CN103852234A - Surge limit measurement method for continuous transonic wind tunnel - Google Patents
Surge limit measurement method for continuous transonic wind tunnel Download PDFInfo
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- CN103852234A CN103852234A CN201410083994.8A CN201410083994A CN103852234A CN 103852234 A CN103852234 A CN 103852234A CN 201410083994 A CN201410083994 A CN 201410083994A CN 103852234 A CN103852234 A CN 103852234A
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Abstract
The invention relates to a surge limit measurement method for a continuous transonic wind tunnel. For an axial flow compressor installed in the continuous transonic wind tunnel, the surge limit of the axial flow compressor in the continuous transonic wind tunnel is measured, and it is fully ensured that the surge limit is applicable to the future running condition of the wind tunnel. Working after the compressor and the wind tunnel are connected and independent working of the compressor are usually different in structural resonance point. According to the surge limit measurement method for the continuous transonic wind tunnel, due to the fact that the compressor and the wind tunnel body are in the connected state, potential hazard caused by offset of the resonance point of the compressor is avoided when the surge limit is measured.
Description
Technical field
The present invention relates to one and relate to axial compressor stall margin assay method, be particularly useful for being arranged on the stall margin mensuration of transonic wind tunnel loop Axial-Flow compressor.The stall margin that is just mounted in the axial compressor in wind-tunnel loop that wind-tunnel stall margin refers to.
Background technology
When axial compressor generation surge, in the runner of compressor, by occurring strong gas, cause the increase of rotor and stator dynamic stress, thereby cause unit high vibration, compressor cannot normally be worked, and this phenomenon is referred to as " surge ".Surge phenomenon, as got rid of not in time, will directly cause compressor train to be damaged.Avoid the generation of compressor surge phenomenon, must find out in advance the pumping point of compressor, but there is no at present method by calculate estimate out exactly, can only, in the time of compressor performance test, judge according to actual conditions the pumping point that it is approximate.
Axial compressor is mainly used in the purposes such as the ventilation in large-scale factories and miness or tunnel; its inlet end generally connects ambient atmosphere; air-flow will directly be sent to hole, ore deposit after compressor; manufacturer is often all furnished with the compressor heat examination platform of this working environment of simulation; before dispatching from the factory, compressor completes the test to its stall margin; set corresponding closely breathing heavily and protected border, its result is completely for actual field of employment.
But the working environment of compressor is enclosed wind-tunnel loop in wind-tunnel loop, the gas flow after compressor compresses is got back to again suction port of compressor through wind-tunnel loop and is again entered compressor.Traditional stall margin assay method is not suitable for this occasion, even if carrying out stall margin before dispatching from the factory on heat examination platform measures, if but its stall margin is directly used in actual use occasion, can produce very large deviation, may cause thus the error to compressor surge judgement, thus the serious consequence that causes compressor and upstream device thereof to damage.
Summary of the invention
The technical matters solving
For fear of the deficiencies in the prior art part, the present invention proposes a kind of continous way transonic wind tunnel stall margin assay method, to reach the target of the Axial Flow Compressor generation surge of avoiding in continous way transonic wind tunnel.
