CN102606502A - Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas - Google Patents
Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas Download PDFInfo
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- CN102606502A CN102606502A CN2012100370071A CN201210037007A CN102606502A CN 102606502 A CN102606502 A CN 102606502A CN 2012100370071 A CN2012100370071 A CN 2012100370071A CN 201210037007 A CN201210037007 A CN 201210037007A CN 102606502 A CN102606502 A CN 102606502A
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Abstract
The invention relates to a method for exciting and controlling gas flow of the stator blade end wall of an axial-flow compressor by the aid of plasmas, which is characterized by including the steps: laying a plasma pneumatic exciter on the stator blade passage end wall of the axial-flow compressor, wherein the front edge and the tail edge of an electrode of the plasma pneumatic exciter are level to the front edge and the tail edge of a stator blade respectively, and the direction of the electrode is parallel to a mean camber line of the stator blade; when an engine controller detects flow instability indication, loading electric signals to the electrode of the plasma pneumatic exciter by employing a pulse plasma power source; and when the engine controller detects disappearance of flow instability indication, sending out control signals, and closing the plasma pneumatic exciter. The control method is capable of effectively suppressing stator blade angle area flow separation of the axial-flow compressor, short in exciting response time and wide in bandwidth, and has an important role in reduction of stator blade wake pitot loss and improvement on stability and efficiency of the compressor.
Description
Technical field
The invention belongs to the active Flow Control technology in gas turbine engine field, relate to a kind of method of utilizing plasma excitation Control Shaft flow air compressor stator blade end wall gas flow, and the plasma pneumatic actuators that is used for this method.
Background technique
Axial flow compressor is one of core component of aviation gas turbine Duct-Burning Turbofan, and its development trend is higher pressure ratio, efficient and stability, progression still less.Because the strong pressure gradient of flow direction and the boundary layer lateral flow in the blade path, low energy fluid is gathered in stator blade suction surface/end wall angular region, and then forms significant angular region flow separation.The angular region is separated one side and is limited the raising that gas compressor is loaded and static pressure rises ability, causes the decline of compressor efficiency and stall margin on the other hand, and gives the interstage matched deleterious impact of multiatage axial flow compressor.Therefore, separate the angular region is one of key factor of restriction gas compressor pressure ratio, efficient and stability lifting, how to suppress the angular region and separate, and be challenging key issue in the design of high-performance gas compressor.
Passive flow control methods such as blade is curved plunders, end wall wing fence, can under typical operating conditions, effectively suppress the angular region separates, still, and because the working state excursion of gas compressor is wide, the very difficult adaptation of these methods different working condition.Adopting the active Flow Control method is an important development trend, and will be blended in the pneumatic design of gas compressor as a new degrees of freedom.Boundary layer blows/inhales is a kind of typical active Flow Control energisation mode of present broad research, is suppressing to have obtained good effect aspect the separation of angular region.But, owing to need the air-channel system of more complicated, very difficult generation fast, wide band excitation, will become a major obstacle that limits its development.
Summary of the invention
The technical problem that solves
For fear of the deficiency of existing technology, the present invention proposes a kind of method of utilizing plasma excitation Control Shaft flow air compressor stator blade end wall gas flow, and the plasma pneumatic actuators that is used for this method.Can solve that other flow control meanses can not solve or problem such as the insoluble excitation of control quickly, for realization real-time adaptive FLOW CONTROL provides the good basis condition.
Technological scheme
A kind of method of utilizing plasma excitation Control Shaft flow air compressor stator blade end wall gas flow is characterized in that step is following:
Step 1: lay the plasma pneumatic actuators in axial flow compressor stator blade passage end wall, the leading edge of plasma pneumatic actuators electrode is concordant with trailing edge with the leading edge of stator blade respectively with trailing edge, and the direction of electrode is parallel with the mean camber line of stator blade;
Step 2:, adopt the pulsed plasma power supply electrical signal to be loaded on the electrode of plasma pneumatic actuators when engine controller detects when flowing the unstability tendency; The output voltage waveforms of said electrical signal is sinusoidal wave, and voltage is between 1～30kV, and discharge frequency is between 1～40kHz, and pulse frequency is between 10-1000Hz, and dutycycle is between 1%-100%;
Step 3: when engine controller detects the unstability tendency that flows and disappears, send control signal, close the plasma pneumatic actuators.
A kind of plasma pneumatic actuators that is used for said method is characterized in that comprising upper surface electrode, lower surface electrode and insulating material; It is parallel on insulating material that to be provided with multi-group electrode right; Described electrode pair is on two surfaces of insulating material, to be provided with upper surface electrode and lower surface electrode, has separation delta d between two electrodes; During use, upper surface electrode connects with the pulsed plasma power supply, and lower surface electrode ground connection produces plasma at the upper surface electrode edge.
The thickness h of said upper surface electrode and lower surface electrode
eBe 0.018mm, width is 2mm.
Said insulation thickness h
dBe 0.5mm.
Said separation delta d is 1mm.
Said insulating material is a polyimide.
Said electrode material is a Copper Foil.
