separation, shock waves and interference of the shock waves and a boundary layer, wake flow of an upstream blade row, dynamic and static interference and other complex flow phenomena. Due to the instability of the flow, the flow field in the turbine is not only unusual, but also has vortex micelles with different sizes and even very different sizes, and the vortex micelles are expressed as multi-scale characteristics in space. In addition, there is an exchange of force and momentum at the interface of the flow field and the blade solid domain inside the turbine. Research results show that the extreme flow not only affects the aerodynamic performance of the turbine blade, but also induces unsteady airflow exciting force causing blade vibration fatigue, and even causes high-cycle fatigue fracture failure of the turbine rotor blade when the unsteady airflow exciting force is severe, so that the safe operation of a turbine component and an engine is affected. Therefore, it is an important approach to enhance the operational reliability of turbine components to provide a solution for suppressing the excitation force of the unsteady flow of the rotor blade, thereby reducing the risk of high cycle fatigue fracture.
Inspired by the quiet flight characteristic of the owl, researchers firstly apply a sawtooth structure on the front edge and the tail edge of the wing profile and further research the action effect of the sawtooth structure on aerodynamic noise and performance in impeller machines such as wind turbines and air compressors. The influence of the sawtooth structure is mainly reflected in the influence on the downstream pressure distribution and the wake flow field characteristics, and research results show that on one hand, pressure surface boundary layers between sawteeth and near the trailing edge are influenced by the increase of turbulence intensity of a near wall surface and a wake shear layer, the shedding process and the shedding position of the trailing edge vortex are changed, the instability degree of the trailing edge vortex is increased, so that the spanwise correlation of the trailing edge vortex is inhibited, and the energy of the trailing edge vortex is weakened; on the other hand, the sawtooth trailing edge structure also reduces the speed pulsation near the trailing edge and in the wake area, breaks large-scale vortexes into small-scale vortexes, strengthens the flow blending and the speed attenuation of the wake area, enables the flow field distribution of the wake area to be more uniform, weakens the span-wise consistency of the wake area, and reduces the influence of wake flow on the downstream flow field.
Although the research on the sawtooth tail edge aims to reduce noise, expand stability and reduce flow loss, the research is carried out on a gas compressor or a wind turbine. However, the turbine, the gas compressor and the wind turbine belong to the same impeller machine, and the deep analysis of the wake flow field structure also shows that the sawtooth trailing edge can destroy the spanwise consistency of the trailing edge vortex, weaken the strength of the wake and reduce the pressure pulsation amplitude of the wake area, which provides possibility for controlling the wake-guided dynamic and static interference flow field in the turbine and inhibiting the airflow exciting force of the rotor blade by using the sawtooth trailing edge guider blade.
Disclosure of Invention
Technical problem to be solved
The technical problem to be solved by the invention is as follows: how to design a scheme for inhibiting the unsteady airflow excitation force of the rotor blade.
(II) technical scheme
In order to solve the technical problem, the invention provides a method for inhibiting the excitation force of the unsteady airflow of the turbine rotor blade.
Preferably, in the method, the profile of the sawtooth structure is designed to be in a form of a sine-like curve, a triangle, a trapezoid or a combination of any one or more of the sine-like curve, the triangle, the trapezoid or the combination, wherein the profile of the sawtooth structure is defined by two geometric parameters, namely an amplitude a and a wavelength W, which are constant values for a certain application object.
Preferably, in the method, the design wave amplitude A takes a value in a range of 1% -3% of the length of the middle arc, and the design wavelength W takes a value in a range of 5% -25% of the chord length.
Preferably, in the method, the spanwise height of the sawtooth structure is designed to be arranged within the full lobe height of the trailing edge, or within only the lower half lobe height or the upper half lobe height of the trailing edge.
Preferably, in the method, the sawtooth structure is provided on all blades of the blade row or on a part of the blades of the blade row.
