CN112576545B - Control system and method for flow separation inside blade cascade of gas compressor - Google Patents

Control system and method for flow separation inside blade cascade of gas compressor Download PDF

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CN112576545B
CN112576545B CN202011463656.9A CN202011463656A CN112576545B CN 112576545 B CN112576545 B CN 112576545B CN 202011463656 A CN202011463656 A CN 202011463656A CN 112576545 B CN112576545 B CN 112576545B
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compressor
plasma
flow separation
cascade
plasma exciter
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CN112576545A (en
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陈聪
郑开元
赵宏博
许平飞
姚露
李俊益
陈先兵
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Wuhan No 2 Ship Design Institute No 719 Research Institute of China Shipbuilding Industry Corp
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Wuhan No 2 Ship Design Institute No 719 Research Institute of China Shipbuilding Industry Corp
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
    • H05H1/00—Generating plasma; Handling plasma
    • H05H1/24—Generating plasma
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Spectroscopy & Molecular Physics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a control system for flow separation in a blade cascade of an air compressor, which comprises: at least one compressor blade; a plasma exciter at a leading edge of the compressor blade inlet for generating an induced vortex when the plasma exciter is turned on. And a method for controlling flow separation inside a compressor cascade, comprising: arranging static pressure measuring points on the surface of the engine to measure whether suction surface flow separation occurs or not; if suction surface flow separation occurs, a plasma exciter located at the leading edge of the compressor blade inlet is activated to generate an induced vortex. The invention replaces a vortex generator with the plasma exciter to generate induced vortex to control the flow separation in the blade grid, thereby improving the pneumatic benefit, simultaneously not only being capable of starting and stopping control at any time, but also being capable of reducing the interference on the original main flow field compared with the existing jet hole structure and passive vortex control structure.