Beneficial effect
A kind of method of utilizing plasma excitation Control Shaft flow air compressor stator blade end wall gas flow that the present invention proposes, and the plasma pneumatic actuators that is used for this method.Plasma flow control is based on a kind of novel active Flow Control method of plasma air-operated drive; Utilize gaseous discharge to produce the controlled disturbance that stream field applies in the process of plasma; Change the speed and the vorticity boundary conditions in flow field; And then the realization FLOW CONTROL, suppressing to have remarkable technical advantage aspect the separation of angular region.
The controlling method that the present invention proposes can effectively suppress axial flow compressor stator blade angular region flow separation, and the exciter response time is short, Bandwidth, for reducing stator blade tail pitot loss, improves gas compressor stability and efficient and has important function.Tunnel test shows that end wall plasma air-operated drive can effectively suppress NACA 0065 compressor blade row angular region flow separation under the condition of speed of incoming flow 90m/s, with the maximum reduction by 13% of the blade wake passing pitot loss of 70% leaf eminence.The major advantage of this method is that excitation frequency band is wide, effect rapidly, do not have moving element, simple in structure, energy consumption is lower.
Description of drawings
Fig. 1: be the conceptual scheme that plasma air-operated drive electrode is arranged on axial flow compressor stator blade end wall;
The 1-blade inlet edge, 2-blade trailing edge, 3-end wall, 4-plasma excitation device, 5-plasma excitation device;
Fig. 2: the layout chart that is plasma air-operated drive electrode;
The 6-upper surface electrode, 7-lower surface electrode, 8-insulating material, A-plasma;
Fig. 3: the output waveform figure that is the pulsed plasma power supply;
Fig. 4: be the installation photo of compressor blade row on the tunnel test platform.
Embodiment
Combine embodiment, accompanying drawing that the present invention is further described at present:
Step 1: lay the plasma pneumatic actuators in axial flow compressor stator blade passage end wall, like the stator blade end wall position that marks among Fig. 1.The leading edge of plasma pneumatic actuators electrode is concordant with trailing edge with the leading edge of stator blade respectively with trailing edge, and the direction of electrode is parallel with the mean camber line of stator blade;
The electrodes use copper electrode of said plasma air-operated drive electrode separates with insulating material between electrode, and insulating material is a polyimide.The layout of plasma air-operated drive electrode is as shown in Figure 2, upper surface electrode width d
1Be 2mm, lower surface electrode width d
2Be 2mm, upper and lower surface electrode separation delta d is 1mm, upper and lower surface electrode thickness h
eBe 0.018mm, insulation thickness h
dBe 0.5mm.
The two ends of plasma air-operated drive electrode are respectively at linking to each other with grounding end with the high voltage terminal of pulsed plasma power supply.
Step 2:, adopt the pulsed plasma power supply electrical signal to be loaded on the electrode of plasma pneumatic actuators when engine controller detects when flowing the unstability tendency; The output voltage waveforms of said electrical signal is sinusoidal wave, and voltage is between 1～30kV, and discharge frequency is between 1～40kHz, and is as shown in Figure 3.Driving pulse repetition frequency f=1/T
Control, f=10～1000Hz; Driving pulse duty cycle alpha=T
Signal/ T
Control* 100%, α=1%～100%.
Step 3: when engine controller detects the unstability tendency that flows and disappears, send control signal, close the plasma pneumatic actuators.
In the present embodiment, in the compressor blade row wind-tunnel quantitative appraisal pulsed plasma air-operated drive suppress the effect that separate the angular region, as shown in Figure 4.Under the condition of speed of incoming flow 90m/s; (energizing voltage is 10kV to the pulsed plasma air-operated drive; Pulse frequency is 600Hz, and dutycycle is 70%) effectively suppress NACA 0065 compressor blade row angular region flow separation, with the maximum reduction by 13% of the blade wake passing pitot loss of 70% leaf eminence.
Claims (7)
1. method of utilizing plasma excitation Control Shaft flow air compressor stator blade end wall gas flow is characterized in that step is following:
Step 1: lay the plasma pneumatic actuators in axial flow compressor stator blade passage end wall, the leading edge of plasma pneumatic actuators electrode is concordant with trailing edge with the leading edge of stator blade respectively with trailing edge, and the direction of electrode is parallel with the mean camber line of stator blade;
Step 2:, adopt the pulsed plasma power supply electrical signal to be loaded on the electrode of plasma pneumatic actuators when engine controller detects when flowing the unstability tendency; The output voltage waveforms of said electrical signal is sinusoidal wave, and voltage is between 1～30kV, and discharge frequency is between 1～40kHz, and pulse frequency is between 10-1000Hz, and dutycycle is between 1%-100%;
Step 3: when engine controller detects the unstability tendency that flows and disappears, send control signal, close the plasma pneumatic actuators.
2. a plasma pneumatic actuators that is used for the said method of claim 1 is characterized in that comprising upper surface electrode, lower surface electrode and insulating material; It is parallel on insulating material that to be provided with multi-group electrode right; Described electrode pair is on two surfaces of insulating material, to be provided with upper surface electrode and lower surface electrode, has separation delta d between two electrodes; During use, upper surface electrode connects with the pulsed plasma power supply, and lower surface electrode ground connection produces plasma at the upper surface electrode edge.