Preferably, in the method, when the sawtooth structures are arranged on part of the blades of the blade row, the blades of the 180-degree sector are designed into the sawtooth structures, and a two-sector asymmetric trailing edge aerodynamic layout is formed.
Preferably, in the method, the saw-tooth structure is designed to be composed of a plurality of continuous saw-teeth or a segmented continuous saw-tooth.
The invention also provides a structure for inhibiting the unsteady airflow excitation force of the turbine rotor blade, which is designed by the method.
The invention also provides application of the method in the technical field of turbine blade aerodynamic design.
The invention also provides an application of the structure in the technical field of turbine blade aerodynamic design.
(III) advantageous effects
According to the actual flow condition in the turbine, the saw tooth structures are arranged in the range of partial or all blade heights of the tail edge of the guide blade aiming at all or part of blades of the blade row to form the saw tooth tail edge guide blade. The invention utilizes the sawtooth structure at the trailing edge of the guide vane to destroy the spanwise consistency of the trailing edge vortex, weaken the strength of the trailing edge, reduce the pressure pulsation of a trailing edge area and destroy the spanwise consistency of the trailing edge vortex, thereby reducing the unsteady airflow exciting force borne by the downstream turbine rotor vane, ensuring the safe and reliable work of the turbine component, reducing the risk of high cycle fatigue fracture of the turbine component and enhancing the working reliability of the turbine component. The sawtooth tail edge has the characteristics of simple structural form, few control parameters, easiness in processing and the like, and is easy to popularize and apply in the engineering field.
Drawings
FIG. 1 is a schematic diagram of the geometric parameter definition of a sawtooth structure according to the present invention;
FIG. 2 is a schematic view of the full-blade high-serration trailing edge configuration of a vane of the present invention;
FIG. 3 is a schematic view of the structure of the high sawtooth trailing edge of the lower half of the vane of the present invention;
FIG. 4 is a schematic view of the high serrated trailing edge structure of the upper half of the vane of the present invention;
FIG. 5 is a schematic view of the serrated trailing edge configuration of the row full vane of the present invention;
FIG. 6 is a schematic view of the blade row section director blade arrangement serrated trailing edge configuration of the present invention;
FIG. 7 is a schematic view of a blade section height segmented continuous sawtooth trailing edge structure of a vane of the invention.
Detailed Description
In order to make the objects, contents, and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
According to the invention, the tail edge of the guide vane is designed into a sawtooth structure, so that the unsteady airflow excitation force of the turbine rotor blade is reduced. For different turbines, the internal flow conditions of the turbines are greatly different, and although the sawtooth trailing edge structure can weaken the strength of a wake, destroy the spanwise consistency of wake vortexes and reduce pressure pulsation of a wake region, the selection of tooth type geometric parameters is closely related to the action effect of the sawtooth trailing edge structure. It is worth noting that the sawtooth structure changes the original trailing edge form, influences the flow field structure of the turbine, especially the blade rows near the trailing edge and downstream thereof, and certainly brings certain influence to the aerodynamic performance of the turbine. In order to reduce the influence degree of the sawtooth trailing edge structure on the turbine aerodynamic performance as much as possible and reduce the unsteady airflow excitation force borne by the rotor blade to the maximum extent, before the sawtooth trailing edge structure of the turbine guider blade is designed, the actual flow condition inside the turbine must be obtained through modes of experiments, numerical calculation, theoretical analysis and the like, the flow characteristics and the distribution form of the wake flow causing the unsteady airflow excitation force are known, and the key geometric parameters of the sawtooth trailing edge structure are determined according to the information.
Based on the above analysis, as shown in fig. 1, the profile of the sawtooth trailing edge structure is in a sine-like curve form, or can be in a triangle, trapezoid or combination form, and is defined by two geometric parameters of amplitude and wavelength, wherein the tooth form of the sawtooth trailing edge structure is defined by two key geometric parameters of amplitude a and wavelength W, the amplitude and the wavelength are constant values for a determined application object, wherein the amplitude a takes a value within 1% -3% of the length of the middle arc, and the wavelength W takes a value within 5% -25% of the chord length.