Description

Control system and method for flow separation inside blade cascade of gas compressor
Technical Field
The invention relates to the field of internal flow control of a gas compressor, in particular to a control system and a control method for internal flow separation of a gas compressor cascade.
Background
The requirement on the high performance of modern aeroengines leads the gas compressor to develop towards the direction of high load all the time, and along with the continuous improvement of the load of the gas compressor, the transverse pressure gradient and the counter pressure gradient in the cascade flow channel are obviously enhanced, so that the flow condition in the cascade is often worsened, and the large-scale flow separation in the cascade flow channel is caused, thereby restricting the improvement of the performance of the gas compressor and reducing the working stability of the gas compressor.
In order to control the flow separation inside the cascade, scholars at home and abroad develop a large number of control methods, which can be mainly divided into passive control and active control. The passive control method comprises the step of inducing the vortex flow direction by adopting a passive vortex generator to control flow separation, but the passive control method is not easy to start and stop control at any time. The active control method mainly inhibits separation by introducing external energy, has the advantages of flexible application and adjustment according to needs, but usually needs to introduce external devices and momentum, thereby increasing the difficulty of design and installation.
Research shows that in the related technology, the flow control is realized by utilizing the kinetic energy injection generated by the plasma excitation, and the main action mode is short-time discharge to form strong pulse disturbance, so that the flow control is realized. However, the jet holes in the active control method easily affect the original main flow field (i.e., the flow field not controlled).
Disclosure of Invention
The embodiment of the invention provides a control system and a control method for flow separation in a blade cascade of an air compressor.
In a first aspect, a control system for flow separation inside a compressor cascade is provided, comprising: at least one compressor blade; a plasma exciter at a leading edge of the compressor blade inlet for generating an induced vortex when the plasma exciter is turned on.
In some embodiments, two electrodes of the plasma exciter are connected with a high-voltage power supply; the plasma exciter is arranged on the front edge of the inlet of the compressor blade and is close to the suction surface of the compressor.
In some embodiments, the two electrodes of the plasma actuator are rectangular electrodes; the electrodes are arranged in the direction of gas flow.
In some embodiments, the compressor blade inlet leading edge is provided with a plasma exciter.
In some embodiments, a plasma exciter is disposed on both the pressure side and the suction side of the leading edge of the compressor blade inlet.
In some embodiments, the compressor blade inlet leading edge is provided with at least three mutually parallel plasma exciters.
In some embodiments, the plasma exciter comprises an exposed electrode and a pre-buried electrode respectively arranged on two side surfaces of an insulating material; the exposed electrode and the embedded electrode are asymmetrically arranged on the insulating material, and a plasma region formed by the exposed electrode and the embedded electrode is a nearly triangular region.
In a second aspect, a method for controlling flow separation inside a compressor cascade is provided, which includes: arranging static pressure measuring points on the surface of the engine to measure whether suction surface flow separation occurs or not; if suction surface flow separation occurs, a plasma exciter located at the leading edge of the compressor blade inlet is activated to generate an induced vortex.
In some embodiments, the method further comprises configuring the position and angle of the plasma actuator according to compressor blade parameters.
In some embodiments, when the compressor blade leading edge is provided with at least three mutually parallel plasma excitations, the spacing between the plasma exciters is configured according to compressor blade parameters.
The technical scheme provided by the invention has the beneficial effects that:
the embodiment of the invention provides a control system for flow separation in a blade cascade of a gas compressor. And when the flow separation of the suction surface occurs, starting a plasma exciter positioned at the front edge of the inlet of the blade of the compressor to generate induced vortex. The control system and the control method can weaken flow loss, improve pneumatic benefit, can start and stop control at any time, and can reduce interference on the original main flow field compared with the existing jet hole structure and passive vortex control structure.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic diagram of an internal vortex structure of a compressor in a control system for flow separation inside a blade cascade of the compressor according to an embodiment of the present invention;
fig. 2 is a schematic diagram of a plasma exciter according to an embodiment of the present invention.
FIG. 3 is a schematic view of an included angle of inlet flow provided by an embodiment of the present invention;
FIG. 4 is a schematic diagram of an arrangement of a plasma exciter at the leading edge of the inlet of a compressor blade according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of an arrangement provided with two plasma actuators at the leading edge of the inlet of a compressor blade according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of an arrangement of not less than three plasma exciters at the leading edge of the inlet of a compressor blade according to an embodiment of the present invention;
fig. 7 is a graph of a variation relationship between a total pressure loss coefficient and a static pressure coefficient of a compressor cascade under different excitation strengths according to an embodiment of the present invention;
FIG. 8 is a graph illustrating the radial distribution of the total pressure loss coefficient of the compressor cascade under different excitation intensities according to an embodiment of the present invention;
fig. 9 is a graph showing a variation relationship between a total pressure loss coefficient and a static pressure coefficient of a compressor cascade under different electrode lengths according to an embodiment of the present invention;
fig. 10 is a distribution diagram of a plasma exciter on a wall surface limit streamline and an induced jet vortex of a compressor under different parameter conditions according to an embodiment of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
As shown in fig. 1, an embodiment of the present invention provides a control system for flow separation inside a compressor cascade, which includes: at least one compressor blade; a plasma exciter at the compressor blade inlet leading edge for generating an induced vortex when the plasma exciter is turned on.
As shown in fig. 1, SV is a wall vortex, CSV is a wall angle vortex, CV is an angle vortex, PV channel vortex, IV is an induced vortex, HSVs is a horseshoe vortex suction surface branch, and HSVp is a horseshoe vortex pressure surface branch.
In the embodiment, the plasma exciter is arranged on the front edge of the compressor blade to replace a vortex generator to generate induced vortex, so that the flow separation in the cascade is controlled. The control can be started and stopped at any time, and the interference on the original main flow field can be reduced compared with the existing jet hole structure and the passive vortex control structure.
Furthermore, two electrodes of the plasma exciter are connected with a high-voltage power supply, and plasmas are generated in the area above the embedded electrodes. The electrodes can be made of copper, and insulating materials can be arranged among the electrodes and can be polytetrafluoroethylene or quartz glass.
Further, as shown in fig. 2, the plasma exciter includes an exposed electrode and a pre-buried electrode respectively disposed on two side surfaces of an insulating medium; the exposed electrode and the embedded electrode are asymmetrically arranged on two side surfaces of the insulating medium, and a plasma region formed by the exposed electrode and the embedded electrode is a nearly triangular region. Wherein, the direction of the inducing force is along the direction of the arc arrow, thereby generating an inducing eddy current, and the electrode is connected with a high-voltage alternating current power supply.
