CN113279978B - Compressor and method for weakening acoustic excitation of compressor rotor blade - Google Patents
Compressor and method for weakening acoustic excitation of compressor rotor blade Download PDFInfo
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- CN113279978B CN113279978B CN202110316961.3A CN202110316961A CN113279978B CN 113279978 B CN113279978 B CN 113279978B CN 202110316961 A CN202110316961 A CN 202110316961A CN 113279978 B CN113279978 B CN 113279978B
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- 230000005284 excitation Effects 0.000 title claims abstract description 78
- 238000000034 method Methods 0.000 title claims abstract description 23
- 230000003313 weakening effect Effects 0.000 title abstract description 10
- 238000011144 upstream manufacturing Methods 0.000 claims description 9
- 230000006378 damage Effects 0.000 abstract description 17
- 230000001808 coupling effect Effects 0.000 abstract description 7
- 238000002474 experimental method Methods 0.000 description 34
- 239000000243 solution Substances 0.000 description 8
- 230000000694 effects Effects 0.000 description 6
- 238000012360 testing method Methods 0.000 description 6
- 230000000052 comparative effect Effects 0.000 description 3
- 229910000881 Cu alloy Inorganic materials 0.000 description 2
- 206010063385 Intellectualisation Diseases 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- SBYXRAKIOMOBFF-UHFFFAOYSA-N copper tungsten Chemical compound [Cu].[W] SBYXRAKIOMOBFF-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009661 fatigue test Methods 0.000 description 2
- 239000011810 insulating material Substances 0.000 description 2
- 239000000741 silica gel Substances 0.000 description 2
- 229910002027 silica gel Inorganic materials 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
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- 230000009528 severe injury Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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Abstract
The application discloses a compressor and method for weakening sound excitation of rotor blades of the compressor, wherein the compressor is an axial-flow compressor and comprises at least one first plasma jet generator fixedly connected to the outer wall of a casing, the first plasma jet generator emits first plasma jet to the inner cavity of the casing through a first jet hole formed in the casing wall, and the extending direction of the first jet hole faces the pressure surface or the back pressure surface of the rotor blades in the corresponding rotor blade grid and inclines relative to the tangential surface of the inner wall of the casing at the position where the opening of the first jet hole is located. The method of attenuating acoustic excitation of a compressor rotor blade is to eject a first plasma jet against a pressure or back pressure surface of the rotor blade during operation of the compressor. According to the technical scheme, tip leakage vortex formed by tip clearance undercurrent can be destroyed or weakened, the probability of occurrence of acoustic excitation of the rotor blade and the strength of the acoustic excitation are reduced, the coupling effect of airflow-acoustic wave-blade is weakened, and therefore the harm of the acoustic excitation to the rotor blade is reduced.
Description
Technical Field
The invention relates to the technical field of compressors, in particular to a compressor and a method for weakening acoustic excitation of a rotor blade of the compressor.
Background
The existing axial-flow compressor comprises a casing, a hub rotating in an inner cavity of the casing around a rotation axis and a plurality of stages of pressurizing structures distributed along the rotation axis, wherein each stage of pressurizing structure comprises a rotor blade grid and a stator blade grid adjacent to and downstream of the rotor blade grid; the rotor blade grids are arranged on the hub and rotate along with the hub around the rotation axis of the hub, and each rotor blade grid comprises a plurality of rotor blades distributed along the circumference of the hub; the stator blade grid is arranged on the inner wall of the casing and is fixed relative to the casing. The sound excitation phenomenon is that sound waves generated by air moving at high speed act on the rotor blade when the rotor blade rotates at high speed, and meanwhile airflow-sound wave-blade coupling is formed, namely noise is generated by unstable flow of airflow in a blade grid, and the pressure change of the sound waves is derived from tip leakage vortex formed by tip clearance undercurrent and wake vortex fallen off from the tail edge of the stator blade. Under the excitation of the vibration, the rotor blade is subjected to strong vibration, and fatigue damage is generated, so that the rotor blade is broken, and the safety and reliability of the engine work are affected.
Disclosure of Invention
The present application aims to overcome the above-mentioned drawbacks or problems in the background art, and provide a compressor and a method for weakening acoustic excitation of a rotor blade of the compressor, which can destroy or weaken tip leakage vortex formed by tip clearance undercurrent, thereby reducing probability of occurrence of acoustic excitation and strength of acoustic excitation of the rotor blade, weakening coupling effect of airflow-acoustic wave-blade, and further reducing harm of acoustic excitation to the rotor blade.
In order to achieve the above purpose, the following technical scheme is adopted:
the first technical scheme relates to a compressor, which is an axial-flow compressor and comprises a casing, a hub rotating in an inner cavity of the casing around a rotation axis and a plurality of stages of supercharging structures distributed along the rotation axis, wherein each stage of supercharging structure comprises a rotor blade grid and a stator blade grid adjacent to and downstream of the rotor blade grid; the rotor blade grids are arranged on the hub and rotate along with the hub around the rotating axis, and each rotor blade grid comprises a plurality of rotor blades distributed along the circumference of the hub; the stator blade grid is arranged on the inner wall of the casing; it also includes: at least one group of first plasma jet generator groups, each group of first plasma jet generator groups corresponding to a rotor blade grid; the first plasma jet generator set comprises at least one first plasma jet generator fixedly connected to the outer wall of the casing; each first plasma jet generator emits first plasma jet to the inner cavity of the casing through a first jet hole which is arranged on the casing wall and corresponds to the first plasma jet generator; the extending direction of the first jet hole faces the pressure surface or the back pressure surface of the rotor blade in the corresponding rotor blade grid and is inclined relative to the tangential plane of the inner wall of the casing at the position of the opening of the first jet hole.
