CN101105187B - Pre-cyclone vane type engine case processing method - Google Patents
Pre-cyclone vane type engine case processing method Download PDFInfo
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- CN101105187B CN101105187B CN2007100243785A CN200710024378A CN101105187B CN 101105187 B CN101105187 B CN 101105187B CN 2007100243785 A CN2007100243785 A CN 2007100243785A CN 200710024378 A CN200710024378 A CN 200710024378A CN 101105187 B CN101105187 B CN 101105187B
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- 238000003672 processing method Methods 0.000 title claims description 10
- 238000000926 separation method Methods 0.000 claims abstract description 9
- 230000035939 shock Effects 0.000 claims description 17
- 230000008676 import Effects 0.000 claims description 11
- 230000015572 biosynthetic process Effects 0.000 claims description 4
- 238000004891 communication Methods 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 8
- 230000006835 compression Effects 0.000 abstract 1
- 238000007906 compression Methods 0.000 abstract 1
- 239000007921 spray Substances 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 11
- 239000012530 fluid Substances 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000001914 calming effect Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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- 238000007789 sealing Methods 0.000 description 1
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Abstract
The invention relates to a pre-rotation vane type casing treatment method. The method comprises performing casing air-entraining at the site where shockwave-induced boundary layer separation is prone to occur to control the separation; leading the entrained airflow to the front of the inlet port of the vane by a vane type treatment casing to form airflow with radial and circumferential speed 0.05-0.3 times of the vane main flow speed and spray out, so as to form pre-rotation flow with the same rotation direction as the vanes at the inlet port. The pre-rotation vane type treatment casing is equipped from the front of the inlet port of a mini-type centrifuging/oblique flow compressor to the casing site corresponding to the front half part of the rotor vanes, and mainly composed of an air suction belt, an exhaust port and a closed vane passage. The invention can effectively control the flow field of the centrifuging/oblique flow compressor, inhibit surging thereof due to unstable operating state, and can enlarge the stable operation range of such type compressor under high rotation speed (high wheel rim linear velocity), so that the compressor can achieve higher compression ratio under the prerequisite of meeting stable operation requirement, thereby providing compressor-using system better performance.
Description
Technical field
What the present invention relates to is the pre-cyclone vane type engine case processing method of controlling centrifugal/inclined flow air compressor flow field, suppressing its unstable working state surge, belongs to centrifugal or diagonal flow type gas compressor technical field,
Background technique
Centrifugal/inclined flow air compressor the outlet that is widely used in middle or small and miniature turbine motor is developing towards more and more higher direction (greater than 5) with the ratio of import stagnation pressure, corresponding, the development trend of impeller tangential velocity is: import blade tip tangential velocity is brought up to 350～400m/s, and the outlet tangential velocity is brought up to 550～650m/s.But, existingly studies show that centrifugal compressor unstable working state surge meeting under high rotating speed early occurs, thereby cause its stable operation range significantly to reduce.With respect to the centrifugal compressor of stock size, minitype compressor efficient is lower, and for reaching the same high outlet and the higher tangential velocity of ratio needs of inlet pressure, this can increase the weight of the little problem of high speed stable operation range; In addition, minitype compressor is because reynolds' number significantly reduces (littler 1 more than the order of magnitude than conventional engine), and boundary layer is easier to be separated, and makes that the little problem of high speed stable operation range is more serious.Therefore, in order to develop more high performance miniature turbine motor, must study the technology of the high stabilization of speed operating range of expanding micro gas compressor.
Because allowing minitype compressor run to more high-revolving purpose is exactly to obtain higher pressure ratio, so that miniature turbine starts function to obtain the thrust of bigger thrust and Geng Gao and the ratio of engine weight.So minitype compressor is expanded stable operation range and should be kept higher pressure ratio just meaningful under high rotating speed, that is to say that expansion surely should make great efforts to expand the stall margin but not stop up the border.
A new generation's minitype compressor surpasses 5 for realizing pressure ratio, the import blade tip tangential velocity of high rotating speed lower rotor part impeller will reach 350～400m/s, flowing relatively of its impeller inlet blade tip district (even bigger zone) must be supersonic speed at this moment, and the Ma number can surpass 1.4 relatively, can produce stronger shock wave in the impeller passage.In this case, as not taking measures, thereby following two kinds of fluidal textures may take place in the impeller of rotor cause surge: (1) is very high at rotating speed, shock wave front Ma number was greater than 1.4 o'clock, the strong (see figure 1) of disturbing takes place in shock wave and blade back side boundary layer, cause the interference range airflow breakaway, will cause surge.(2) be not very high at rotating speed, shock wave front Ma number is not under the very big situation, and general impeller inlet section less than the big separation of air-flow surge does not take place.When runner downstream back-pressure increased, shock wave can move forward and form the detached shock wave (see figure 2), and the overflow to blade back side adjacency channel takes place air-flow behind the ripple, and the angle between airintake direction and the blade (angle of attack) increases.This just makes compressor blade leading edge generation blade back side separate easily, thereby causes surge.