Technical scheme
A kind of continous way transonic wind tunnel stall margin assay method, is characterized in that: Axial Flow Compressor is arranged in continous way transonic wind tunnel, and determination step is as follows:
Step 1: pressure, the temperature of continuous collecting compressor incoming flow, and calculate the volume flow Q of the compressor of flowing through;
Step 2: set the original state of compressor and wind-tunnel, start compressor, increase the rotation speed n of compressor according to the ladder of setting, it is remained on rotating speed of target and move;
Step 3: close the quick valve in the bypass of wind-tunnel anti-asthma according to the ladder of setting, in this process, if open the quick valve in the bypass of wind-tunnel anti-asthma when compressor approaches surge, and record compressor rotary speed n1 and stator blade angle β 1 this moment, the volume flow Q 1 of compressor of now flowing through is the pumping point of compressor in the time of rotation speed n 1 and stator blade angle β 1, if there is not yet surge until stator blade angle arrives desired value β 1 compressor, enter step 4;
Step 4: increase compressor stator blade angle β according to the ladder of setting, in this process, if open the quick valve in the bypass of wind-tunnel anti-asthma when compressor approaches surge, and record compressor rotary speed n2 and stator blade angle β 2 this moment, the volume flow Q 2 of compressor of now flowing through is the pumping point of compressor in the time of rotation speed n 2 and stator blade angle β 2, if there is not yet surge until stator blade angle arrives desired value β 2 compressors, the normal operation of compressor enters step 5;
Step 5: reduce the aperture of convection current through the larger motion of the gas flow impact of compressor, reduce compressor gas flow according to the ladder of setting; In this process, if open quick valve in the bypass of wind-tunnel anti-asthma when compressor approaches surge, motion returned to original position, and record compressor rotary speed n3 and stator blade angle β 3 this moment, the volume flow Q 3 of compressor of now flowing through is the pumping point of compressor in the time of rotation speed n 3 and stator blade angle β 3, if there is not yet surge until motion closes to smallest compressor, illustrate that wind-tunnel can move arbitrarily for 3 times at compressor rotary speed n3 and stator blade angle β;
Step 6: all pumping points that obtain in step 3, step 4 and step 5 are linked to be to line, obtain the stall margin of compressor in the time of rotating speed of target n.
The basis for estimation that approaches surge of described compressor is: the amplitude of pressure fluctuation of compressor air-discharging is greater than 15% of normal value, or compressor shaft vibration amplitude is greater than 1.5 times of normal runtime value.
Beneficial effect
A kind of continous way transonic wind tunnel stall margin assay method that the present invention proposes, for the Axial Flow Compressor being arranged in continous way transonic wind tunnel, can realize the stall margin of continous way transonic wind tunnel axis streaming compressor is measured, and fully ensure that this stall margin is applicable to wind-tunnel operating condition from now on.Mesomerism point when work works independently with compressor after compressor is connected with wind-tunnel is often different, in the method proposing in the present invention, because compressor and wind tunnel noumenon are in connection status, therefore can also avoid the resonance point of compressor to be offset the potential hazard bringing while test in stall margin.
Brief description of the drawings
Fig. 1: compressor surge point testing experiment process flow diagram
Fig. 2: NF-6 wind tunnel principle figure and compressor, grid refer to, the signal of anti-asthma bypass position
Fig. 3: wind-tunnel diffuser grid refer to force breathes heavily motion schematic diagram
Fig. 4: the oscillogram of compressor delivery pressure and speed
(a) when nominal situation
(b) when surging condition
Fig. 5: compressor shaft oscillating curve figure
Fig. 6: the pumping point test data of compressor rotary speed n=1600rpm
Fig. 7: the pumping point test data of compressor rotary speed n=2100rpm
Fig. 8: compressor surge border
1-compressor, 2-test chamber, 3-grid refer to, 4-anti-asthma bypass quick valve, 5-wind tunnel side wall, 6-airflow direction, 7-suction port of compressor oscillating component, 8-compressor outlet oscillating component, pumping point test data when 9-compressor is 40 ° at 1600rpm stator blade angle, pumping point test data when 10-compressor is 50 ° at 1600rpm stator blade angle, pumping point test data when 11-compressor is 60 ° at 1600rpm stator blade angle, pumping point test data when 12-compressor is 70 ° at 1600rpm stator blade angle, pumping point test data when 13-compressor is 80 ° at 1600rpm stator blade angle, pumping point test data when 14-compressor is 55 ° at 2100rpm stator blade angle, pumping point test data when 15-compressor is 65 ° at 2100rpm stator blade angle, pumping point test data when 16-compressor is 75 ° at 2100rpm stator blade angle, the stall margin of 17-compressor in the time of 1600rpm, the stall margin of 18-compressor in the time of 2100rpm, the stall margin of 19-compressor in the time of 2524rpm, the stall margin of 20-compressor in the time of 2900rpm, the stall margin of 21-compressor in the time of 3000rpm, the stall margin of 22-compressor in the time of 3200rpm.