A second technical aspect is based on the first technical aspect, wherein an extension direction of the first jet hole is directed toward a pressure surface of the rotor blade and toward a middle of a chord line of the rotor blade.
The third technical scheme is based on the first technical scheme, wherein an included angle between the extending direction of the first jet hole and a tangent plane of the inner wall of the casing at the position where the opening of the first jet hole is located is in a range of 25-35 degrees.
The fourth technical scheme is based on the third technical scheme, wherein an included angle between the extending direction of the first jet hole and a tangent plane of the inner wall of the casing at the position where the opening of the first jet hole is located is 30 degrees.
A fifth technical means is based on any one of the first to fourth technical means, wherein the first plasma jet generator includes a first body, a first power source, and two first electrodes; the first body is fixedly connected to the outer wall of the casing and forms a first plasma generation cavity communicated with the first jet hole; the first power supply is used for generating pulse voltage; the two first electrodes are respectively and electrically connected with the first power supply and extend into the first plasma generation cavity.
A sixth technical aspect is based on the first technical aspect, further comprising at least one set of second plasma jet generator sets, each set of second plasma jet generator sets corresponding to a rotor blade cascade; the second plasma jet generator set comprises at least one second plasma jet generator fixedly connected to the outer wall of the casing; each second plasma jet generator emits second plasma jet to the inner cavity of the casing through a second jet hole which is arranged on the casing wall and corresponds to the second plasma jet generator; the openings of the second jet holes on the inner wall of the casing are positioned between the corresponding rotor blade row and the stator blade row adjacent to and upstream of the rotor blade row, and the extending direction of the second jet holes is towards the rotating axis.
A seventh technical means is based on the sixth technical means, wherein an extending direction of the second jet hole is perpendicular to the rotation axis.
An eighth technical means is based on the sixth or the seventh technical means, wherein the second plasma jet generator includes a second body, a second power source, and two second electrodes; the second body is fixedly connected to the outer wall of the casing and forms a second plasma generation cavity communicated with the second jet hole; the second power supply is used for generating pulse voltage; the two second electrodes are respectively and electrically connected with the second power supply and extend into the second plasma generation cavity.
A ninth technical solution relates to a method for weakening acoustic excitation of a rotor blade of a compressor, during operation of the compressor, by emitting a first plasma jet to a pressure surface or a back pressure surface of the rotor blade through a first jet hole formed in a casing wall, an extension direction of the first jet hole being inclined with respect to a tangential plane of an inner wall of the casing at a position where an opening of the first jet hole is located.
A tenth technical means is based on the ninth technical means, wherein during operation of the compressor, the second plasma jet is further emitted to a space between the rotor blade cascade and a stator blade cascade adjacent to and upstream of the rotor blade cascade through a second jet hole provided in the casing wall, and an extending direction of the second jet hole is directed to a rotation axis of the hub.
Compared with the prior art, the scheme has the following beneficial effects:
in the first technical scheme, the extending direction of the first jet hole faces the pressure surface or the back pressure surface of the rotor blade in the corresponding rotor blade grid, so that the first plasma jet can directly interfere tip clearance undercurrents formed between the tips of the rotor blade and the inner wall of the casing in the operation process of the compressor, tip leakage vortex formed by the tip clearance undercurrents is destroyed or weakened, the excitation effect of noise generated by the tip leakage vortex on the rotor blade is reduced, the probability of acoustic excitation of the rotor blade is reduced, the intensity of acoustic excitation is reduced, the coupling effect of airflow-acoustic wave-blade is weakened, and the harm of the acoustic excitation on the rotor blade of the compressor is reduced. In addition, related experiments prove that when the extending direction of the first jet hole is inclined relative to the tangential plane of the inner wall of the casing at the position of the opening of the first jet hole, the first plasma jet can be obliquely emitted from the casing wall, so that the weakening effect on acoustic excitation can be more effectively improved. And when the extending direction of the first jet hole is vertical to the tangential plane of the inner wall of the casing at the position of the opening of the first jet hole, the acoustic excitation cannot be effectively weakened.
A second aspect is based on the first aspect, further defining a middle portion of a chord line of the rotor blade in which an extension direction of the first jet hole is directed toward a pressure surface of the rotor blade. Experiments prove that the first plasma jet formed by the structure can better reduce the strength of acoustic excitation and more effectively reduce the harm of the acoustic excitation to the rotor blade of the compressor.
The third and fourth technical solutions further ensure that the first plasma jet effectively interferes with the gap undercurrent formed at the tip of the rotor blade by defining the angular relationship between the extension direction of the first jet hole and the tangential plane of the inner wall of the casing.
The fifth technical solution provides a specific structure of the first plasma jet generator, and since the first plasma jet generator is powered by the power supply, no air flow is required to be introduced from other parts of the air compressor, and the work efficiency of the air compressor can be prevented from being reduced. Meanwhile, because electric energy is used, the first plasma jet can be automatically or autonomously started and stopped, and a foundation is provided for realizing intellectualization.