As shown in fig. 2, 3 and 4, the spanwise height of the sawtooth trailing edge structure can be determined according to the actual flow condition inside the turbine, and the sawtooth structure can be arranged in the full blade height range of the trailing edge, only in the lower half blade height or the upper half blade height range of the trailing edge, or in other local blade height ranges. Because the more outstanding scope of action of sawtooth structure to the flow suppression effect of director blade wake is mainly located the lower half blade height, and changes the potential flow interference intensity that static interference caused and weaken gradually along with the improvement of spanwise position, still in order to reduce the influence of sawtooth trailing edge structure to turbine aerodynamic performance as far as possible simultaneously, the design of this embodiment is the sawtooth structure with the lower half blade height of director blade trailing edge.
As shown in fig. 5 and 6, the sawtooth tail edge structure may be disposed on all blades of the blade row or may be disposed on a part of the blades of the blade row. Because the asymmetric wake of the inlet guide vane can generate very beneficial unsteady coupling excitation effect on a downstream rotor flow field, and the fluid excitation force is reduced, when the sawtooth structure is arranged on the tail edge of part of the blades of the blade row, the blades of the sector of 180 degrees are designed into the sawtooth tail edge to form the two-sector asymmetric tail edge pneumatic layout.
As shown in fig. 7, the sawtooth tail edge structure may be composed of a plurality of continuous sawteeth, and may be composed of piecewise continuous sawteeth.
It can be seen that the key technology of the invention lies in:
1. the sawtooth trailing edge structure of the guide vane can destroy the spanwise consistency of a trailing vortex, weaken the trailing strength and reduce the pressure pulsation amplitude, particularly low-frequency pressure pulsation, of a trailing edge area, so that the unsteady airflow exciting force borne by the rotor vane is reduced.
2. The sawtooth tail edge structure of the guide vane is defined by two key geometric parameters of amplitude and wavelength, and has the characteristics of few control parameters and easiness in optimization design.
3. The influence of the circumferential local phase or partial blade height sawtooth tail edge structure on the aerodynamic performance of the turbine is small.
4. The molded line of the sawtooth tail edge structure of the guide vane can be a sine-like curve, a triangle, a trapezoid or a combination form of the shapes, the processing difficulty is relatively small, the popularization and the application are convenient, and the wide engineering application prospect is realized.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A method for inhibiting the excitation force of the unsteady airflow of the turbine rotor blade is characterized in that in the method, the excitation force of the unsteady airflow of the turbine rotor blade is reduced by designing the tail edge of a guide vane into a sawtooth structure.
2. The method of claim 1, wherein the profile of the saw-tooth structure is designed in a sinusoidal-like form, a triangular form, a trapezoidal form or a combination of any one or more thereof, wherein the profile of the saw-tooth structure is defined by two geometrical parameters, amplitude a and wavelength W, which are constant values for a certain application.
3. The method of claim 2, wherein the design amplitude a is in the range of 1% to 3% of the mid-arc length and the design wavelength W is in the range of 5% to 25% of the chord length.
4. A method according to claim 3, characterized in that the spanwise height of the sawtooth structure is designed to be arranged over the full leaf height of the trailing edge or only over the lower or upper half leaf height of the trailing edge.
5. A method according to claim 4, characterized in that the sawtooth structures are provided on all blades of the blade row or on part of the blades of the blade row.
6. A method according to claim 5, wherein, when the serrations are provided on part of the blades of the blade row, the blades of the 180 ° sector are designed to be serrated, resulting in a two-sector asymmetric trailing edge aerodynamic configuration.
7. The method as claimed in claim 6, characterized in that the saw-tooth structure is designed to consist of a plurality of successive saw-teeth or of piecewise successive saw-teeth.
8. A structure for suppressing excitation forces of an unsteady flow of turbine rotor blades designed by the method as set forth in any one of claims 1 to 7.
