CN100491950C - Air compressor louver experiment device with adjustable additional blades based on relative motion concept - Google Patents
Air compressor louver experiment device with adjustable additional blades based on relative motion concept Download PDFInfo
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- CN100491950C CN100491950C CNB2007100723439A CN200710072343A CN100491950C CN 100491950 C CN100491950 C CN 100491950C CN B2007100723439 A CNB2007100723439 A CN B2007100723439A CN 200710072343 A CN200710072343 A CN 200710072343A CN 100491950 C CN100491950 C CN 100491950C
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- end wall
- leaf blade
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Abstract
The invention relates to an air compressor cascade test installation with adjustable attachment leaf blade belt based on the relative motion concept, which relates to an air compressor cascade test installation. The invention goal is that solves the high air compressor dynamic laboratory bench equipment expense and the experiment surveys difficult major problem; the question of plane blading static laboratory bench model is that flow has big difference with the actual flow, low experimental result direct application value. The invention experiment leaf blade (7) fixes in between the fixed end wall (3) and the down fixed end wall(4), the adjustable attachment leaf blade (6) establishes in the reciprocal motion lower extremity wall (2) upside of the down fixed end wall (4) side. The invention may take as the multi analysis compressor rotor leaf blade grid interior three-dimensional flow dynamic characteristic simplification model, and used for researching the new compressor rotor blading interior air current movement situation with the adjustable attachment leaf blade, the experimental system causes based on the plane blading experimental study to approach to the actual flow, but also has the merit of experimental cost inexpensively, easy to realize the leaf blade channel interior flow field comprehensive survey and so on.
Description
Technical field
The present invention relates to a kind of air compressor louver experiment device.
Background technology
The function of pneumatic plant is that gas is compressed to specific pressure, can be divided into rotary (or vane type) and piston type two classes, and rotary compressor can be divided into axial-flow type and centrifugal.Axial-flow compressor is the important component part of gas turbine, is widely used in fields such as aviation, ground, naval vessel and cruising missile, is important power system.Blade is the critical piece of pneumatic plant, gas stream be subjected to when crossing the runner that blade forms blade to its acting force and obtain mechanical energy.Pneumatic plant flow passage component and blade design belong to the high-tech category, and be all the more so for the novel air pressing machine rotor that adopts the adjustable additional blades technology.The physical process or the structure that from understand the compressor rotor leaf grating in depth, flow, the mutual relationship equal angles of exploring between aerodynamic parameter such as aerodynamic loss, pressure distribution and the blade primitive level geometric parameter is set out, experimental study work is ten minutes fundamental sum necessity, and it is irreplaceable to be still existing theoretical analysis and numerical computation method institute.Experimental study model for compressor rotor blade tip zone flows generally has two kinds, the dynamic experiment table (see figure 1) of first pneumatic plant, but real simulated rotator tip gap area flows, but cost of equipment height, the experiment measuring difficulty is big, especially must design the fluidal texture that complicated surveying instrument servomechanism just can measure rotor leaf grating inside; It two is static experimental facilities (see figure 2)s of plane cascade of band gap, and advantage is that equipment cost is low, be easy to realize the detailed measurements to the blade path flow field, but because model flows and true flowing differs greatly, experimental result direct application value is not high.
Summary of the invention
The objective of the invention is for solving the dynamic experiment table cost of equipment of pneumatic plant height, the experiment measuring difficulty is big, especially must design the problem that complicated surveying instrument servomechanism just can measure the fluidal texture of rotor leaf grating inside; The plane cascade static laboratory bench model flows and true flowing differs greatly, and the problem that experimental result direct application value is not high provides a kind of air compressor louver experiment device of the band adjustable additional blades based on the relative motion notion.The present invention is by reciprocating upper end wall 1, reciprocating lower end wall 2, last anchor end wall 3, following anchor end wall 4, guide vane 5, adjustable additional blades 6 and experiment blade 7 are formed, reciprocating upper end wall 1 and reciprocating lower end wall 2 are arranged in parallel up and down, guide vane 5 is fixed between reciprocating upper end wall 1 and the reciprocating lower end wall 2, last anchor end wall 3 and following anchor end wall 4 are arranged in parallel up and down, experiment blade 7 is fixed between anchor end wall 3 and the following anchor end wall 4, last anchor end wall 3 and following anchor end wall 4 are arranged on a side of reciprocating upper end wall 1 and reciprocating lower end wall 2, and adjustable additional blades 6 is arranged on the close upside of the reciprocating lower end wall 2 of anchor end wall 4 one sides down.The present invention can be used as the simplified model of labor compressor rotor blade grid interior three-dimensional flow characteristics, is used for studying the novel air pressing machine rotor leaf grating internal gas flow motion conditions of band adjustable additional blades, explores the approach that improves this pneumatic plant aeroperformance.This experimental system makes the experimental study based on plane cascade more approach true flowing, also have experimental cost cheap, be easy to realize to advantages such as blade path interior flow field detailed measurements.