A sixth technical solution is to add a second plasma jet generator, through which a second plasma jet can be injected into a region between the rotor blade cascade and the stator blade cascade adjacent to and upstream of the rotor blade cascade. The second plasma jet can interfere vortex motion in the area, break up a large-scale vortex structure, change the falling frequency of wake vortex at the tail edge of the stator blade, and enable the falling frequency of the wake vortex to be far away from the inherent vibration frequency of the rotor blade, so that the probability of acoustic excitation of the rotor blade is reduced, the intensity of the acoustic excitation is reduced, the coupling effect of airflow-acoustic wave-blade is weakened, and the harm of the acoustic excitation to the rotor blade of the compressor is reduced.
In the seventh technical scheme, the extending direction of the second jet hole is perpendicular to the rotation axis, so that vortex motion in the area can be better disturbed, and damage of sound excitation to the compressor rotor blade can be better reduced.
The eighth technical solution provides a specific structure of the second plasma jet generator, and since the second plasma jet generator is powered by a power supply, it is unnecessary to introduce air flow from the other part of the compressor, and it is possible to avoid reducing the work efficiency of the compressor. Meanwhile, because electric energy is used, the first plasma jet can be automatically or autonomously started and stopped, and a foundation is provided for realizing intellectualization.
According to a ninth technical scheme, the method for disturbing the clearance undercurrent formed at the tip of the rotor blade by emitting the first plasma jet flow can destroy or weaken tip leakage vortex formed by the tip clearance undercurrent, enable the frequency of noise generated by the tip leakage vortex to deviate from the inherent vibration frequency of the rotor blade, reduce the excitation effect of the noise generated by the tip leakage vortex on the rotor blade, reduce the probability of acoustic excitation of the rotor blade, or reduce the strength of the acoustic excitation, so that the coupling effect of acoustic wave-air flow-blade can be weakened, and the harm of the acoustic excitation on the rotor blade of the air compressor can be reduced.
The tenth technical solution further provides a method of disturbing vortex motion in a region between a rotor blade cascade and a stator blade cascade adjacent to and upstream of the rotor blade cascade by emitting a second plasma jet, scattering a large-scale vortex structure, changing wake vortex shedding frequency at a trailing edge of the stator blade, and enabling the wake vortex shedding frequency to be far away from natural vibration frequency of the rotor blade, thereby reducing probability of occurrence of acoustic excitation of the rotor blade, reducing intensity of the acoustic excitation, and reducing harm of the acoustic excitation to the rotor blade of the compressor.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments, the following brief description of the drawings is provided, in which:
fig. 1 is a longitudinal sectional view of a related portion of a compressor in accordance with an embodiment;
FIG. 2 is a schematic diagram of a rotor cascade and stator cascade layout after circumferential expansion of a hub of a compressor in accordance with an embodiment;
FIG. 3 is an enlarged view of part A of FIG. 1;
FIG. 4 is a schematic view showing the extending direction of the first jet hole according to the first embodiment;
FIG. 5 is an enlarged view of part B of FIG. 1;
FIG. 6 is a schematic diagram of the position of a second plasma jet generator in accordance with the first embodiment;
FIG. 7 is a schematic illustration of the position of the first jet aperture in comparative experiment one;
FIG. 8 is a schematic view of the position of the first jet hole in comparative experiment two;
FIG. 9 is a schematic illustration of the first jet hole location in comparative experiment three;
FIG. 10 is a photograph of a rotor blade structural failure caused by acoustic excitation;
the main reference numerals illustrate:
a compressor 1; a casing 2; a hub 3; a rotation axis 4; a supercharging structure 5; rotor blade row 6; a stator cascade 7; a rotor blade 8; stator blades 9; a pressure surface 10; a back pressure surface 11; a first plasma jet generator 12; a first body 13; a first plasma generation chamber 14; a first power supply 15; a first electrode 16; first jet holes 17, 17a, 17b, 17c, 17d, 17e, 17f, 17g; a second plasma jet generator 18; a second body 19; a second plasma generation chamber 20; a second power supply 21; a second electrode 22; a second jet hole 23; a velocity vector V of the incoming flow in front of the rotor blade relative to the casing; velocity vector V' of incoming flow in front of stator blade relative to casing; velocity vector V of incoming flow ahead of rotor blade relative to rotor blade r The method comprises the steps of carrying out a first treatment on the surface of the The rotor blade rotates at an angular velocity omega relative to the casing; the linear speed U of the movement of the rotor blade relative to the casing; tip clearance undercurrent V g The method comprises the steps of carrying out a first treatment on the surface of the First plasma jet V j The method comprises the steps of carrying out a first treatment on the surface of the Second plasma jet V j 'A'; air pressure P of rotor blade pressure surface 1 The method comprises the steps of carrying out a first treatment on the surface of the Air pressure P of rotor blade back pressure surface 2 The method comprises the steps of carrying out a first treatment on the surface of the Rotor blade mounting angle α; the first angle beta.
Detailed Description
In the claims and in the description, unless otherwise defined, the terms "first," "second," or "third," etc., are used for distinguishing between different objects and not for describing a particular sequential order.
In the claims and the specification, unless otherwise defined, the terms "center", "lateral", "longitudinal", "horizontal", "vertical", "top", "bottom", "inner", "outer", "upper", "lower", "front", "rear", "left", "right", "clockwise", "counterclockwise", etc., refer to an orientation or positional relationship based on that shown in the drawings, and are merely for convenience of description, and do not imply that the devices or elements referred to must have a particular orientation or be constructed and operated in a particular orientation.