Summary of the invention
The object of the invention is intended to overcome the above-mentioned defective of existing in prior technology, proposes a kind of processing method of prerotation vane casing, and they can effectively be controlled centrifugal/inclined flow air compressor flow field, suppress the surge of its unstable working state.
Technical solution of the present invention: this method is that the bleed of prerotation vane processor box is carried out to control this separation in the position that easy generation shock wave brings out the boundary layer separation in impeller passage; And the air communication of institute's carrying-off is crossed the blade type processor box guide to that to form before the impeller inlet be the air-flow ejection of 0.05-0.3 times of impeller mainstream speed with circumferential speed radially, at the import formation preswirl identical with the impeller sense of rotation.
Advantage of the present invention: improve shock wave and blade back side boundary layer the strong caused interference range airflow breakaway of disturbing takes place, effective surge of controlling centrifugal/inclined flow air compressor flow field, suppressing its unstable working state, and can enlarge this class gas compressor stable operation range under high rotating speed (high linear speed), make the function of calming the anger satisfy the stable operation requirement and be issued to higher pressure ratio, thereby provide higher performance for the system that uses gas compressor.Simultaneously, relief opening is discharged air-flow makes the impeller main flow form the preswirl identical with the impeller sense of rotation, causes surge thereby suppress impeller blade leading edge detached shock wave.Time stream flow that passes through from the prerotation vane processor box is along with the change of working staties such as wheel speed is regulated automatically: the flow increase satisfies the demands automatically when needing this device control effect strong at a high speed, and time stream flow reduces automatically during low speed.The present invention suppressed from two aspects simultaneously high speed miniature centrifugal/surge of inclined flow air compressor, to enlarge high speed and high pressure than miniature centrifugal/there is good effect the inclined flow air compressor stall margin, simultaneously, the present invention can both bring into play good effect in the operating range of gas compressor broadness.In a word, the present invention can increase the stable operation range of the miniature centrifugal/inclined flow air compressor of high speed and high pressure ratio, makes it have more the real world applications meaning.
Description of drawings
Accompanying drawing 1 is that shock wave/boundary layer does not disturb to cause and separates when adopting any measure.
Accompanying drawing 2 is that the leading edge that detached shock wave causes when not adopting any measure is separated.
Accompanying drawing 3 is to flow in the prerotation vane processor box passage.
Accompanying drawing 4 is that shock wave under the absorbing gas belt effect/boundary layer disturbs initiation to separate.
Accompanying drawing 5 is that the leading edge that detached shock wave causes under the relief opening effect is separated.
Accompanying drawing 6 is prerotation vane processor box meridian plane schematic representation.
Among the figure 10 expression prerotation vane processor box absorbing gas belt central position; 11 expression prerotation vane processor box relief opening central positions; 12 expression impeller inlet blade tip diameters; 13 expression impeller primary blades meridian surface shape length; The distance of 14 expression relief opening centers and impeller primary blades leading edge; The meridional flow of 15 expression absorbing gas belt centers and impeller primary blades leading edge is to distance.
Embodiment
Pre-cyclone vane type engine case processing method is to carry out the bleed of prerotation vane processor box to control this separation in the position that easy generation shock wave in impeller passage brings out the boundary layer separation; And the air communication of institute's carrying-off is crossed the blade type processor box guide to that to form before the impeller inlet be the air-flow ejection of 0.05～0.3 times of impeller mainstream speed with circumferential speed radially, at the import formation preswirl identical with the impeller sense of rotation;
The structure of described prerotation vane processor box is formed (shown in Fig. 3,6) by absorbing gas belt, processor box passage and three major components of relief opening.Wherein, absorbing gas belt is positioned at certain suitable position after the impeller primary blades leading edge; Relief opening is positioned at certain position before the primary blades leading edge, and flow condition is definite near centrifugal/inclined flow air compressor leading edge that discharge directions is used according to the prerotation vane processor box; Absorbing gas belt is connected with the blade path of relief opening by processor box, blade path is all sealings except that absorbing gas belt and relief opening, and the moulding of blade path is smooth and easy with air current flow in it, flow losses are little is near flow condition, the required flow angle matching design of relief opening in impeller principle and the absorbing gas belt.
Near the downstream of bleed band corresponding position blade inlet edge relief opening in centrifugal/inclined flow air compressor is because the pressurization of impeller is so the pressure at bleed band place is higher than relief opening.Low kinetic energy fluid (shock wave/formation such as the boundary layer interference) sucking-off that the bleed band can be piled up impeller blade back tip under the effect of pressure reduction is like this guided to relief opening and is produced positive eddy flow in the impeller blade leading edge by the stator in the passage.
The low energy fluid that the blade back tip is piled up is by the sucking-off of bleed band, reduce or eliminated these low energy fluid under contrary pressure gradient effect, forming the possible (see figure 4) that flows backwards, thereby prevent or postponed first kind of generation that causes the situation of surge being analyzed in the background technique.Before the air-flow effect downstream that relief opening penetrates enters blade path, had the circumferential speed (see figure 5) identical, suppressed the effect that the impeller leading edge is separated thereby reach with the rotary blade sense of rotation.
