CN203051237U - Surge-preventing structure for aero-engine compressor - Google Patents
Surge-preventing structure for aero-engine compressor Download PDFInfo
- Publication number
- CN203051237U CN203051237U CN 201320020277 CN201320020277U CN203051237U CN 203051237 U CN203051237 U CN 203051237U CN 201320020277 CN201320020277 CN 201320020277 CN 201320020277 U CN201320020277 U CN 201320020277U CN 203051237 U CN203051237 U CN 203051237U
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- casing
- surge
- compressor
- stator
- vent hole
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Abstract
The utility model relates to a surge-preventing structure for an aero-engine compressor. A stator ring is mounted inside a compressor case, stator vanes which are evenly and peripherally distributed are arranged on the stator ring, a compressor rotor is located inside the compressor case (1) and is provided with rotor vanes, a radial vent hole is formed between every two stator vanes and at the peripheral position of the stator vanes on the stator ring, and vent holes with the diameters larger than that of each radial vent hole are formed in the corresponding positions on an intermediate case and the compressor case. Speed loss and surge due to overlarge attack angles are eliminated, flow condition is improved, and therefore surge can be prevented effectively. The surge-preventing structure has the advantages that compressor characteristics can be improved, the stable working range can be widened, and the surge-preventing structure can be used for preventing 'front-surge and rear-vortex' type surges and is convenient to process, low in size required accuracy, simple, low in cost and reduced in gas loss.
Description
Technical field
The utility model relates to a kind of aero-engine compressor anti-asthma structure.
Background technique
When the multi stage axial flow compressor of aeroengine is worked under variable working condition, when inlet flow rate reduces, the angle of attack be on the occasion of, air-flow can produce separation in the blade back side, in this zone, separates in case produce, just have and continue the trend that development is gone down, therefore, excessive high incidence can make the job insecurity of gas compressor, thereby causes surge.When engine speed during less than design speed, preceding what gas compressor produces surge owing to the angle of attack is excessive, and the angle of attack reduces in final stage, voltage rise value and efficient reduce rapidly, when operating mode off-design operating mode was very big, the voltage rise value of final stage became negative value probably, is in the turbine state, we become " the preceding whirlpool, back of breathing heavily " state above situation, are multi stage axial flow compressor incidental a kind of phenomenons when the off-design operating mode.
On the gas compressor of the aeroengine of modern high supercharging pressure level, the anti-surge measure is arranged, surge-preventing system can be divided into by mechanism form: but air-release mechanism, arrange and can change inlet guide vane and can change stator blade, design variable camber inlet guide vane, design air inlet processor casing structure and multi-rotor engine structure etc., wherein the principle of air-release mechanism is that air is emitted from gas compressor intergrade or final stage, the method is simple and effective, shortcoming is that the air after the supercharging is bled off in vain, and the efficient of gas compressor is reduced; Setting can change inlet guide vane and can change stator blade be when gas compressor when off design point is worked, with angle of inlet guide vane rotation, make the corresponding change of the pre-spinor of compressor inlet, so just can make the air inlet angle of attack of first order working blade return to situation near design point, eliminate the airflow breakaway on the blade back, avoided the generation of surging phenomenon; But the inlet guide vane of design variable camber, blade is formed by forward and backward two sections, and leading portion is fixing to adapt to the situation of incoming flow, and back segment can regulate to guarantee the desired air inlet angle of attack of working blade continuously; Design air inlet processor casing structure refers to open narrow slit, groove, hole etc. at compressor air inlet machine casing place wall, can postpone the stall of blade, enlarges the surge margin of gas compressor; Birotary engine since it to have operating range than one-spool engine on the situation of identical pressure ratio wide, progression is few under the same pressure ratio, off design point efficient advantages of higher.The structure of triple-spool, supporting, power transmission, lubricated all complicated, the cost height.
Summary of the invention
The purpose of this utility model provide a kind of simply, aero-engine compressor anti-asthma structure efficiently, can improve compressor characteristics, enlarge stable operation range, and can be used for preventing " the preceding whirlpool, back of breathing heavily " type surge.
The technical solution of the utility model is: the anti-asthma structure of aero-engine compressor comprises the casing of calming the anger, intermediary's casing and stator ring, intermediary's casing is installed on the casing of calming the anger, the casing inside of calming the anger is equipped with the stator ring, the stator ring is provided with circumferentially uniform stator blade, compressor rotor 4 is positioned at calms the anger casing and rotor blade is installed, rotor blade and stator blade are interlaced, form main duct, intermediary casing outside is by-pass air duct, be positioned at all stator blades position on the stator ring, in the middle of per 2 stator blades, have radially vent hole, corresponding position has diameter greater than the vent hole of vent hole radially on calm the anger casing and intermediary's casing, described stator blade and radially vent hole be 76, the diameter of the vent hole on the described stator ring is 5mm, and the diameter of the vent hole on calm the anger casing and the intermediary's casing is 6mm.