Embodiment
Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:
The embodiment of the present invention is as follows:
Step 1: activate wind tunnel data capture program, the parameter such as pressure, temperature of compressor incoming flow is implemented to continuous acquisition, and calculate the volume flow Q of the compressor of flowing through, this step is emphasized continuous collecting, until whole off-test just can stop gathering;
Step 2: set the original state of compressor and wind-tunnel, start compressor, point ladder increases compressor rotary speed n, finally manages to make it remain on rotating speed of target;
Step 3: point ladder, close the quick valve in the bypass of wind-tunnel anti-asthma lentamente, in process, note observing and judging whether compressor approaches surge in time, open immediately, fast the quick valve in the bypass of wind-tunnel anti-asthma if approach surge, and record compressor rotary speed n1 and stator blade angle β 1 this moment, the volume flow Q 1 of compressor of now flowing through is the pumping point of compressor in the time of rotation speed n 1 and stator blade angle β 1, if there is not yet surge until stator blade angle arrives desired value β 1 compressor, enter step 4;
Step 4: point ladder, increase compressor stator blade angle β lentamente, finally reach angle on target, in process, note observing and judging whether compressor approaches surge in time, open fast the quick valve in the bypass of wind-tunnel anti-asthma if approach surge, and record compressor rotary speed n2 and stator blade angle β 2 this moment, the volume flow Q 2 of compressor of now flowing through is the pumping point of compressor in the time of rotation speed n 2 and stator blade angle β 2, if there is not yet surge until stator blade angle arrives desired value β 2 compressors, enter step 5;
Step 5: find out in the time of wind-tunnel commencement of commercial operation, convection current is through the larger motion of gas flow impact of compressor, as mechanisms such as second throats, manage to divide ladder by reducing mechanism aperture, reduce lentamente compressor gas flow, in process, note observing and judging whether compressor approaches surge in time, open fast the quick valve in the bypass of wind-tunnel anti-asthma if approach surge, motion is returned to original position, and record compressor rotary speed n3 and stator blade angle β 3 this moment, the volume flow Q 3 of compressor of now flowing through is the pumping point of compressor in the time of rotation speed n 3 and stator blade angle β 3, if there is not yet surge until motion closes to smallest compressor, illustrate that wind-tunnel can move arbitrarily for 3 times at compressor rotary speed n3 and stator blade angle β,
Step 6: by step 3, step 4, step 5, obtain all pumping points be linked to be line, obtain the stall margin of compressor in the time of rotating speed of target n.
Wherein, described in step 3, step 4, step 5, the basis for estimation that whether approaches surge about compressor is mainly: the amplitude of pressure fluctuation of compressor air-discharging is greater than 15% of normal value, or compressor shaft vibration amplitude is greater than 1.5 times of normal runtime value.
Specific embodiment is:
The compressor of the NF-6 wind-tunnel to Northwestern Polytechnical University carries out stall margin mensuration.This wind-tunnel is a continous way transonic wind tunnel, and power source is an Axial Flow Compressor.
