CN103967843A - Air compressor peripheral groove self-circulating and jetting combined stability extension device and method - Google Patents
Air compressor peripheral groove self-circulating and jetting combined stability extension device and method Download PDFInfo
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Abstract
The invention discloses an air compressor peripheral groove self-circulating and jetting combined stability extension device and method. The air compressor peripheral groove self-circulating and jetting combined stability extension device comprises a blade top casing, multiple peripheral grooves with a certain width-depth ratio, multiple through holes, multiple holes, a self-circulating mechanism, and a nozzle, the peripheral grooves are formed at the top end of an inner-wall movable blade of the blade top casing, the through holes are formed on the casing wall face at the movable blade front edge and the movable blade top end and fixedly connected with the peripheral grooves in a sealed manner, the holes are formed at the bottoms of the peripheral grooves, the self-circulating mechanism is formed by connecting the through holes at the movable blade front edge and the movable blade top end, the nozzle is connected to the self-circulating mechanism and performs air injection at the movable bade front edge, and the through holes formed on the casing wall face of the movable blade front edge are fixedly connected with the nozzle in a sealed manner. By the air compressor peripheral groove self-circulating and jetting combined stability extension device and method, stability extension capability of the peripheral grooves and blade top air injection can be fully utilized to achieve the objective of improving stall margin, and an axial flow fan or an air compressor can run under the working conditions of high pressure ratio and wide stall margin.
Description
Technical field
The present invention relates to gas turbine technology field, the jet combined type of especially a kind of gas compressor circumferential groove self-loopa expands stabilization device and method.
Background technique
Gas compressor is as a kind of fluid machinery of extensive use, and how to improve its working stability is study hotspot and difficult point always.In the world the steady measure of expansion that improves engine sta bility margin is carried out to various explorations, mainly comprised adjustable vane, casing processing (peripheral groove and axial slit), leaf top spray gas, big and small blade etc.Leaf top spray gas and casing are processed as effectively expanding steady measure and have been subject in the world paying close attention to widely, and it are expanded to steady mechanism and carried out relevant numerical value and experimental research.
Leaf top spray gas method as far back as last century early seventies just by people are attempted.At that time, the blade suction surface flow separation that Emmons proposes can cause the viewpoint of stall to obtain the accreditation of Most scholars in the world, and some scholars have also proposed to want to postpone stall on this basis, first will suppress blade surface flow separation.Therefore, the method for many inhibition separated flows is arisen at the historic moment, and leaf top spray gas is exactly one of them, and researchers think jet can take away the obstruction group causing because separating, thereby reduces to separate.Koch and Smith have carried out " spray-suction " gas and have expanded steady trial on a transonic compressor, have obtained good effect.Last century 80, people made much progress to the mechanism understanding of gas compressor flow unstable to middle nineteen nineties, had greatly inspired many researchers to remove to seek more advanced effectively stability enhancement method from the discovery that is established to two class stall tendencys of M-G model.
The Day of Cambridge University thinks that leaf top spray gas can suppress the initial of stall tendency, and on multi stage axial flow compressor Laboratory Furniture, adopt the jet method of active successfully to postpone the generation of rotating stall and surge, and jet amount used is less than 1% of gas compressor design discharge, but make the unstability nargin of gas compressor increase by 4%.The people such as the Weigl of MIT think the jet development that can produce feedback control ripple and come disturbance suppression, and study nozzle arrangements to the impact across sound Stability of Axial compressors on initiatively jet basis, the jet amount that adopts is 5.8% of gas compressor design discharge, adopt leaf top spray gas under 70% rotating speed and 100% speed conditions time, make the stable operation range of gas compressor widen respectively 11% and 3.5%, make gas compressor design discharge improve 3.6% simultaneously.Subsequently, the people such as Spakovszky adopt initiatively jet controlling method to carry out experimental research equally on across sound axial flow compressor, in experiment, detect that by high frequency sound dynamic pickup long yardstick disturbance is as feedback signal, control strategy adopts respectively permanent and non-permanent jet means.