The utility model in use, the vent hole of the gas in the main duct of gas compressor by the stator ring enters in the annular chamber between stator ring outer shroud and the compressor casing, and then flows in the by-pass air duct by the vent hole of compressor casing and intermediary's casing.By venting, the flow of chopped-off head gas compressor increases, and corresponding axial velocity and flow coefficient increase, and the angle of attack is excessive to be caused stall and likelihood of turbocharger surge takes place thereby eliminated; Because the improvement of chopped-off head gas compressor operating conditions and the raising of pressure ratio and efficient, the air density of final stage increases, and flox condition also improves, thereby can prevent surge effectively.The advantage of this structure is can improve compressor characteristics, enlarge stable operation range, and can be used for preventing " the preceding whirlpool, back of breathing heavily " type surge, has easy to processly simultaneously, and the size requirement precision is low, and is simple in structure, the characteristics that cost is low, reduce gas loss.
Description of drawings
Fig. 1 is structural representation of the present utility model.
Embodiment
As shown in the figure, the anti-asthma structure of aero-engine compressor comprises the casing 1 of calming the anger, intermediary's casing 2 and stator ring 3, intermediary's casing 2 is installed on the casing 1 of calming the anger, casing 1 inside of calming the anger is equipped with stator ring 3, stator ring 3 is provided with circumferentially uniform stator blade 6, compressor rotor 4 is positioned at calms the anger casing 1 and rotor blade 5 is installed, rotor blade 5 is interlaced with stator blade 6, form main duct 10, intermediary's casing 2 outsides are by-pass air duct 11, be positioned at all stator blades 6 positions on the stator ring 3, in the middle of per 2 stator blades 6, have radially vent hole 7, corresponding position has diameter greater than the vent hole 8 of vent hole 7 radially on calm the anger casing 1 and intermediary's casing, described stator blade 6 and radially vent hole be 76, the diameter of the vent hole 7 on the described stator ring 3 is 5mm, and the diameter of the vent hole 7 on calm the anger casing 1 and the intermediary's casing 2 is 6mm.
Claims (3)
1. aero-engine compressor anti-asthma structure, it is characterized in that, described structure comprises the casing of calming the anger [1], intermediary's casing [] 2 and stator ring [3], intermediary's casing [2] is installed on the casing of calming the anger [1], casing [1] inside of calming the anger is equipped with stator ring [3], stator ring [3] is provided with circumferentially uniform stator blade [6], compressor rotor [4] is positioned at the casing of calming the anger [1] and rotor blade [5] is installed, rotor blade [5] is interlaced with stator blade [6], form main duct [10], intermediary's casing [2] outside is by-pass air duct [11], be positioned at all stator blades [6] position on the stator ring [3], per 2] have radially vent hole [7] in the middle of the sheet stator blade [6], corresponding position has diameter greater than the vent hole [8] of vent hole [7] radially on the casing of calming the anger [1] and intermediary's casing.
2. aero-engine compressor anti-asthma structure as claimed in claim 1 is characterized in that, described stator blade [6] and radially vent hole be 76.
3. aero-engine compressor anti-asthma structure as claimed in claim 1 is characterized in that, the diameter of the vent hole [7] on the described stator ring [3] is 5mm, and the diameter of the vent hole [7] on the casing of calming the anger [1] and the intermediary's casing [2] is 6mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320020277 CN203051237U (en) | 2013-01-15 | 2013-01-15 | Surge-preventing structure for aero-engine compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320020277 CN203051237U (en) | 2013-01-15 | 2013-01-15 | Surge-preventing structure for aero-engine compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203051237U true CN203051237U (en) | 2013-07-10 |
Family
ID=48734195
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320020277 Expired - Fee Related CN203051237U (en) | 2013-01-15 | 2013-01-15 | Surge-preventing structure for aero-engine compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203051237U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108223429A (en) * | 2017-09-30 | 2018-06-29 | 中国航发沈阳发动机研究所 | The fancase of the domain not fault wall |
| CN111188779A (en) * | 2020-01-08 | 2020-05-22 | 易利锋 | Gas compressor of gas turbine engine |
| CN111664124A (en) * | 2020-06-05 | 2020-09-15 | 中国航发沈阳发动机研究所 | Stator structure, rotor and stator assembly structure with same and assembly method of rotor and stator assembly structure |
-
2013
- 2013-01-15 CN CN 201320020277 patent/CN203051237U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108223429A (en) * | 2017-09-30 | 2018-06-29 | 中国航发沈阳发动机研究所 | The fancase of the domain not fault wall |
| CN111188779A (en) * | 2020-01-08 | 2020-05-22 | 易利锋 | Gas compressor of gas turbine engine |
| CN111664124A (en) * | 2020-06-05 | 2020-09-15 | 中国航发沈阳发动机研究所 | Stator structure, rotor and stator assembly structure with same and assembly method of rotor and stator assembly structure |
| CN111664124B (en) * | 2020-06-05 | 2022-07-26 | 中国航发沈阳发动机研究所 | Stator structure, rotor and stator assembly structure with same and assembly method of rotor and stator assembly structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130710 Termination date: 20210115 |