Step (1): activate wind tunnel data capture program, the parameter such as pressure, temperature of compressor incoming flow is implemented to continuous acquisition, and calculate the volume flow Q of the compressor of flowing through;
Step (2): compressor stator blade angle β is set as to 30 ° of initial values, wind-tunnel anti-asthma bypass valve standard-sized sheet, wind-tunnel grid refer to two venturi standard-sized sheets.Start compressor, according to 0,100,300,500 ..., order divide ladder to increase gradually rotating speed, finally reach and remain on rotating speed of target 1600rpm;
Step (3): point ladder, increase compressor stator blade angle β lentamente, finally reach angle on target, in process, note observing and judging whether compressor approaches surge in time, if approaching surge opens fast quick valve in the bypass of wind-tunnel anti-asthma, initial position is recovered in compressor stator blade angle, and record stator blade angle β 4 this moment, the volume flow Q 4 of compressor of now flowing through is the pumping point of compressor in the time of rotating speed 1600rpm and stator blade angle β 4, if there is not yet surge until stator blade angle arrives desired value β 4 compressors, enter next step;
Step (4): point ladder, close the quick valve in the bypass of wind-tunnel anti-asthma lentamente, in process, note observing and judging whether compressor approaches surge in time, open immediately, fast the quick valve in the bypass of wind-tunnel anti-asthma if approach surge, and record stator blade angle β 5 this moment, the volume flow Q 5 of compressor of now flowing through is the pumping point of compressor in the time of rotating speed 1600rpm and stator blade angle β 5, if there is not yet surge until stator blade angle arrives desired value β 5 compressors, enter next step;
Step (5): manage by increasing the insertion that refers to of grid, divide ladder, reduce lentamente compressor gas flow, in process, note observing and judging whether compressor approaches surge in time, open fast the quick valve in the bypass of wind-tunnel anti-asthma if approach surge, compressor stator blade angle and grid are referred to recover initial position, and record stator blade angle β 6 this moment, the volume flow Q 6 of compressor of now flowing through is the pumping point of compressor in the time of rotating speed 1600rpm and stator blade angle β 6, if there is not yet surge until motion closes to smallest compressor, illustrate that wind-tunnel can move arbitrarily for 6 times at compressor rotary speed 1600rpm and stator blade angle β,
Step (6): all pumping points that obtain in step (3), step (4), step (5) are linked to be to line, obtain the stall margin of compressor in the time of rotating speed of target 1600rpm.
Step (7): implementation step (1) to step (6) can obtain the stall margin under another one rotating speed of target again, and the surge curve under all rotating speed of target is united, and obtains the stall margin of wind tunnel compressor.
Wherein, described in step (3), step (4), step (5), the basis for estimation that whether approaches surge about compressor is mainly:
Criterion (1): pressure and the velocity variations of monitoring compressor outlet
When compressor normally moves, the variation of its top hole pressure and speed is to increase regularly or reduce, but in the time closing on pumping point work, the top hole pressure of compressor and speed all will present significantly periodically pulsing.Fig. 3 has provided NF-6 wind tunnel compressor in the time of normal work and while closing on surge, the pressure p of compressor outlet and the time dependent oscillogram of speed v elocity.
Criterion (2): monitoring compressor block and bear vibration situation
When compressor normally moves, the vibration amplitude of compressor block and bearing is very little, but in the time closing on pumping point work, the vibration of compressor train will aggravate, and the amplitude of body and bearing obviously increases.Fig. 4 has provided the curve that compressor shaft vibration that NF-6 wind-tunnel gathers in the time carrying out stall margin test under certain rotating speed changes with compressor rotary speed, according to the concrete condition of this wind-tunnel, thinks that, in the time that shaft vibration is greater than 4mm/s, compressor approaches surge.
Criterion (3): monitor and listen to the pneumatic noise that compressor outlet sends
When compressor normally moves, the noise of whole system is stable and continuous, but in the time closing on pumping point work, there will be the periodically sound of " puffing and blow ... puff and blow ... ", and decibel value at this moment also obviously increases.Conventionally the variation phase specific pressure of sound, vibration, flow, power etc. want slower.
The experiment process figure of above compressor surge point testing procedure as shown in Figure 5.
According to above step, the pumping point test data that obtains compressor rotary speed n=1600rpm is shown in Fig. 6, and the pumping point test data of compressor rotary speed n=2100rpm is shown in Fig. 7.The compressor surge border finally obtaining is as Fig. 8, and this stall margin has met wind tunnel operation requirement, has reached test objective.