In the claims and specification, unless otherwise defined, the terms "fixedly coupled" and "fixedly connected" are to be construed broadly as any manner of connection without a displacement relationship or relative rotational relationship therebetween, and that is to say include non-detachably fixedly connected, integrally connected, and fixedly connected by other means or elements.
In the claims and specification, unless otherwise defined, the terms "comprising," having, "and variations thereof mean" including but not limited to.
In the claims and specification, unless otherwise defined, the term "forward" is the range between the rotor blade leading edge to 20% chord aft; "mid-forward" refers to a range from 20% chord length aft of the rotor blade leading edge to 40% chord length aft of the rotor blade leading edge; "mid-section" refers to the range from 40% chord length aft of the rotor blade leading edge to 60% chord length aft of the rotor blade leading edge.
The technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings.
Example 1
Referring to fig. 1, fig. 1 shows the structure of the relevant portion of a compressor 1 in the first embodiment. As shown in fig. 1, the compressor 1 is an axial flow compressor. The compressor 1 comprises a casing 2, a hub 3, a plurality of stages of pressurizing structures 5, a set of first plasma jet generator sets and a set of second plasma jet generator sets.
The casing 2 is formed by enclosing casing walls, and a casing inner cavity is formed in the casing 2. The cross section of the inner cavity of the casing is circular. As shown in fig. 3, 4 and 5, the casing wall is provided with a first jet hole 17 and a second jet hole 23. The first jet hole 17 and the second jet hole 23 are through holes penetrating from the outer casing wall to the inner casing wall, and the positions and the extending directions of the through holes are described in detail later.
The hub 3 rotates in the housing interior about a rotational axis 4, the rotational direction of which is shown in fig. 1. The compressor 1 is further provided with a plurality of stages of supercharging structures 5 along the direction of the rotation axis 4 of the hub 3. Each stage of the supercharging structure 5 comprises a rotor blade row 6 and stator blade rows 7 adjacent to and downstream of the rotor blade row 6. Wherein, rotor blade bars 6 are mounted to hub 3 and rotate along with hub 3 about rotational axis 4, each rotor blade bar 6 includes a plurality of rotor blades 8 circumferentially disposed along hub 3, and the spacing between adjacent rotor blades 8 forms a rotor blade bar channel for airflow therethrough. The stator blade cascades 7 are arranged on the inner wall of the casing, each stator blade cascades 7 comprises a plurality of stator blades 9 which are circumferentially arranged along the inner wall of the casing, and stator blade cascades channels for air flow to pass through are formed at intervals between adjacent stator blades 9.
As shown in fig. 2, the linear velocity of the movement of the rotor blade 8 relative to the casing 2 is U. The velocity vector of the incoming flow in front of the rotor blades 8 with respect to the casing 2 is V, which is parallel to the axis of rotation 4. From this, it is possible to obtain a velocity vector V of the incoming flow in front of the rotor blade 8 relative to the rotor blade 8 r Which is inclined to the axis of rotation 4. Chord and inflow of a rotor blade 8 relative to the velocity vector V of the rotor blade 8 r The included angle between them is the mounting angle α of the rotor blade, which in this embodiment is 15 °.
In this embodiment, the number of the first plasma jet generators is one. In other embodiments, the number of the first plasma jet generator sets may be more than two. Regardless of the number of first groups of plasma jet generators, each group of first plasma jet generators corresponds to a rotor blade cascade 6.
As shown in fig. 1, 3 and 4, in this embodiment, the first plasma jet generator set includes a first plasma jet generator 12 fixedly connected to the outer wall of the casing. In other embodiments, the first plasma jet generator set may also include a plurality of first plasma jet generators 12, where the plurality of first plasma jet generators 12 may be circumferentially distributed on the outer casing wall, may be distributed on the outer casing wall in a direction parallel to the rotation axis 4, and may form a plurality of units, each unit being circumferentially distributed on the outer casing wall, and each first plasma jet generator 12 being distributed on the outer casing wall in a direction parallel to the rotation axis 4 in each unit. Each first plasma jet generator 12 comprises a first body 13, a first power supply 15 and two first electrodes 16. The first body 13 is made of a high-temperature-resistant insulating material, is fixedly connected to the outer wall of the casing, and is matched with the outer wall of the casing to form a first plasma generation cavity 14 communicated with the first jet hole 17. The first power supply 14 is a pulsed high voltage power supply that generates a pulsed voltage. The two first electrodes 16 have different polarities and may be made of tungsten copper alloy. One end of each of the two first electrodes 16 is electrically connected to two poles of the first power supply 15, and the other end extends into the first plasma generation chamber 14 through the side wall of the first body 13. The first electrode 16 and the first body 13 are fixed by high temperature resistant silica gel to ensure the air tightness of the first plasma generation cavity 14. The two first electrodes 16 extend into the plasma-generating chamber 14 at a distance which is determined by the relevant parameters of the first power supply 15. The first power supply 15 generates a pulse excitation voltage at a certain duty cycle. At positive voltage, air is highly ionized between the two first electrodes 16 to form a first plasma and expand, and the first plasma emits a first plasma jet V to the inner cavity of the casing through a first jet hole 17 communicated with the first plasma generation cavity 14 j The method comprises the steps of carrying out a first treatment on the surface of the At the time when the voltage value is zero, the gas flow flows from the first jet hole 17 into the first plasma generation chamber 14 due to the negative pressure formed in the first plasma generation chamber 14.