Active based on ACTIVE CONTROL theory is jet, and it is also very complicated that it realizes mechanism, therefore in the time of practical application, is also greatly limited.Therefore, along with to ACTIVE CONTROL theory advantage and not enough self-examination, initiatively jet beginning again returns to early stage passive jet.The discrete jet result of stable state that the people such as the Suder of NASA obtained in 2000, its result of study shows: in the time that rotating speed of gas compressor is 70% design speed, the jet amount of 1% main flow flow can make the unstability border maximum of gas compressor move to left nearly 30%; In the time that gas compressor moves with 100% rotating speed, the jet amount of 1.3% main flow flow can make the unstability border maximum of gas compressor move to left 3.5%.The people such as Greece scholar Kefalakis in 2006 have studied that stable state is jet and pulsation (non-permanent) is jet on improving impact of axial flow compressor surge margin.Utilize first jet trial to disturb beginning to compression system flow field by early stage Day, gas jet technique is paid attention to by each research institution.But in the interception that the research of Day is only confined to unstability to produce, do not set forth and how to realize can large flow flow field comparatively speaking being produced and be intervened compared with the jet means of small flow.
In recent years, the research work that micro-gas jet technique pushed up at leaf in Institute of Engineering Thernophysics, Academia Sinica also obtains the understanding of some valuable experimental results and theoretical side.The people such as Nie Chaoqun have carried out experimental research to gas compressor near-stalled condition, use the analytical method of dynamic measuring tech and UNSTEADY FLOW, and improve on this basis nozzle structure, on three grades of axial flow compressors of low speed, test and in conjunction with follow-up numerical calculation processing, as follows from experiment and two angle analysis conclusions of numerical simulation: micro-jet major effect region is in blade tip top area, and casing inwall is got in influence area, expand steady effect better; Leaf top micro-jet in fact active be jet exit momentum, instead of jet mass flow rate; Processing result to wall Dynamic Signal shows: jet meeting exerts an influence to top Unsteady Flow feature; Increase along with expanding steady effect, jet caused impact also becomes more obvious.
Within 2006, Tong Zhi front yard combines the research of micro-jet control technique and rotating stall instability Mechanism, and successively carry out experimental research at subsonics and high subsonics single rotor axial flow compressor, experimental result shows: take micro-discharge rate jet (be less than main flow flow 0.1%) to exert an influence to the stability characteristic (quality) of gas compressor, possess the ability of gas compressor stable operation zone being widened to certain limit.Subsequently, wall dynamic pressure signal is analyzed, and successfully wavelet analysis means are incorporated in unsteady flow field analysis, proved internal flow and there is significantly non-permanent mechanism.Geng Shaojuan studies the corresponding physical phenomenon of non-permanent mechanism by numerical simulation; find micro-jet actual steady effect of opening up that has; with the be associated number of the micro-jet singular point that can suppress the microvariations that flow field is inner relevant to flow unstable tendency in visible leaf top of wavelet analysis result in this institute early stage; and can make blade tip clearance leakage vortex to the movement of blade middle part, in great role, stop leaf top leakage vortex to be overflowed by blade tip and crossed whole blade path to form the possible of stall.In a word, leaf top spray gas expands the focus that steady control technique is research in the world always, by optimizing nozzle geometry structure, and jet position, the stable operation range of jet yaw angle etc. are verified leaf top spray gas can widen to a great extent gas compressor.
And casing is processed as the steady measure of another effective passive expansion, come across the sixties in last century, simple in structure because of it, be easy to repacking, expand surely respond wellly, obtain widely research and applied.The Hathaway of NASA has summed up a series of typical casing processing modes, and has pointed out that peripheral groove and axial slit are the casing processing modes of two quasi-representatives.Although the steady effect of the expansion of peripheral groove is not as seam class, little because of its impact on efficiency, this makes size design and the layout of researchers to peripheral groove carry out large quantity research.Most research thinks that the inflow of peripheral groove inner fluid and outflow can affect leaf top leakage flow and delay it and overflows, and thinks and flows and changed the track of leaf top leakage flow in groove as the research team of Northwestern Polytechnical University, makes it more be close to blade suction surface.The people such as Wilke think that thereby fragmentation that peripheral groove can delay blade tip clearance leakage vortex reaches expands steady object.The people such as German scholar Muller have similar view to this, think that peripheral groove can also weaken obstruction simultaneously.
