CN112324516A - Pneumatic damping device for moving blade of impeller machinery - Google Patents
Pneumatic damping device for moving blade of impeller machinery Download PDFInfo
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- CN112324516A CN112324516A CN202011323750.4A CN202011323750A CN112324516A CN 112324516 A CN112324516 A CN 112324516A CN 202011323750 A CN202011323750 A CN 202011323750A CN 112324516 A CN112324516 A CN 112324516A
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- blade
- airflow hole
- damping device
- shroud
- impeller
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- 238000013016 damping Methods 0.000 title claims abstract description 61
- 238000000034 method Methods 0.000 description 7
- 239000012530 fluid Substances 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 239000013585 weight reducing agent Substances 0.000 description 3
- 230000005284 excitation Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
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Classifications
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
本发明公开了一种用于叶轮机械动叶片的气动阻尼装置。该阻尼装置在动叶片围带处设有气流孔通道，气流孔通道内置有阻尼棒，阻尼棒将气流孔通道分成多通道。当叶片振动时，气流孔内气流发生振荡，从而消耗叶片振动能量，提高叶片安全性。本发明有益效果为结构简单、加工方便、成本低、可靠性高，可以在较宽的频域范围内吸收叶片的振动能量，从而有效延长叶轮机械动叶片的寿命。
The invention discloses an aerodynamic damping device for a mechanical moving blade of an impeller. The damping device is provided with an airflow hole channel at the shroud of the moving blade, the airflow hole channel is built with a damping rod, and the damping rod divides the airflow hole channel into multiple channels. When the blade vibrates, the airflow in the airflow hole oscillates, thereby consuming the vibration energy of the blade and improving the safety of the blade. The invention has the advantages of simple structure, convenient processing, low cost and high reliability, and can absorb the vibration energy of the blade in a wide frequency range, thereby effectively prolonging the life of the impeller mechanical moving blade.
Description
Technical Field
The invention belongs to the technical field of impeller machinery, and particularly relates to a pneumatic damping device for a moving blade of the impeller machinery.
Background
The rotor blades are important parts of the impeller machinery, and are generally subjected to high centrifugal load, aerodynamic load and alternating load during operation, and are easy to generate faults. With the continuous development of the technology, the running load of the impeller machinery is increased, and higher requirements are put forward on the reliability of the moving blades.
Blade vibration failure is an important component of a moving blade failure. Statistically, almost all moving blades have experienced varying degrees of blade vibration failure. Increasing blade damping and reducing blade aerodynamic excitation are considered two primary methods of reducing blade vibration failure. In the method for increasing the blade damping, the traditional design idea is to design a structural damper on the blade or the impeller. The damping of the blade unit is improved by adding the structural damper, so that the amplitude of the blade is reduced, and the vibration resistance of the blade is improved.
Currently, the design of structural damping encounters challenges from two sides: first, structural dampers are generally designed for predominantly low order modes; whereas the fluid excitation in the cascade flow field tends to excite higher order modes. Second, for blisks used in modern advanced turbomachinery, the provision of structural dampers would add significant complexity to the manufacturing process. Therefore, a new method is needed to be found to improve the high cycle fatigue damage resistance of the moving blade of the impeller machinery and prolong the service life of the moving blade. The high-frequency vibration of the blade can be effectively restrained by the pneumatic damping, meanwhile, the weight of the blade is not increased, the weight reduction requirement of modern blade design is met, and the service life of the moving blade can be effectively prolonged by adopting a method of combining the structural damping and the pneumatic damping.
Disclosure of Invention
In order to effectively compensate the problems of the structural damping device, the invention provides an aerodynamic damping device for a moving blade of an impeller machine.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme:
a pneumatic damping device for a moving blade of an impeller machine is arranged on the moving blade and comprises a blade shroud band, a blade body and a blade root, wherein the blade body comprises a blade pressure surface, a blade suction surface, and a blade air outlet edge and a blade air inlet edge which are arranged between the blade pressure surface and the blade suction surface; at least one row of airflow hole channels for vibration reduction are distributed on the blade shroud band close to the front edge of the air inlet side of the blade, and damping rods are arranged in the airflow hole channels.
The invention is further improved in that the air flow hole channel is positioned at the front edge of the moving blade air inlet side shroud, and the central connecting line of the holes is parallel to the front edge line of the shroud.
A further improvement of the invention is that the airflow aperture passage is oval in shape.
The invention has the further improvement that the minor radius r of the ellipse of the airflow hole is less than or equal to L/4; the long radius R of the ellipse is less than or equal to L/2, and L is the thickness of the blade shroud.
The invention is further improved in that the airflow hole channel is divided into two sections which are respectively perpendicular to the bottom surface of the blade shroud and parallel to the bottom surface of the blade shroud, and a rotating angle theta is 90 degrees between the two sections.
The invention has the further improvement that the airflow hole channel is firstly vertical to the bottom surface of the blade shroud, and the length of the vertical section of the airflow hole channel is not more than L/4; the length of the parallel section of the airflow hole channel is b less than or equal to 4L.