FIGS. 2 and 4 illustrate the present embodimentA first jet aperture 17 communicating with the first plasma generation chamber 14. Wherein fig. 2 shows the opening of the first jet hole 17 on the inner wall of the casing and the extending direction of the first jet hole 17 (i.e., the first plasma jet V j Ejection direction). In the present exemplary embodiment, the first jet holes 17 extend in a direction toward the pressure surface 10 of the rotor blade 8 in the corresponding rotor blade row 6 and in a direction toward the middle of the chord line of the rotor blade 8. In other embodiments, the direction of extension of the first jet holes 17 is directed towards the counter pressure surface 11 of the rotor blade 8 in the corresponding rotor blade row 6. As shown in fig. 4, the extending direction of the first jet hole 17 is also inclined with respect to the tangential plane of the inner wall of the casing at the position where the opening of the first jet hole 17 is located. The extending direction of the first jet hole 17 and the tangential plane of the inner wall of the casing at the position where the opening of the first jet hole 17 is located form a first included angle β, the first included angle β should not be equal to 90 °, the value range may be 25 ° to 35 °, and in this embodiment, the first included angle β is 30 °.
As shown in fig. 2 and 4, the air pressure at the pressure surface 10 of the rotor blade 8 is P 1 The air pressure at the back pressure surface 11 of the rotor blade 8 is P 2 And P is 1 >P 2 Whereby a tip clearance undercurrent V is formed between the tips of the rotor blades 8 and the inner wall of the casing 2 by the pressure difference g . The first plasma jet generator 12 and the first jet aperture 17 in this embodiment cause the first plasma jet V to flow j Can directly sink the blade tip clearance subsurface flow V g Disturbance, destruction or attenuation of undercurrent V from tip clearance g The formed blade tip leakage vortex reduces the excitation effect of noise generated by the blade tip leakage vortex on the rotor blade 8, reduces the probability of acoustic excitation of the rotor blade 8, and reduces the strength of the acoustic excitation, thereby weakening the coupling effect of airflow-acoustic wave-blades and reducing the harm of the acoustic excitation to the rotor blade 8.
In this embodiment, the number of second groups of plasma jet generators is one. In other embodiments, the number of second groups of plasma jet generators may be more than two. Regardless of the number of second sets of plasma jet generators, each set of second sets of plasma jet generators corresponds to a rotor blade cascade 6.
As shown in fig. 1, 5 and 6, in this embodiment, the second plasma jet generator set includes a second plasma jet generator 18 fixedly connected to the outer wall of the casing. In other embodiments, the second set of plasma jet generators may also include a plurality of second plasma jet generators 18. The plurality of second plasma jet generators 18 may be circumferentially distributed on the casing outer wall. Each second plasma jet generator 18 comprises a second body 19, a second power supply 21 and two second electrodes 22. The second body 19 is made of a high temperature resistant insulating material, is fixedly connected to the outer wall of the casing, and is matched with the outer wall of the casing to form a second plasma generation cavity 20 communicated with the second jet hole 23. The second power supply 21 is a pulsed high voltage power supply that generates a pulsed voltage. The two second electrodes 22 have different polarities and can be made of tungsten-copper alloy. One end of each of the two second electrodes 22 is electrically connected to two poles of the second power source 21, and the other end of each of the two second electrodes extends into the second plasma generating chamber 20 through the side wall of the second body 19. The second electrode 22 and the second body 19 are fixed by high temperature resistant silica gel to ensure the air tightness of the second plasma generating chamber 20. The two second electrodes 22 extend into the ends of the second plasma-generating chamber 20 to form a gap, the distance of which is determined by the relevant parameters of the second power supply 21. The second power supply 21 generates a pulse excitation voltage at a certain duty cycle. At positive voltage, air is highly ionized between the two second electrodes 22 to form second plasma and expand, and the second plasma generator 18 emits second plasma jet V to the inner cavity of the casing through second jet hole 23 communicated with second plasma generating cavity 20 j 'A'; at the time when the voltage value is zero, the gas flow flows from the second jet hole 23 into the second plasma generation chamber 20 due to the negative pressure formed in the second plasma generation chamber 20.
Fig. 2, 5 and 6 show a second jet hole 23 communicating with the second plasma generation chamber 20 in the present embodiment. Wherein, as shown, the openings of the second jet holes 23 on the inner wall of the casing are located between the corresponding rotor blade row 6 and the stator blade row 7 adjacent to and upstream of the rotor blade row 6. As shown in fig. 5 and 6The direction of extension of the second jet aperture 23 (i.e. the second plasma jet V j The' injection direction) towards the rotational axis 4 of the hub 3 and perpendicular to this rotational axis 4.
As shown in fig. 6, the velocity vector of the incoming flow in front of the stator blade 9 relative to the casing 2 is V', the direction of the incoming flow through the stator blade cascade passage is changed to be parallel to the rotation axis 4, and the air flow forms wake vortex at the trailing edge of the stator blade 9 and falls off. The second plasma jet generator 18 and the second jet aperture 23 in this embodiment cause the second plasma jet V to flow j ' vortex motion in the area between the rotor blade 6 and the stator blade 7 adjacent to and upstream of the rotor blade 6 is disturbed, a large-scale vortex structure is broken up, the shedding frequency of wake vortexes at the tail edge of the stator blade 9 is changed, the shedding frequency of the wake vortexes is far away from the natural vibration frequency of the rotor blade 8, so that the probability of occurrence of acoustic excitation of the rotor blade 8 is reduced, the intensity of the acoustic excitation is reduced, the coupling effect of airflow-acoustic wave-blade can be weakened, and the harm of the acoustic excitation to the rotor blade 8 is reduced.