These researchs are based upon on multiple-grooved basis more, and think and expand surely effective near the groove of movable vane leading edge.The people such as the Ivor Day of Cambridge University expand steady effect to the research discovery 50% axial chord length position of circumferential single groove and still have a peak value.The circumferential single groove experiment of Institute of Engineering Thernophysics, Academia Sinica on lower velocity shaft flow air compressor also finds that the single groove in the axial chord length of 40%-70% position also has the steady effect of better expansion.These all show that blade mid-rear portion groove still has the steady effect of better expansion, and this provides certain design criterion also to the practical application of peripheral groove.
Because the groove of blade mid-rear portion is smaller on the impact of blade front end leakage flow, the leakage vortex of major effect rear end, and generally acknowledge in the world at present one of two kinds of main stall approach: leakage flow and main flow interface leading edge are overflowed and can be brought out prominent sharp type stall tendency, and then cause stall.Like this, when near stalling point, push ahead although peripheral groove can weaken rear end leakage flow to a certain extent, cannot stop the variation of front end leakage flow track, so also just limited it and expanded steady ability.And according to analyzing above, leaf top spray gas can act on the leakage flow track of blade inlet edge and the intensity of inhibition leakage vortex realizes expansion surely.
Therefore, if can, effectively in conjunction with the effect of leaf top spray gas and peripheral groove, just can realize the steady object of dual expansion.
Summary of the invention
(1) technical problem that will solve
In view of this, the object of the invention is, for the jet combined type of open a kind of gas compressor circumferential groove self-loopa expands stabilization device and method, to realize the steady ability of expansion of utilizing peripheral groove and leaf top spray gas simultaneously, to widen to greatest extent gas compressor flow unstable nargin.
(2) technological scheme
For achieving the above object, the invention provides the jet combined type of a kind of gas compressor circumferential groove self-loopa and expand stabilization device, this device comprises: a leaf top casing; Multiple peripheral grooves with certain breadth depth ratio of opening on the inwall movable vane top of this leaf top casing; Multiple through holes of opening respectively on the casing wall on movable vane leading edge and movable vane top, the through hole of opening on the casing wall of movable vane top and the sealing of this peripheral groove are affixed; Multiple holes of opening at the bottom land of this peripheral groove; The self-loopa mechanism that connects movable vane leading edge and the multiple through holes in movable vane top and form; And be connected in this self-loopa mechanism and carry out jet nozzle in movable vane leading edge, through hole and this sealed nozzle opened at the casing wall of this movable vane leading edge are affixed.
For achieving the above object, the present invention also provides the self-loopa of a kind of gas compressor circumferential groove jet combined type stability enhancement method, the method is under the promotion of front and back differential static pressure, the gas of movable vane top peripheral groove bottom land is drawn through self-loopa mechanism, and spray through nozzle at movable vane leading edge casing inwall, realize the object that improves engine sta bility margin.
(3) beneficial effect
The jet combined type of peripheral groove self-loopa of the present invention expands stabilization device, and advantage is:
1, two kinds of leaf top spray gas and peripheral grooves are expanded to steady mode and combine, nozzle can just utilize the gas of drawing at the bottom of peripheral groove, sprays at movable vane leading edge casing inwall, makes full use of the steady effect of dual expansion of leaf top spray gas and peripheral groove, reaches and expands steady object.
2, peripheral groove expands steady time, can form a large amount of whirlpools at bottom land, will certainly affect to some extent compressor efficiency, and adopt self-loopa mechanism the gas of bottom land can be drawn, and reduces the impact on efficiency.
3, self-loopa mechanism adopts pipe and nozzle and groove to carry out seamless link, ensures as far as possible pipe loss minimum.