Claims (2)
1. a continous way transonic wind tunnel stall margin assay method, is characterized in that: Axial Flow Compressor is arranged in continous way transonic wind tunnel, and determination step is as follows:
Step 1: pressure, the temperature of continuous collecting compressor incoming flow, and calculate the volume flow Q of the compressor of flowing through;
Step 2: set the original state of compressor and wind-tunnel, start compressor, increase the rotation speed n of compressor according to the ladder of setting, it is remained on rotating speed of target and move;
Step 3: close the quick valve in the bypass of wind-tunnel anti-asthma according to the ladder of setting, in this process, if open the quick valve in the bypass of wind-tunnel anti-asthma when compressor approaches surge, and record compressor rotary speed n1 and stator blade angle β 1 this moment, the volume flow Q 1 of compressor of now flowing through is the pumping point of compressor in the time of rotation speed n 1 and stator blade angle β 1, if there is not yet surge until stator blade angle arrives desired value β 1 compressor, enter step 4;
Step 4: increase compressor stator blade angle β according to the ladder of setting, in this process, if open the quick valve in the bypass of wind-tunnel anti-asthma when compressor approaches surge, and record compressor rotary speed n2 and stator blade angle β 2 this moment, the volume flow Q 2 of compressor of now flowing through is the pumping point of compressor in the time of rotation speed n 2 and stator blade angle β 2, if there is not yet surge until stator blade angle arrives desired value β 2 compressors, the normal operation of compressor enters step 5;
Step 5: reduce the aperture of convection current through the larger motion of the gas flow impact of compressor, reduce compressor gas flow according to the ladder of setting; In this process, if open quick valve in the bypass of wind-tunnel anti-asthma when compressor approaches surge, motion returned to original position, and record compressor rotary speed n3 and stator blade angle β 3 this moment, the volume flow Q 3 of compressor of now flowing through is the pumping point of compressor in the time of rotation speed n 3 and stator blade angle β 3, if there is not yet surge until motion closes to smallest compressor, illustrate that wind-tunnel can move arbitrarily for 3 times at compressor rotary speed n3 and stator blade angle β;
Step 6: all pumping points that obtain in step 3, step 4 and step 5 are linked to be to line, obtain the stall margin of compressor in the time of rotating speed of target n.
2. continous way transonic wind tunnel stall margin assay method according to claim 1, it is characterized in that: the basis for estimation that approaches surge of described compressor is: the amplitude of pressure fluctuation of compressor air-discharging is greater than 15% of normal value, or compressor shaft vibration amplitude is greater than 1.5 times of normal runtime value.
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| CN104728151A (en) * | 2015-04-09 | 2015-06-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Axial flow compressor surge boundary measurement system |
| CN107559230A (en) * | 2017-09-19 | 2018-01-09 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of wind-tunnel Silence Process axial flow compressor surge preventing system using interpolation arithmetic |
| CN112128133A (en) * | 2020-11-25 | 2020-12-25 | 中国航发上海商用航空发动机制造有限责任公司 | Opening margin measurement test method for adjustable stationary blade of high-pressure gas compressor |
| CN114166459A (en) * | 2022-02-11 | 2022-03-11 | 中国空气动力研究与发展中心计算空气动力研究所 | Wind tunnel group medium-voltage scheduling method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104728151A (en) * | 2015-04-09 | 2015-06-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Axial flow compressor surge boundary measurement system |
| CN107559230A (en) * | 2017-09-19 | 2018-01-09 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of wind-tunnel Silence Process axial flow compressor surge preventing system using interpolation arithmetic |
| CN107559230B (en) * | 2017-09-19 | 2019-03-29 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of wind-tunnel Silence Process axial flow compressor surge preventing system using interpolation arithmetic |
| CN112128133A (en) * | 2020-11-25 | 2020-12-25 | 中国航发上海商用航空发动机制造有限责任公司 | Opening margin measurement test method for adjustable stationary blade of high-pressure gas compressor |
| CN112128133B (en) * | 2020-11-25 | 2021-02-02 | 中国航发上海商用航空发动机制造有限责任公司 | Opening margin measurement test method for adjustable stationary blade of high-pressure gas compressor |
| CN114166459A (en) * | 2022-02-11 | 2022-03-11 | 中国空气动力研究与发展中心计算空气动力研究所 | Wind tunnel group medium-voltage scheduling method |
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Application publication date: 20140611 |