The method for weakening the acoustic excitation of the rotor blade 8 by the compressor 1 according to the first embodiment comprises, during the operation of the compressor 1, generating pulsed high voltage power by controlling the first power supply 15 and the second power supply 21 to operate the first plasma jet generator 12 and the second plasma jet generator 18, so as to emit the first plasma jet V to the pressure surface 10 or the back pressure surface 11 of the rotor blade 8 through the first jet hole 17 formed in the casing wall j To interfere tip clearance undercurrent, destroy or weaken tip leakage vortex formed by tip clearance undercurrent f; and emits a second plasma jet V toward the space between the rotor blade cascade 6 and the stator blade cascade 7 adjacent to and upstream of the rotor blade cascade 6 through a second jet hole 23 formed in the casing wall j ' scattering large-scale vortex structures by disturbing vortex motion in the interval area, and changing the shedding frequency of wake vortexes at the tail edge of the stator blade 9. Wherein the extension direction of the first jet hole 17 is inclined relative to the tangential plane of the inner wall of the casing at the position of the opening of the first jet hole 17, and the extension direction of the second jet hole 23 is towards the rotation axis 4 of the hub 3.
As a further modification of the first embodiment, the vibration of the rotor blade 8 may be sensed by a vibration sensor or a strain sensor, and the first power supply 15 and/or the second power supply 21 may be controlled to generate pulsed high voltage power to operate the first plasma jet generator 12 and the second plasma jet generator 18 when the amplitude of the vibration of the rotor blade 8 reaches a threshold set by man. In this way, the acoustic excitation of the rotor blade 8 can be intelligently reduced. In general, vibration sensors or strain sensors may be mounted at the root of the rotor blade 8 to which the hub 3 is connected, to avoid affecting the gas flow. The above-mentioned sensor may be electrically connected to a controller or connected to a wireless signal, and the controller may control the first power source 15 and the second power source 21 to generate a pulsed high voltage with a specific duty cycle by transmitting an excitation signal.
Example two
As shown in fig. 7, the only difference between the second embodiment and the first embodiment is that the extending direction of the first jet hole 17a in the second embodiment is directed toward the front of the chord line of the rotor blade 8.
Example III
As shown in fig. 8, the embodiment three differs from the embodiment one only in that the first jet hole 17b in the embodiment three extends in a direction toward the back pressure surface 11 of the rotor blade 8 and is directed toward the front of the chord line of the rotor blade 8.
Example IV
As shown in fig. 8, the fourth embodiment differs from the first embodiment only in that the first jet hole 17c in the fourth embodiment extends in a direction toward the back pressure surface 11 of the rotor blade 8 and is directed toward the middle-front portion of the chord line of the rotor blade 8.
Example five
As shown in fig. 8, the embodiment five differs from the embodiment one only in that the first jet hole 17d in the embodiment five extends in a direction toward the back pressure surface 11 of the rotor blade 8 and is directed toward the middle of the chord line of the rotor blade 8.
To verify the first plasma jet V j Influence on the acoustic excitation of the rotor blade 8, the applicant devised three experiments, each verifying that the first jet hole 17 is directed towards the rotor blade 8 when the first jet hole 17 is directed towards the pressure surface 10 of the rotor blade 8The first plasma jet V at the back pressure surface 11 and with the first jet hole 17 facing the tip of the rotor blade 8 j Influence on the acoustic excitation of the rotor blade 8.
The common points of the three experiments are as follows: the three experiments are all carried out in a wind tunnel, and the experimental device comprises a rectangular box body with two open ends, five rotor blades 8, a plurality of first plasma jet generators 12, a sound pressure sensor for collecting sound pressure and a strain sensor for collecting strain of the rotor blades. The extending direction of the rectangular box body is the same as that of the wind tunnel, the openings at two ends respectively form an air inlet end and an air outlet end, the top wall of the rectangular box body simulates the casing 2, and the bottom wall simulates the hub 3. Five rotor blades 8 are arranged in the rectangular box body along the direction perpendicular to the incoming flow direction and are fixedly connected with the bottom wall of the rectangular box body, and the installation angle alpha of each rotor blade 8 is 15 degrees (refer to fig. 7, 8 and 9). A 5mm spacing (used to simulate tip clearance) is formed between the tip of the rotor blade 8 and the top wall of the rectangular box. The sound pressure sensor is mounted in the rectangular box, and the strain sensor is mounted at the root of the rotor blade 8 in the middle (the part fixedly connected with the bottom wall of the rectangular box). The top wall of the rectangular box body in the three experiments is provided with first jet holes 17 which are equal to the first plasma jet generators 12 in the experiments in number and correspond to each other one by one, and the first jet holes 17 are communicated with the first plasma generation cavity 14 of the first plasma jet generators 12.
All three experiments were performed by turning on or off the first plasma jet generator 12 and by changing the orientation and direction of the first jet aperture 17 to verify the first plasma jet V j Influence of acoustic excitation of the rotor blade 8.