Brief description of the drawings
Fig. 1 is the flow schematic diagram in peripheral groove while not adopting the jet mechanism of self-loopa;
Fig. 2 is the structural representation that the jet combined type of gas compressor circumferential groove provided by the invention self-loopa expands stabilization device;
Fig. 3 is the jet structural representation of circumferential multiple-grooved self-loopa.
Embodiment
For making the object, technical solutions and advantages of the present invention clearer, below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in more detail.
The invention provides the jet combined type of a kind of gas compressor circumferential groove self-loopa and expand stabilization device and method, adopt self-circulation mode, the gas of compressor casing wall peripheral groove bottom land is drawn and gets back to movable vane leading edge and carry out jet.This device and method can make full use of the steady ability of expansion of peripheral groove and leaf top spray gas, reaches the object of improving stall margin, makes the axial flow compressor can be at high pressure ratio, under the operating mode of wide stall margin, moves.
As shown in Figure 1 to Figure 3, the jet combined type of this gas compressor circumferential groove provided by the invention self-loopa expands stabilization device, comprising: a leaf top casing; Multiple peripheral grooves with certain breadth depth ratio of opening on the inwall movable vane top of this leaf top casing; Multiple through holes of opening respectively on the casing wall on movable vane leading edge and movable vane top, the through hole of opening on the casing wall of movable vane top and the sealing of this peripheral groove are affixed; Multiple holes of opening at the bottom land of this peripheral groove; The self-loopa mechanism that connects movable vane leading edge and the multiple through holes in movable vane top and form; And be connected in this self-loopa mechanism and carry out jet nozzle in movable vane leading edge, through hole and this sealed nozzle opened at the casing wall of this movable vane leading edge are affixed.
Wherein, described self-loopa mechanism is made up of one section of pipe, the attachment portion that pipe and nozzle and peripheral groove are affixed, ensure inwall smooth transition and the seamless link as far as possible of round tube inner wall and attachment portion, to ensure that air-flow is when the Flow In A Circular Tube, sealing performance is good, and loses little.Described self-loopa mechanism draws the gas of bottom land and gets back to movable vane leading edge casing inwall and spray in gas compressor running, in the time of gas compressor variable parameter operation, the pressure on movable vane top can with throttle valve close and gradually raise, and make jet amount become gradually large, and then can make full use of the steady ability of expansion of peripheral groove and leaf top spray gas, reach the steady object of dual expansion.
Described peripheral groove is for being drawn into the high pressure draught of blade pressure surface in peripheral groove, then spray at blade suction surface, blade tip clearance leakage vortex is passed in passage, suppress the intensity of leaf top leakage vortex, further postpone the reach of leakage flow and main flow interface, realize the generation of postponing stall.Described peripheral groove, for the gas of vane tip pressure side is sucked, then sprays at vane tip suction surface; Because suction-jet stream has only been contained the partial depth of peripheral groove, can form a large amount of whirlpools at bottom land, will cause like this entropy of bottom land to increase larger, the efficiency of whole gas compressor will decline, and self-loopa mechanism can draw the vortex system structure of bottom land, under the promotion of pressure reduction, the formation that wall nozzle is sentenced momentum in movable vane leading edge casing is sprayed.
For peripheral groove, due to the axial fan/gas compressor for different, structure and the axial position of optimum groove are different.Through different compressor rotors being tested and numerical value research, when the depth-to-width ratio of groove is 1-2, it is little to the negative effect of compressor efficiency in reaching the steady effect of certain expansion; And when peripheral groove be centered close to apart from the axial chord length of blade inlet edge 40%-70% position time, the steady effect of expansion of peripheral groove is best.On this basis, select structure and the position of groove.。
Nozzle can flow as much as possible the air-flow ejecting after interacting with main flow along casing wall, gas jet can act on blade tip clearance stream like this, play and suppress leakage vortex intensity, increase the axial momentum of main flow, the interface of leakage flow and main flow is passed to passage trailing edge, realized the generation of postponing stall.