3. plasma pneumatic actuators according to claim 2 is characterized in that: the thickness h of said upper surface electrode and lower surface electrode
eBe 0.018mm, width is 2mm.
4. plasma pneumatic actuators according to claim 2 is characterized in that: said insulation thickness h
dBe 0.5mm.
5. plasma pneumatic actuators according to claim 2 is characterized in that: said separation delta d is 1mm.
6. plasma pneumatic actuators according to claim 2 is characterized in that: said insulating material is a polyimide.
7. plasma pneumatic actuators according to claim 2 is characterized in that: said electrode material is a Copper Foil.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100370071A CN102606502A (en) | 2012-02-19 | 2012-02-19 | Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas |
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| CN2012100370071A CN102606502A (en) | 2012-02-19 | 2012-02-19 | Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103352860A (en) * | 2013-07-05 | 2013-10-16 | 北京航空航天大学 | Plasma excitation end wall circumferential direction layout method and device for suppressing compressor stator corner separation |
| CN103807218A (en) * | 2013-09-29 | 2014-05-21 | 北京航空航天大学 | Plasma combined actuation layout method for restraining corner separation of stators of compressors |
| CN108487937A (en) * | 2018-03-15 | 2018-09-04 | 哈尔滨工业大学 | Turbine cascade leaf roof construction with plasma excitation layout |
| CN109460573A (en) * | 2018-09-17 | 2019-03-12 | 中国人民解放军空军工程大学 | A kind of excitation layout optimization method improving plasma excitation flowing controlled efficiency |
| CN111022382A (en) * | 2019-12-05 | 2020-04-17 | 中国人民解放军空军工程大学 | Method and device for regulating and controlling laminar flow blade type shock wave/boundary layer interference of supersonic compressor by using arc discharge plasma exciter |
| CN111050456A (en) * | 2018-10-11 | 2020-04-21 | 中国人民解放军空军工程大学 | Unsteady plasma excitation layout design method for inhibiting stalling of gas compressor |
| CN112576545A (en) * | 2020-12-11 | 2021-03-30 | 武汉第二船舶设计研究所(中国船舶重工集团公司第七一九研究所) | Control system and method for flow separation inside blade cascade of gas compressor |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103352860B (en) * | 2013-07-05 | 2015-07-08 | 北京航空航天大学 | Plasma excitation end wall circumferential direction layout method and device for suppressing compressor stator corner separation |
| CN103352860A (en) * | 2013-07-05 | 2013-10-16 | 北京航空航天大学 | Plasma excitation end wall circumferential direction layout method and device for suppressing compressor stator corner separation |
| CN103807218A (en) * | 2013-09-29 | 2014-05-21 | 北京航空航天大学 | Plasma combined actuation layout method for restraining corner separation of stators of compressors |
| CN103807218B (en) * | 2013-09-29 | 2017-01-11 | 北京航空航天大学 | Plasma combined actuation layout method for restraining corner separation of stators of compressors |
| CN108487937A (en) * | 2018-03-15 | 2018-09-04 | 哈尔滨工业大学 | Turbine cascade leaf roof construction with plasma excitation layout |
| CN109460573B (en) * | 2018-09-17 | 2022-09-20 | 中国人民解放军空军工程大学 | Excitation layout optimization method for improving plasma excitation flow control efficiency |
| CN109460573A (en) * | 2018-09-17 | 2019-03-12 | 中国人民解放军空军工程大学 | A kind of excitation layout optimization method improving plasma excitation flowing controlled efficiency |
| CN111050456A (en) * | 2018-10-11 | 2020-04-21 | 中国人民解放军空军工程大学 | Unsteady plasma excitation layout design method for inhibiting stalling of gas compressor |
| CN111050456B (en) * | 2018-10-11 | 2023-05-30 | 中国人民解放军空军工程大学 | Unsteady plasma excitation layout design method for inhibiting compressor stall |
| CN111022382A (en) * | 2019-12-05 | 2020-04-17 | 中国人民解放军空军工程大学 | Method and device for regulating and controlling laminar flow blade type shock wave/boundary layer interference of supersonic compressor by using arc discharge plasma exciter |
| CN111022382B (en) * | 2019-12-05 | 2020-11-27 | 中国人民解放军空军工程大学 | Method and device for regulating and controlling laminar flow blade type shock wave/boundary layer interference of supersonic compressor by using arc discharge plasma exciter |
| CN112576545A (en) * | 2020-12-11 | 2021-03-30 | 武汉第二船舶设计研究所(中国船舶重工集团公司第七一九研究所) | Control system and method for flow separation inside blade cascade of gas compressor |
| CN112576545B (en) * | 2020-12-11 | 2023-03-14 | 武汉第二船舶设计研究所(中国船舶重工集团公司第七一九研究所) | Control system and method for flow separation inside blade cascade of gas compressor |
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Application publication date: 20120725 |