The invention is further improved in that the damping rod material is high filling rubber.
The invention is further improved in that the damping rod is a regular hexagon cylinder with a uniform cross section, the side length c of the regular hexagon cylinder with the cross section is r, and the length d of the damping rod is b.
The invention is further improved in that the damping rods are embedded in the parallel sections of the airflow hole channels, keep close contact with the airflow hole channels, cannot rotate freely in the airflow hole channels, and divide the airflow hole channels into multiple channels.
The invention has at least the following beneficial technical effects:
the moving blade provided by the invention comprises at least one row of airflow hole channels for damping vibration. When the blade vibrates, the vibration energy of the blade is transmitted to the airflow hole, and the blade vibrates to cause the relative movement of the wall surface of the airflow hole, so that the gas in the airflow hole flows. Due to the viscous action of the fluid, the blades dissipate vibration energy during vibration against the viscous forces of the gas. The damping rods divide the airflow holes into a plurality of airflow channels, after airflow enters the airflow channels, the flow speed is increased violently due to the sudden reduction of the area of the airflow channels, the direction is changed, fluid particles collide with each other, friction and momentum exchange are generated, and therefore vibration energy is consumed. Based on the two modes, the pneumatic damping device can effectively reduce the vibration energy of the blade and improve the safety of the blade.
Compared with the existing damping treatment method for the blade (such as dry friction damping at a blade shoulder and a lacing wire, a flange plate friction damper, a blade shroud damper and the like), the blade does not directly contact with the blade body of the blade, and the blade body of the blade does not need to be additionally processed.
Gas is introduced into the airflow hole channel, the high-frequency vibration of the blades can be effectively inhibited through pneumatic damping generated in the gas flowing process, meanwhile, the weight of the blades is not increased through the airflow hole channel, and the requirement of weight reduction of modern impeller machinery is met.
The design of the damping rod increases the local energy loss of gas caused by the sudden change of the airflow channel, greatly improves the pneumatic damping of the airflow hole channel, and meanwhile, the impact resistance of the airflow hole channel is effectively improved by the built-in damping rod.
Only a plurality of airflow hole channels are processed on the blade shroud ring, and the damping rods are arranged in the airflow hole channels, so that the blade shroud ring has the characteristics of simple structure, convenience in processing, low cost and high reliability.
Drawings
FIG. 1 is a view showing the configuration of the gas flow holes of the present invention.
Fig. 2 is a side view of the present invention.
FIG. 3 is a right perspective cross-sectional view of the internally mounted damping rod of the present invention.
Fig. 4 is a right perspective cross-sectional view of the air flow aperture channel of the present invention.
FIG. 5 is a top view cross-section of the internally mounted dampening bar of the present invention.
FIG. 6 is a schematic view of the structure of the damping rod of the present invention.
Description of reference numerals:
1. the air flow hole comprises an air flow hole channel, 2 damping rods, 3 blade shrouds, 4 blade pressure surfaces, 5 blade air outlet edges, 6 blade air inlet edges, 7 blade suction surfaces, 8 blade roots, 9 vertical sections of the air flow hole channel, 10 corners of the air flow hole channel and 11 parallel sections of the air flow hole channel.
Detailed Description
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
It should be noted that: any technical features and any technical solutions in the present embodiment are one or more of various optional technical features or optional technical solutions, and for the sake of brevity, this document cannot exhaustively enumerate all the alternative technical features and alternative technical solutions of the present invention, and is also not convenient for each embodiment of the technical features to emphasize it as one of various optional embodiments, so those skilled in the art should know that: any technical features and any technical solutions in the present embodiment do not limit the scope of the present invention, and the scope of the present invention should include any alternative technical solutions that can be conceived by those skilled in the art without inventive efforts.
Referring to fig. 1, 2 and 3, the invention relates to a pneumatic damping device for a moving blade of an impeller machine. The pneumatic damping device is positioned on a moving blade and consists of a blade shroud 3, a blade body and a blade root 8, wherein the blade body comprises a blade pressure surface 4, a blade air outlet edge 5, a blade air inlet edge 6 and a blade suction surface 7. The blade shroud 3 is provided with an airflow hole channel 1, and a damping rod 2 is arranged in the airflow hole channel 1.
Referring to fig. 1 and 2, the damping device of the present invention is provided with an air flow hole passage 1 at a blade shroud 3. The airflow hole channels 1 are distributed on the front edge of the side of the blade inlet edge 6 of the moving blade shroud 3, and the central connecting line of each airflow hole channel 1 is parallel to the front edge line of the blade shroud 2. In order to reduce stress concentration, the airflow hole channels 1 are oval, and are uniformly distributed among the airflow holes. The thickness of the blade shroud ring 2 is a design value L, and the elliptical short radius r of the airflow hole 1 is less than or equal to L/4; the long radius R of the ellipse is less than or equal to L/2.