For nozzle, early stage is according to a large amount of experimental research of leaf top spray gas and numerical value are studied, the structure of nozzle has also been carried out to corresponding optimization, and while thinking radially jet angle as far as possible little (15 °), jet exit air-flow is substantially pasting casing wall and is flowing, and consider the convenience that nozzle is processed, the radially jet angle of the nozzle of choosing is 15 °.In addition, jet yaw angle is negative angle (contrary with compressor rotor sense of rotation), when jet expansion is 2mm apart from movable vane blade tip, to inhibition the best of blade tip clearance leakage flow.
The jet combined type of gas compressor circumferential groove self-loopa based on shown in Fig. 1 to Fig. 3 expands stabilization device, the present invention also provides the self-loopa of a kind of gas compressor circumferential groove jet combined type stability enhancement method, the method is under the promotion of front and back differential static pressure, the gas of movable vane top peripheral groove bottom land is drawn through self-loopa mechanism, and spray through nozzle at movable vane leading edge casing inwall, realize the object that improves engine sta bility margin.
Wherein, described self-loopa mechanism draws the gas of bottom land and gets back to movable vane top and spray in gas compressor running; In the time of gas compressor variable parameter operation, the pressure of movable vane leading edge casing inwall can, with the closing and raise gradually of throttle valve, and become greatly jet amount, and then can make full use of the steady ability of expansion of peripheral groove and leaf top spray gas gradually, reaches the steady object of dual expansion.
Described peripheral groove is drawn into the high pressure draught of blade pressure surface in peripheral groove, then spray at blade suction surface, blade tip clearance leakage vortex is advanced in passage, suppress the intensity of leaf top leakage vortex, further postpone the reach of leakage flow and main flow interface, realize the generation of postponing stall.Described peripheral groove sucks the gas of vane tip pressure side, then sprays at vane tip suction surface; Because suction-jet stream has only been contained the partial depth of peripheral groove, can form a large amount of whirlpools at bottom land, will cause like this entropy of bottom land to increase larger, the efficiency of whole gas compressor will decline, and self-loopa mechanism can draw the vortex system structure of bottom land, under the promotion of pressure reduction, the formation that wall nozzle is sentenced momentum in movable vane leading edge casing is sprayed.
Described nozzle can flow as much as possible the air-flow ejecting after interacting with main flow along casing wall, gas jet can act on blade tip clearance stream like this, play and suppress leakage vortex intensity, increase the axial momentum of main flow, the interface of leakage flow and main flow is passed to passage trailing edge, realized the generation of postponing stall.
In the time of design self-loopa mechanism, should ensure the effect of peripheral groove, air-flow vortex system structure unnecessary in groove can be drawn again; In addition, because can drawing, air-flow gets back to the impetus that movable vane leading edge is dependence peripheral groove position, Ye Ding region axial position differential static pressures different from movable vane import completely.Therefore,, in the time of design self-loopa mechanism, reduce as much as possible friction loss.
When peripheral groove, first circumferential single groove is carried out to experimental research and numerical calculation in design, result of study shows that it expands steady effect and compares better when groove is during in the position apart from the axial chord length of movable vane leading edge 40%-70%.Therefore in the time of the circumferential single groove of processing, first process light wall casing, then the peripheral groove that the position of the axial chord length of span movable vane blade tip leading edge 40%-70% processing depth-to-width ratio is 1-2 in casing, as shown in Figure 1, in the time carrying out number crunching, find that groove plays the effect of suction-spray: the pressurized gas of pressure side are drawn in groove, then spray at suction surface.And the air-flow that expands steady effectively inhale-spray has only been occupied to a part for groove depth, and can form a large amount of vortex system structures at bottom land, it is strong that complicated vortex system structure exacerbates the entropy of bottom land, has a strong impact on compressor efficiency.
And if the air-flow that bottom land produces whirlpool is drawn, the entropy that will reduce like this bottom land increases, and contributes to the lifting of efficiency.Also can find out from Fig. 2, when in bottom land perforate, adopt after bindiny mechanism and self-loopa mechanism carry out seamless link, the gas of bottom land be drawn to the nozzle place of getting back to movable vane leading edge, spray via nozzle.Schematic diagram from figure can be found out, the flow field of the air-flow major effect blade tip leading edge that nozzle ejection goes out, and the flow field of peripheral groove major effect rear end.So just can make full use of suction-spray effect and the leaf top spray gas jet effect of peripheral groove, realize the steady object of dual expansion of axial fan/gas compressor.