Experiment one
Experiment one aims at verifying that the first plasma jet V when the direction of extension of the first jet hole 17 is directed to different parts of the chord line of the rotor blade 8 in the case where the direction of extension of the first jet hole 17 is directed towards the pressure surface 10 of the rotor blade 8 j Influence on the acoustic excitation of the rotor blade 8.
As shown in fig. 7, the experiment includes two first plasma jet generators 12 (controlling jet frequency 100 Hz), and the top wall of the rectangular box body is correspondingly provided with two first jet holes 17 and 17a. The two first jet holes 17 and 17a form a first included angle beta with the top wall of the rectangular box body, and beta is equal to 30 degrees. Wherein the extension direction of the first jet hole 17 is directed towards the middle of the chord line of the rotor blade 8 and the extension direction of the first jet hole 17a is directed towards the front of the chord line of the rotor blade 8. The first orifice 17 and 17a are used to simulate the first orifice 17 in the first embodiment and the first orifice 17a in the second embodiment, respectively.
The method of the experiment is to gradually increase the incoming flow speed in the wind tunnel under the condition of closing the two first plasma jet generators 12 until the rotor blade 8 generates acoustic excitation, respectively starting one of the two first plasma jet generators 12, and measuring different first plasma jet V j And finally, closing the two first plasma jet generators 12 to perform fatigue test on the rotor blade 8 under the condition of acoustic excitation until the rotor blade 8 is damaged due to the acoustic excitation, and observing the damage condition.
The present experiment produced acoustic excitation of the rotor blade 8 when the incoming flow rate reached 30 m/s. The test results of this experiment are shown in table 1 and fig. 10.
Table 1: test results of experiment one
As is clear from table 1, when the extending direction of the first jet hole 17 is directed toward the pressure surface 10 of the rotor blade 8, the amplitude of the acoustic excitation is most reduced when the extending direction of the first jet hole 17 is directed toward the middle of the chord line of the rotor blade 8.
Fig. 10 shows the structural failure of the rotor blade 8 by the acoustic excitation fatigue test. As can be seen from fig. 10, the rotor blade 8 is caused to be inclined from the root to the middle of the blade due to acoustic excitation. From the above-described damage, the acoustic excitation frequency approaches the third-order vibration frequency of the rotor blade 8, and thus the damage to the rotor blade 8 includes both the damage by bending and the damage by twisting. Thereby making it possible toIt is known that acoustic excitation can cause severe damage to the rotor blade 8. And a first plasma jet V j The amplitude of the acoustic excitation of the rotor blade 8 can be reduced, and the effect of attenuating the acoustic excitation can be effectively improved.
Experiment two
The second experiment was aimed at verifying that the first plasma jet V when the direction of extension of the first jet hole 17 was directed to different portions of the chord line of the rotor blade 8, with the direction of extension of the first jet hole 17 toward the back pressure surface 11 of the rotor blade 8 j Influence on the acoustic excitation of the rotor blade 8.
As shown in fig. 8, the experiment included three first plasma jet generators 12 (controlling jet frequency 100 Hz), and the top wall of the rectangular box body was provided with three first jet holes 17b, 17c and 17d, respectively. The three first jet holes 17b, 17c and 17d each form a first angle beta with the top wall of the rectangular box body, and beta is equal to 30 degrees. Wherein the extending direction of the first jet hole 17b is directed to the front of the chord line of the rotor blade 8, the extending direction of the first jet hole 17c is directed to the middle front of the chord line of the rotor blade 8, and the extending direction of the first jet hole 17d is directed to the middle of the chord line of the rotor blade 8. The first orifice 17b, 17c, and 17d are used to simulate the first orifice 17b in the third embodiment, the first orifice 17c in the fourth embodiment, and the first orifice 17d in the fifth embodiment, respectively.
The method of the experiment is to gradually increase the incoming flow speed in the wind tunnel under the condition of turning off the three first plasma jet generators 12 until the rotor blade 8 generates acoustic excitation, respectively turning on one of the three first plasma jet generators 12 to measure different first plasma jet V j Influence on the acoustic excitation of the rotor blade 8.
The present experiment produced acoustic excitation of the rotor blade 8 when the incoming flow rate reached 30 m/s. The test results of this experiment are shown in Table 2.
Table 2: test results of experiment two
As is clear from table 2, when the extending direction of the first jet hole 17 is directed toward the back pressure surface 11 of the rotor blade 8, the degree of reduction of the acoustic excitation amplitude is highest when the extending direction of the first jet hole 17 is directed toward the middle of the chord line of the rotor blade 8, but is still lower than when the extending direction of the first jet hole 17 is directed toward the pressure surface 10 of the rotor blade 8 and toward the middle of the chord line of the rotor blade 8.
Experiment three
The purpose of experiment three was to verify that the first plasma jet V when the first pilot hole 17 was located at a different location on the tip of the rotor blade 8 with the direction of extension of the first pilot hole 17 toward the tip of the rotor blade 8 j Influence on the acoustic excitation of the rotor blade 8.
As shown in fig. 9, the experiment includes three first plasma jet generators 12 (controlling jet frequency 100 Hz), and the top wall of the rectangular box body is correspondingly provided with three first jet holes 17e, 17f and 17g. The three first jet holes 17e, 17f and 17g are each perpendicular to the top wall of the rectangular box (the first included angle β is equal to 90 °). Wherein the first jet hole 17e is located at the front of the tip of the rotor blade 8, the first jet hole 17f is located at the middle front of the tip of the rotor blade 8, and the first jet hole 17g is located at the middle of the tip of the rotor blade 8.