Further, as shown in fig. 1 and 2, the plasma exciter is arranged on the front edge of the inlet of the compressor blade and is close to the suction surface of the compressor; the two electrodes of the plasma actuator are rectangular electrodes and the electrodes are arranged as far as possible in the direction of the gas flow to ensure that the jet vortex generated can develop along the suction surface. The plasma exciter is arranged at the front edge of the inlet of the blade of the gas compressor, provides space for the development of jet flow vortex and is close to the suction surface of the gas compressor, so that the induced vortex can be developed close to the suction surface, on one hand, the transverse flow of the end wall can be prevented, the effect of inhibiting flow separation is achieved, and on the other hand, the interference on main flow is not generated.
In some embodiments, as shown in fig. 1 and 4, the leading edge of the compressor blade inlet is provided with a plasma exciter. A plasma actuator is arranged to form a jet vortex at the end wall adjacent the suction side to control the transverse secondary flow in the passage between the two blades. The effect of preventing the transverse flow of the end wall and inhibiting the flow separation is also achieved, and the main flow is not disturbed.
In a specific embodiment, a plasma exciter is arranged at the leading edge of the inlet of the compressor blade according to the parameters of the compressor cascade. The parameters of the compressor cascade are shown in the table I.
Watch 1
Parameter(s) Numerical value (Unit) Parameter(s) Numerical value (Unit)
Chord length/C 100.0(mm) Geometric folding angle 42(°)
Leaf height/H 100.0(mm) Mounting angle/gamma 112.5(°)
Pitch/t 33.0(mm) Mach/Ma of inlet 0.7(-)
Geometric inlet angle/beta 1 132.0(°) Reynolds number at inlet/Re 1.5×10 6 (-)
In this example, a plasma height of a =1.5mm, b =3mm is defined and a simulation of the plasma actuator is performed using a phenomenological model structure, in which an electric force is added to the momentum equation in the form of a source term. As shown in fig. 4, the plasma exciter was placed 15% axial chord from the compressor blade inlet leading edge and-25% pitch circumferentially from the suction surface.
A plasma exciter is arranged at the front edge of the inlet of the compressor blade, and the flow loss can be controlled by changing the excitation strength of the plasma exciter. Specifically, the inlet relative mach number is defined as Ma =0.1. The quantity of the leaf grid is about 230 ten thousand, and a phenomenological model area is added for local encryption. Using dimensionless parameters
Figure BDA0002832343170000051
Defining a ratio of electric field force to inertial force, where p e Is the electric field density, E is the elementary charge, E 0 Maximum electric field strength between the electrodes, d exciter length, p ∞ For density of incoming flow, U ∞ The excitation strength of the plasma exciter is measured as the incoming flow velocity. As shown in fig. 7, ω is a total pressure loss coefficient, dc is excitation intensity, cp is a static pressure rise coefficient, and the results of experimental data calculation of the variation relationship between the total pressure loss coefficient and the static pressure coefficient of the compressor blade cascade at different excitation intensities show that the loss gradually decreases and changes substantially linearly as the excitation intensity increases, and the static pressure coefficient gradually increases. In addition, as shown in fig. 8, as a result of distribution of total pressure loss coefficients of the compressor cascade along the radial direction under different excitation intensities, the result shows that the blending loss of the near end wall region is increased, and the loss of the secondary flow in the middle part is obviously weakened, so that the control of the flow separation in the cascade can be realized by arranging a plasma exciter at the front edge of the inlet of the compressor blade.
A plasma exciter is arranged on the front edge of the inlet of the compressor blade, and the pneumatic parameters can be adjusted by changing the electrode length of the plasma exciter. Specifically, as shown in fig. 9, the results of experimental data calculation of the variation relationship between the total pressure loss coefficient and the static pressure coefficient of the vane cascade of the compressor under different electrode lengths indicate that the total pressure loss coefficient and the static pressure rise coefficient linearly vary with the increase of the electrode length.
As shown in fig. 10, for distribution diagrams of the plasma exciter on the wall surface limit streamline and the induced jet vortices of the compressor under different parameter conditions, when the electrode length L =5mm (and Dc = 10) of the plasma exciter, the intensity of the induced vortex generated by excitation is very low, and the induced vortex develops substantially close to the suction surface. When L =15mm (and Dc = 10), the strength of the induced streamwise vortices increases, with an increase in both axial and circumferential extent, and disappears until 60% chord length has developed, with a significant delay in separation of the suction surface and a corresponding decrease in the extent of the recirculation zone. When Dc =30 (and L =15 mm), a distinct separation line is formed downstream of the excitation, with a distinct streamwise vortex corresponding to the upper side, progressing until the outlet, the transverse secondary flow of the end wall is significantly suppressed, and the suction surface separation is impaired.
In some embodiments, as shown in fig. 5, the compressor blade inlet leading edge is provided with a plasma exciter on both the pressure side and the suction side. The two plasma exciters are respectively close to the pressure surface and the suction surface and are arranged along the flowing direction as much as possible to form a certain cross angle so as to avoid interference with incoming flow (air inflow). Specifically, one plasma exciter is arranged on the pressure surface side and used for weakening the vortex on the suction surface side, the other plasma exciter is arranged on the pressure surface side and can simultaneously weaken the vortex on the pressure surface side, and a plurality of strands of jet vortices which do not interfere with each other are formed by combining a plurality of compressor blades, so that the control effect of a pneumatic fence is realized, and the channel vortex can be gradually weakened.
In some embodiments, as shown in fig. 6, the compressor blade inlet leading edge is provided with at least three parallel plasma actuators, which form a multi-strand aerodynamic barrier similar to an endwall blade, providing multiple barriers to cross flow.
On the other hand, the embodiment of the invention also provides a control method for flow separation in the blade cascade of the compressor, which comprises the following steps:
s10, arranging static pressure measuring points on the surface of the engine to measure whether suction surface flow separation occurs or not;
and S20, if the flow separation of the suction surface occurs, starting a plasma exciter positioned at the front edge of the inlet of the blade of the compressor to generate an induced vortex.
In some embodiments, further comprising the step of:
and S30, configuring the position and the angle of the plasma exciter according to the parameters of the compressor blade.
It should be noted that the compressor blade parameters described in step S30 include the actual cascade form, the electrode length of the plasma exciter, the intake flow angle α (as shown in fig. 3), and the like, and it is necessary to reasonably select the parameters and adjust the position of the plasma exciter to meet different control requirements. Meanwhile, the optimization method can be used for optimizing the total pressure loss coefficient, the static pressure coefficient and the blocking coefficient cascade pneumatic parameters of the blade cascade of the air compressor so as to further adjust the pneumatic parameters, improve the control effect and enhance the pneumatic benefits.
In some embodiments, further comprising the step of:
s40, when the front edge of the compressor blade is provided with at least three parallel plasmas for excitation, configuring the interval between the plasma exciters according to the parameters of the compressor blade.
In the description of the present invention, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are merely for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
It is to be noted that, in the present invention, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising one of 8230; \8230;" 8230; "does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
The above description is merely illustrative of particular embodiments of the invention that enable those skilled in the art to understand or practice the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (8)