In practical application, in the time carrying out multiple-grooved design, consider the Combinatorial Optimization of multiple-grooved, therefore with numerical calculation, the steady ability of expansion of multiple-grooved combination is optimized first by experiment.Then in the bottom land perforate of multiple-grooved, adopt equally self-loopa mechanism to draw to get back to movable vane blade tip leading edge and spray.As shown in Figure 3, so just can make full use of the steady ability of comprehensive expansion of circumferential multiple-grooved and leaf top spray gas, at utmost realize and expand steady object.
Above-described specific embodiment; object of the present invention, technological scheme and beneficial effect are further described; institute is understood that; the foregoing is only specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any amendment of making, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (15)
1. the jet combined type of gas compressor circumferential groove self-loopa expands a stabilization device, it is characterized in that, this device comprises:
One leaf top casing;
Multiple peripheral grooves with certain breadth depth ratio of opening on the inwall movable vane top of this leaf top casing;
Multiple through holes of opening respectively on the casing wall on movable vane leading edge and movable vane top, the through hole of opening on the casing wall of movable vane top and the sealing of this peripheral groove are affixed;
Multiple holes of opening at the bottom land of this peripheral groove;
The self-loopa mechanism that connects movable vane leading edge and the multiple through holes in movable vane top and form; And
Be connected in this self-loopa mechanism and carry out jet nozzle in movable vane leading edge, through hole and this sealed nozzle opened at the casing wall of this movable vane leading edge are affixed.
2. the jet combined type of gas compressor circumferential groove according to claim 1 self-loopa expands stabilization device, it is characterized in that, described self-loopa mechanism is made up of one section of pipe, the attachment portion that pipe and nozzle and peripheral groove are affixed, ensure inwall smooth transition and the seamless link as far as possible of round tube inner wall and attachment portion, to ensure that air-flow is when the Flow In A Circular Tube, sealing performance is good, and loses little.
3. the jet combined type of gas compressor circumferential groove according to claim 2 self-loopa expands stabilization device, it is characterized in that, described self-loopa mechanism draws the gas of bottom land and gets back to movable vane leading edge casing inwall and spray in gas compressor running, in the time of gas compressor variable parameter operation, the pressure on movable vane top can with throttle valve close and gradually raise, and jet amount is become greatly gradually, and then can make full use of the steady ability of expansion of peripheral groove and leaf top spray gas, reach the steady object of dual expansion.
4. the jet combined type of gas compressor circumferential groove according to claim 1 self-loopa expands stabilization device, it is characterized in that, described peripheral groove is for being drawn into the high pressure draught of blade pressure surface in peripheral groove, then spray at blade suction surface, blade tip clearance leakage vortex is passed in passage, suppress the intensity of leaf top leakage vortex, further postpone the reach of leakage flow and main flow interface, realize the generation of postponing stall.
5. the jet combined type of gas compressor circumferential groove according to claim 1 self-loopa expands stabilization device, it is characterized in that, described peripheral groove, for the gas of vane tip pressure side is sucked, then sprays at vane tip suction surface; Because suction-jet stream has only been contained the partial depth of peripheral groove, can form a large amount of whirlpools at bottom land, will cause like this entropy of bottom land to increase larger, the efficiency of whole gas compressor will decline, and self-loopa mechanism can draw the vortex system structure of bottom land, under the promotion of pressure reduction, the formation that wall nozzle is sentenced momentum in movable vane leading edge casing is sprayed.
6. the jet combined type of gas compressor circumferential groove according to claim 1 self-loopa expands stabilization device, it is characterized in that, the depth-to-width ratio of described peripheral groove is 1-2.
7. the jet combined type of gas compressor circumferential groove according to claim 1 self-loopa expands stabilization device, it is characterized in that being centered close to apart from the axial chord length of blade inlet edge 40%-70% position of described peripheral groove.