Described relief opening is the open front of prerotation vane processor box, its center is arranged at the preceding corresponding casing place apart from impeller primary blades import 0.05～0.5 multiplication of voltage mechanism of qi inlet diameter of gas compressor, and function is to discharge air-flow to make the impeller main flow form the preswirl (promptly just prewhirl) identical with the impeller sense of rotation.
The internal gas flow passage that described enclosed blade path is the prerotation vane processor box, be arranged between absorbing gas belt and the relief opening, its structure be by the enclosed blade path of several quantity along circumferentially being consecutively arranged to form, function be the sucking-off of guiding absorbing gas belt gas to relief opening and make air-flow betwixt by the time obtain quickening to form preswirl at relief opening with enough kinetic energy.
The pairing casing of 0.1～0.4 gall nut noon runner blade tip molded lines total length place after the impeller blade import that prerotation vane processor box absorbing gas belt center is arranged on, the low energy fluid that is piled up in the blade back tip (Fig. 4) that sucking-off is caused by the interference of shock wave boundary layer, boundary layer separation, secondary flow etc. is to cause first kind of fluidal texture (Fig. 1) of surge thereby improve the described treatment measures of not taking of background technique; The gas of sucking-off guides to the relief opening that is arranged at before the gas compressor by the enclosed blade path between absorbing gas belt and the relief opening, relief opening is discharged air-flow makes the impeller main flow form the preswirl identical with the impeller sense of rotation, thereby improves the second kind of fluidal texture (Fig. 2) that causes surge when background technique is described not to process measure.
Before the air-flow effect downstream that relief opening penetrates enters blade path, had the circumferential speed (see figure 5) identical, suppressed the effect that the impeller leading edge is separated thereby reach with the rotary blade sense of rotation.
Because corresponding the change takes place in the pressure difference of absorbing gas belt and prerotation vane processor box absorbing gas belt and relief opening under compressor impeller different operating state, so its throughput of drawing is along with the change of the working state of assembling impeller is regulated automatically.
Claims (5)
1. pre-cyclone vane type engine case processing method is characterized in that easily taking place shock wave and brings out the position that boundary layer separates and carry out the casing bleed to control this separation in impeller passage; And the air communication of institute's carrying-off is crossed the blade type processor box guide to that to form before the impeller inlet be the air-flow ejection of 0.05-0.3 times of impeller mainstream speed with circumferential speed radially, at the import formation preswirl identical with the impeller sense of rotation.
2. the processing method of a kind of prerotation vane processor box according to claim 1, it is characterized in that the blade type processor box be arranged on miniature centrifugal/the inclined flow air compressor import before to the pairing casing of the front half part of impeller of rotor place, mainly constitute by absorbing gas belt, relief opening and enclosed blade path.
3. a kind of pre-cyclone vane type engine case processing method according to claim 2, it is characterized in that described absorbing gas belt is the rear aperture of prerotation vane processor box, its center is arranged on the pairing casing of 0.1～0.4 gall nut noon runner blade tip molded lines total length place after the impeller blade import.
4. a kind of pre-cyclone vane type engine case processing method according to claim 2, it is characterized in that described relief opening is the open front of prerotation vane processor box, its center is arranged at the preceding corresponding casing place apart from impeller primary blades import 0.05～0.5 multiplication of voltage mechanism of qi inlet diameter of gas compressor, function is to discharge air-flow to make the impeller main flow form the preswirl identical with the impeller sense of rotation, promptly just prewhirls.
5. a kind of pre-cyclone vane type engine case processing method according to claim 2, it is characterized in that the internal gas flow passage that described enclosed blade path is the prerotation vane processor box, be arranged between absorbing gas belt and the relief opening, processor casing structure is along circumferentially being consecutively arranged to form by several enclosed blade paths.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2007100243785A CN101105187B (en) | 2007-06-14 | 2007-06-14 | Pre-cyclone vane type engine case processing method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2007100243785A CN101105187B (en) | 2007-06-14 | 2007-06-14 | Pre-cyclone vane type engine case processing method |
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| CN101105187A CN101105187A (en) | 2008-01-16 |
| CN101105187B true CN101105187B (en) | 2011-04-20 |
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| CN2007100243785A Expired - Fee Related CN101105187B (en) | 2007-06-14 | 2007-06-14 | Pre-cyclone vane type engine case processing method |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102022351B (en) * | 2010-12-08 | 2012-06-27 | 北京航空航天大学 | Method for widening stable working range of high-load axial flow gas compressor |
| CN102297149B (en) * | 2011-09-08 | 2014-07-02 | 中国科学院上海高等研究院 | Device and method for widening stable operation area of centrifugal compressor, and centrifugal compressor |
| CN111396196A (en) * | 2019-01-02 | 2020-07-10 | 中国航发商用航空发动机有限责任公司 | S-shaped switching section of gas compressor and turbofan engine |
| CN113217461B (en) * | 2021-05-12 | 2022-08-16 | 中南大学 | Blade, molding method and manufacturing method thereof and air compressor |
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