9. Use of a method according to any one of claims 1 to 7 in the field of turbine blade aerodynamic design technology.
10. Use of the structure according to claim 8 in the field of aerodynamic design of turbine blades.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011381166.4A CN112523809A (en) | 2020-11-30 | 2020-11-30 | Method for inhibiting unsteady airflow excitation force of turbine rotor blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011381166.4A CN112523809A (en) | 2020-11-30 | 2020-11-30 | Method for inhibiting unsteady airflow excitation force of turbine rotor blade |
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| CN112523809A true CN112523809A (en) | 2021-03-19 |
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| CN202011381166.4A Pending CN112523809A (en) | 2020-11-30 | 2020-11-30 | Method for inhibiting unsteady airflow excitation force of turbine rotor blade |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114165290A (en) * | 2021-12-07 | 2022-03-11 | 佛山市特亚菲科技有限公司 | Turbine and vibrator applying same |
| CN114295378A (en) * | 2021-11-17 | 2022-04-08 | 南京航空航天大学 | Hinge type distortion generator with serrated edge |
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| GB117008A (en) * | 1917-10-27 | 1918-07-04 | Blackburn Aeroplane & Motor Co | Improvements in Gripping or Clamping Devices or Jigs. |
| GB789883A (en) * | 1954-08-20 | 1958-01-29 | Power Jets Res & Dev Ltd | High speed aerofoil |
| CN102330571A (en) * | 2010-05-28 | 2012-01-25 | 通用电气公司 | Be used for system and method through the enhancing turbine wake flow mixing of fluid eddy generation |
| US20170159442A1 (en) * | 2015-12-02 | 2017-06-08 | United Technologies Corporation | Coated and uncoated surface-modified airfoils for a gas turbine engine component and methods for controlling the direction of incident energy reflection from an airfoil |
| US20180023398A1 (en) * | 2016-07-22 | 2018-01-25 | General Electric Company | Blade with parallel corrugated surfaces on inner and outer surfaces |
| CN110821851A (en) * | 2019-11-22 | 2020-02-21 | 南京航空航天大学 | Multistage axial compressor expands steady structure based on sawtooth trailing edge blade |
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2020
- 2020-11-30 CN CN202011381166.4A patent/CN112523809A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB117008A (en) * | 1917-10-27 | 1918-07-04 | Blackburn Aeroplane & Motor Co | Improvements in Gripping or Clamping Devices or Jigs. |
| GB789883A (en) * | 1954-08-20 | 1958-01-29 | Power Jets Res & Dev Ltd | High speed aerofoil |
| CN102330571A (en) * | 2010-05-28 | 2012-01-25 | 通用电气公司 | Be used for system and method through the enhancing turbine wake flow mixing of fluid eddy generation |
| US20170159442A1 (en) * | 2015-12-02 | 2017-06-08 | United Technologies Corporation | Coated and uncoated surface-modified airfoils for a gas turbine engine component and methods for controlling the direction of incident energy reflection from an airfoil |
| US20180023398A1 (en) * | 2016-07-22 | 2018-01-25 | General Electric Company | Blade with parallel corrugated surfaces on inner and outer surfaces |
| CN110821851A (en) * | 2019-11-22 | 2020-02-21 | 南京航空航天大学 | Multistage axial compressor expands steady structure based on sawtooth trailing edge blade |
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| 石乾宇: "大型离心式压缩机叶轮静动载荷的分析与研究", pages 53 - 54 * |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114295378A (en) * | 2021-11-17 | 2022-04-08 | 南京航空航天大学 | Hinge type distortion generator with serrated edge |
| CN114165290A (en) * | 2021-12-07 | 2022-03-11 | 佛山市特亚菲科技有限公司 | Turbine and vibrator applying same |
| CN114165290B (en) * | 2021-12-07 | 2023-07-25 | 佛山市特亚菲科技有限公司 | Turbine and vibrator applying same |
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