The method of the experiment is to gradually increase the incoming flow speed in the wind tunnel under the condition of turning off the three first plasma jet generators 12 until the rotor blade 8 generates acoustic excitation, respectively turning on one of the three first plasma jet generators 12 to measure different first plasma jet V j Influence on the acoustic excitation of the rotor blade 8.
The present experiment produced acoustic excitation of the rotor blade 8 when the incoming flow rate reached 30 m/s. The test results of this experiment are shown in Table 3.
Table 3: test results of experiment three
As can be seen from Table 3, when the first jet hole 17 extendsWith the direction of extension towards the tip of the rotor blade 8, a first plasma jet V j The method has no effect of reducing the acoustic excitation amplitude, and improves the acoustic excitation amplitude. From the third experiment, when the extending direction of the first jet hole 17 is perpendicular to the tangential plane of the inner wall of the casing at the opening of the first jet hole 17, the acoustic excitation cannot be reduced.
From the above three experiments, when the extending direction of the first jet hole 17 is perpendicular to the tangential plane of the inner wall of the casing at the opening of the first jet hole 17, the acoustic excitation cannot be reduced. When the direction of extension of the first jet holes 17 is toward the pressure surface 10 of the rotor blade 8 and toward the middle of the chord line of the rotor blade 8, the first plasma jet V j The effect of reducing the amplitude of the acoustic excitation to the rotor blade 8 is best.
The foregoing description of the specification and examples is provided to illustrate the scope of the application and is not intended to limit the scope of the application.
Claims (8)
1. The compressor is an axial-flow compressor and comprises a casing, a hub rotating in an inner cavity of the casing around a rotation axis and a plurality of stages of pressurizing structures distributed along the rotation axis, wherein each stage of pressurizing structure comprises a rotor blade grid and a stator blade grid adjacent to and downstream of the rotor blade grid; the rotor blade grids are arranged on the hub and rotate along with the hub around the rotating axis, and each rotor blade grid comprises a plurality of rotor blades distributed along the circumference of the hub; the stator blade grid is arranged on the inner wall of the casing; it is characterized by also comprising:
at least one group of first plasma jet generator groups, each group of first plasma jet generator groups corresponding to a rotor blade grid; the first plasma jet generator set comprises at least one first plasma jet generator fixedly connected to the outer wall of the casing; each first plasma jet generator emits first plasma jet to the inner cavity of the casing through a first jet hole which is arranged on the casing wall and corresponds to the first plasma jet generator; the extending direction of the first jet hole faces to the pressure surface or the back pressure surface of the rotor blade in the corresponding rotor blade grid and is inclined relative to the tangential plane of the inner wall of the casing at the position of the opening of the first jet hole;
the device also comprises at least one group of second plasma jet generator groups, and each group of second plasma jet generator groups corresponds to a rotor blade grid; the second plasma jet generator set comprises at least one second plasma jet generator fixedly connected to the outer wall of the casing;
each second plasma jet generator emits second plasma jet to the inner cavity of the casing through a second jet hole which is arranged on the casing wall and corresponds to the second plasma jet generator; the opening of the second jet hole on the inner wall of the casing is positioned between the corresponding rotor blade grid and the stator blade grid adjacent to and upstream of the rotor blade grid, and the extending direction of the second jet hole faces the rotating axis;
the second jet hole extends in a direction perpendicular to the rotation axis.
2. A compressor as defined in claim 1 wherein said first jet aperture extends in a direction toward the pressure face of said rotor blade and toward the middle of the chord line of said rotor blade.
3. A compressor as claimed in claim 1 wherein the angle between the direction of extension of the first jet aperture and the tangent plane of the inner wall of the casing at the location of the opening of the first jet aperture is in the range of 25 ° to 35 °.
4. A compressor as claimed in claim 3 wherein the angle between the direction of extension of the first jet aperture and the tangent plane of the inner wall of the casing at the location of the opening of the first jet aperture is 30 °.
5. A compressor as claimed in any one of claims 1 to 4 wherein said first plasma jet generator comprises a first body, a first power source and two first electrodes; the first body is fixedly connected to the outer wall of the casing and forms a first plasma generation cavity communicated with the first jet hole; the first power supply is used for generating pulse voltage; the two first electrodes are respectively and electrically connected with the first power supply and extend into the first plasma generation cavity.
6. The compressor of claim 1 wherein said second plasma jet generator comprises a second body, a second power source and two second electrodes; the second body is fixedly connected to the outer wall of the casing and forms a second plasma generation cavity communicated with the second jet hole; the second power supply is used for generating pulse voltage; the two second electrodes are respectively and electrically connected with the second power supply and extend into the second plasma generation cavity.
7. A method of attenuating acoustic excitation of a rotor blade of a compressor, based on a compressor according to any one of claims 1-6, wherein during operation of the compressor a first plasma jet is emitted to the pressure or back pressure side of the rotor blade through a first jet aperture provided in the casing wall, the first jet aperture extending in a direction inclined relative to the tangential plane of the casing inner wall at the location of the opening of the first jet aperture.
8. A method of attenuating acoustic excitation of a compressor rotor blade as set forth in claim 7, wherein during operation of said compressor, a second plasma jet is also emitted toward a space between the rotor blade cascade and a stator blade cascade adjacent to and upstream of the rotor blade cascade through a second jet aperture opening into the casing wall, the second jet aperture extending in a direction toward the axis of rotation of the hub.
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