Referring to fig. 3 and 4, the air flow hole channel 1 is divided into two sections, which are respectively perpendicular to the bottom surface of the blade shroud 3 and parallel to the bottom surface of the blade shroud 3, and a flow hole channel turning angle 10 is formed between the two sections, and the turning angle θ is 90 °. The vertical section 9 of the airflow hole is firstly vertical to the bottom surface of the blade shroud band 3, and the length of the vertical section 9 of the airflow hole channel is more than or equal to L/4; after passing through the corner 10 of the airflow hole channel, the airflow hole channel is parallel to the bottom surface of the blade shroud band 3, and the length of the parallel section 11 of the airflow hole channel is b less than or equal to 4L.
Referring to fig. 5, after the damper rod 2 is installed, the damper rod is tightly embedded in the parallel section 11 of the airflow hole channel and cannot freely rotate in the parallel section 11 of the airflow hole channel, so that the parallel section 11 of the airflow hole channel is divided into multiple channels.
Referring to fig. 6, the damping rod 2 is a regular hexagonal cylinder with a uniform cross section, the side length c of the regular hexagonal cylinder is r, and the length d of the damping rod 2 is b.
According to the pneumatic damping device for the moving blade of the impeller machine, when the blade vibrates, vibration energy is absorbed by airflow in the airflow hole channel, so that the vibration energy is consumed, and the safety of the blade is improved. Compared with the traditional damping device, the pneumatic damping device for the moving blade of the impeller machine provided by the invention is not in direct contact with the blade body of the blade, does not need to additionally process the blade body of the blade, does not need to increase an additional damping device part, does not increase the weight of the blade while inhibiting the high-frequency vibration of the blade, meets the weight reduction requirement of the modern impeller machine, and has the advantages of simple structure, convenience in processing, low cost and high reliability.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011323750.4A CN112324516B (en) | 2020-11-23 | 2020-11-23 | Pneumatic damping device for impeller mechanical moving blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011323750.4A CN112324516B (en) | 2020-11-23 | 2020-11-23 | Pneumatic damping device for impeller mechanical moving blade |
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| Publication Number | Publication Date |
|---|---|
| CN112324516A true CN112324516A (en) | 2021-02-05 |
| CN112324516B CN112324516B (en) | 2024-08-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011323750.4A Active CN112324516B (en) | 2020-11-23 | 2020-11-23 | Pneumatic damping device for impeller mechanical moving blade |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB711572A (en) * | 1951-02-27 | 1954-07-07 | Rateau Soc | Improvements in vibration damping means for bladings in fluid actuated or actuating rotary machines |
| US3958905A (en) * | 1975-01-27 | 1976-05-25 | Deere & Company | Centrifugal compressor with indexed inducer section and pads for damping vibrations therein |
| JPH0763004A (en) * | 1993-08-23 | 1995-03-07 | Mitsubishi Heavy Ind Ltd | Turbine moving blade |
| EP2455586A1 (en) * | 2010-11-17 | 2012-05-23 | MTU Aero Engines GmbH | Rotor for a turbo engine comprising sealing and damping elements |
| CN105041726A (en) * | 2015-07-09 | 2015-11-11 | 上海交通大学 | Damping ring device used for controlling vibration of compressor blades |
| CN106246233A (en) * | 2016-08-01 | 2016-12-21 | 杭州汽轮机股份有限公司 | A kind of industrial steam turbine blade damping loose lacing wire and mounting structure thereof |
| CN110671155A (en) * | 2019-10-18 | 2020-01-10 | 西安交通大学 | Self-adaptive variable working condition optimal positive pressure damping blade structure and design method |
| CN213574234U (en) * | 2020-11-23 | 2021-06-29 | 华能国际电力股份有限公司 | A kind of aerodynamic damping device for impeller mechanical moving blade |
-
2020
- 2020-11-23 CN CN202011323750.4A patent/CN112324516B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB711572A (en) * | 1951-02-27 | 1954-07-07 | Rateau Soc | Improvements in vibration damping means for bladings in fluid actuated or actuating rotary machines |
| US3958905A (en) * | 1975-01-27 | 1976-05-25 | Deere & Company | Centrifugal compressor with indexed inducer section and pads for damping vibrations therein |
| JPH0763004A (en) * | 1993-08-23 | 1995-03-07 | Mitsubishi Heavy Ind Ltd | Turbine moving blade |
| EP2455586A1 (en) * | 2010-11-17 | 2012-05-23 | MTU Aero Engines GmbH | Rotor for a turbo engine comprising sealing and damping elements |
| CN105041726A (en) * | 2015-07-09 | 2015-11-11 | 上海交通大学 | Damping ring device used for controlling vibration of compressor blades |
| CN106246233A (en) * | 2016-08-01 | 2016-12-21 | 杭州汽轮机股份有限公司 | A kind of industrial steam turbine blade damping loose lacing wire and mounting structure thereof |
| CN110671155A (en) * | 2019-10-18 | 2020-01-10 | 西安交通大学 | Self-adaptive variable working condition optimal positive pressure damping blade structure and design method |
| CN213574234U (en) * | 2020-11-23 | 2021-06-29 | 华能国际电力股份有限公司 | A kind of aerodynamic damping device for impeller mechanical moving blade |
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| CN112324516B (en) | 2024-08-27 |
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