8. the jet combined type of gas compressor circumferential groove according to claim 1 self-loopa expands stabilization device, it is characterized in that, described nozzle can flow as much as possible the air-flow ejecting after interacting with main flow along casing wall, gas jet can act on blade tip clearance stream like this, play and suppress leakage vortex intensity, increase the axial momentum of main flow, the interface of leakage flow and main flow is passed to passage trailing edge, realize the generation of postponing stall.
9. the jet combined type of gas compressor circumferential groove according to claim 8 self-loopa expands stabilization device, it is characterized in that, the radially jet angle of described nozzle is 15 °.
10. the jet combined type of gas compressor circumferential groove according to claim 8 self-loopa expands stabilization device, it is characterized in that, the jet yaw angle of described nozzle is negative angle, contrary with compressor rotor sense of rotation, and jet expansion is 2mm apart from movable vane blade tip.
The jet combined type stability enhancement method of 11. 1 kinds of gas compressor circumferential grooves self-loopa, the device of the method based on described in any one in claim 1 to 10, it is characterized in that, the method is under the promotion of front and back differential static pressure, the gas of movable vane top peripheral groove bottom land is drawn through self-loopa mechanism, and spray through nozzle at movable vane leading edge casing inwall, realize the object that improves engine sta bility margin.
The jet combined type stability enhancement method of 12. gas compressor circumferential groove according to claim 11 self-loopa, is characterized in that, described self-loopa mechanism draws the gas of bottom land and gets back to movable vane leading edge casing inwall and spray in gas compressor running; In the time of gas compressor variable parameter operation, the pressure on movable vane top can, with the closing and raise gradually of throttle valve, and become greatly jet amount, and then can make full use of the steady ability of expansion of peripheral groove and leaf top spray gas gradually, reaches the steady object of dual expansion.
The jet combined type stability enhancement method of 13. gas compressor circumferential groove according to claim 11 self-loopa, it is characterized in that, described peripheral groove is drawn into the high pressure draught of blade pressure surface in peripheral groove, then spray at blade suction surface, blade tip clearance leakage vortex is advanced in passage, suppress the intensity of leaf top leakage vortex, further postpone the reach of leakage flow and main flow interface, realize the generation of postponing stall.
The jet combined type stability enhancement method of 14. gas compressor circumferential groove according to claim 11 self-loopa, is characterized in that, described peripheral groove sucks the gas of vane tip pressure side, then sprays at vane tip suction surface; Because suction-jet stream has only been contained the partial depth of peripheral groove, can form a large amount of whirlpools at bottom land, will cause like this entropy of bottom land to increase larger, the efficiency of whole gas compressor will decline, and self-loopa mechanism can draw the vortex system structure of bottom land, under the promotion of pressure reduction, the formation that wall nozzle is sentenced momentum in movable vane leading edge casing is sprayed.
The jet combined type stability enhancement method of 15. gas compressor circumferential groove according to claim 11 self-loopa, it is characterized in that, described nozzle can flow as much as possible the air-flow ejecting after interacting with main flow along casing wall, gas jet can act on blade tip clearance stream like this, play and suppress leakage vortex intensity, increase the axial momentum of main flow, the interface of leakage flow and main flow is passed to passage trailing edge, realize the generation of postponing stall.
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| CN110145497A (en) * | 2019-05-09 | 2019-08-20 | 西北工业大学 | A kind of compressor self-loopa treated casing expansion stabilization device of axial advancement |
| CN112177981A (en) * | 2020-09-27 | 2021-01-05 | 西北工业大学 | Novel radial and axial inclined self-circulation treatment casing and design method |
| CN112412885A (en) * | 2020-05-09 | 2021-02-26 | 北京理工大学 | Adjustable self-circulation air injection stability expansion structure and centrifugal compressor with stability expansion structure |
| CN114526263A (en) * | 2022-02-17 | 2022-05-24 | 集美大学 | Self-adaptive casing processing device of axial flow compressor and design method thereof |
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