1. A control system for flow separation within a compressor cascade, comprising:
at least one compressor blade;
a plasma exciter at the compressor blade inlet leading edge for generating an induced vortex when the plasma exciter is turned on;
the pressure surface side and the suction surface side of the inlet front edge of the compressor blade are respectively provided with a plasma exciter, and the two plasma exciters are respectively close to the pressure surface and the suction surface and are arranged along the flow direction to form a cross angle.
2. The compressor cascade internal flow split control system of claim 1,
two electrodes of the plasma exciter are connected with a high-voltage power supply;
the plasma exciter is arranged on the front edge of the inlet of the compressor blade and is close to the suction surface of the compressor.
3. The compressor cascade internal flow split control system of claim 2, wherein the two electrodes of the plasma exciter are rectangular electrodes;
the electrodes are arranged in the direction of gas flow.
4. The compressor cascade internal flow split control system of claim 1,
and at least three parallel plasma exciters are arranged at the front edge of the inlet of the adjacent compressor blade.
5. The system for controlling flow separation inside an air compressor cascade as claimed in claim 1, wherein the plasma exciter comprises an exposed electrode and a pre-buried electrode respectively disposed on two side surfaces of an insulating material;
the exposed electrode and the embedded electrode are asymmetrically arranged on the insulating material, and a plasma region formed by the exposed electrode and the embedded electrode is a nearly triangular region.
6. The method for controlling flow separation inside a compressor cascade based on the control system of claim 1, comprising:
arranging static pressure measuring points on the surface of the engine to measure whether suction surface flow separation occurs or not;
if suction surface flow separation occurs, a plasma exciter located at the leading edge of the compressor blade inlet is activated to generate an induced vortex.
7. The method of controlling flow separation within a compressor cascade of claim 6, comprising:
and configuring the position and the angle of the plasma exciter according to the parameters of the compressor blade.
8. The method of controlling flow separation within a compressor cascade of claim 6,
when at least three parallel plasmas are excited on the front edges of the adjacent compressor blades, the interval between the plasma exciters is configured according to the parameters of the compressor blades.
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CN102606502A (en) * 2012-02-19 2012-07-25 中国人民解放军空军工程大学 Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas
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

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Publication number Priority date Publication date Assignee Title
CN101666343A (en) * 2008-09-03 2010-03-10 中国科学院工程热物理研究所 Control system and control method for plasma excitation for cascade internal flow
CN102192083A (en) * 2010-03-09 2011-09-21 通用电气公司 System and method of deicing and prevention or delay of flow separation over wind turbine blades
CN102606502A (en) * 2012-02-19 2012-07-25 中国人民解放军空军工程大学 Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas
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

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