Description of drawings
Fig. 1 is the synoptic diagram of the dynamic experiment table of prior art pneumatic plant, Fig. 2 is the principle of work synoptic diagram of the static experimental facilities of prior art plane cascade, Fig. 3 is a structural representation of the present invention, Fig. 4～Fig. 7 is a principle of work synoptic diagram of the present invention, Fig. 8 and Fig. 9 are the velocity triangle synoptic diagram of true compressor rotor under the axial admission condition, and the rotor inlet type twists speed.
Embodiment
Embodiment one: (referring to Fig. 3) present embodiment is by reciprocating upper end wall 1, reciprocating lower end wall 2, last anchor end wall 3, following anchor end wall 4, guide vane 5, adjustable additional blades 6 and experiment blade 7 are formed, reciprocating upper end wall 1 and reciprocating lower end wall 2 are arranged in parallel up and down, guide vane 5 is fixed between reciprocating upper end wall 1 and the reciprocating lower end wall 2, last anchor end wall 3 and following anchor end wall 4 are arranged in parallel up and down, experiment blade 7 is fixed between anchor end wall 3 and the following anchor end wall 4, last anchor end wall 3 and following anchor end wall 4 are arranged on a side of reciprocating upper end wall 1 and reciprocating lower end wall 2, and adjustable additional blades 6 is arranged on the close upside of the reciprocating lower end wall 2 of anchor end wall 4 one sides down.
Principle of work: one, adopt the simulation that experimentizes of static plane cascade to be mainly reflected between blade and the end wall with the true difference of compressor rotor and not have relative motion, from Fig. 8, velocity triangle shown in Figure 9 as can be seen, under true compressor rotor axial admission condition, increase gradually to potential barrier district inlet air flow absolute velocity C from boundary-layer, but direction is constant all the time and be axial, and relative velocity W then is what twist; Two, based on the thought of relative motion, the pneumatic plant plane cascade experimental system of the band adjustable additional blades of design consideration dynamic effects as shown in Figure 3, make the lower end wall motion, and guide vane (being used for realizing making inlet air flow to move with end wall and satisfying the rotor inlet airflow direction) and adjustable additional blades (monoblock type or local formula) are installed on it, the spinner blade that is installed in upper end wall is then motionless, has so just simulated the rotator tip Clearance Flow of band adjustable additional blades more truly according to the relative motion notion; Three, lower end wall is the to-and-fro movement form, adopt step motor drive, surveying instruments such as pneumatic probe or hot-wire anemometer are installed on static upper end wall, when vibration-direction is forward, the surveying instrument image data, when vibration-direction is negative sense, the surveying instrument cease operation, the detailed aerodynamic parameter that can obtain to measure the cross section through to-and-fro movement repeatedly distributes, certainly, be straight end wall because stationary rotor does not have centrifugal force and plane cascade, still there are differences with actual conditions, but in tip clearance stream, these two factors are more less important.
Claims (1)
1, a kind of air compressor louver experiment device of the band adjustable additional blades based on the relative motion notion, it is by reciprocating upper end wall (1), reciprocating lower end wall (2), last anchor end wall (3), following anchor end wall (4), guide vane (5), adjustable additional blades (6) and experiment blade (7) are formed, reciprocating upper end wall (1) and reciprocating lower end wall (2) are arranged in parallel up and down, guide vane (5) is fixed between reciprocating upper end wall (1) and the reciprocating lower end wall (2), it is characterized in that anchor end wall (3) and following anchor end wall (4) are arranged in parallel up and down, experiment blade (7) is fixed between anchor end wall (3) and the following anchor end wall (4), last anchor end wall (3) and following anchor end wall (4) are arranged on a side of reciprocating upper end wall (1) and reciprocating lower end wall (2), and adjustable additional blades (6) is arranged on the close upside of the reciprocating lower end wall (2) of anchor end wall (4) one sides down.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100723439A CN100491950C (en) | 2007-06-11 | 2007-06-11 | Air compressor louver experiment device with adjustable additional blades based on relative motion concept |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100723439A CN100491950C (en) | 2007-06-11 | 2007-06-11 | Air compressor louver experiment device with adjustable additional blades based on relative motion concept |
Publications (2)
| Publication Number | Publication Date |
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| CN101067586A CN101067586A (en) | 2007-11-07 |
| CN100491950C true CN100491950C (en) | 2009-05-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2007100723439A Expired - Fee Related CN100491950C (en) | 2007-06-11 | 2007-06-11 | Air compressor louver experiment device with adjustable additional blades based on relative motion concept |
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| CN101556205B (en) * | 2009-03-25 | 2010-10-27 | 北京航空航天大学 | Rotary slotted cylinder/movable wing panel type gust generator |
| CN104897406B (en) * | 2015-06-04 | 2017-05-03 | 大连海事大学 | Rotary stamping compressed rotor plane cascade experimental system |
| CN106441782B (en) * | 2016-10-21 | 2018-12-18 | 大连理工大学 | A kind of reciprocating blade wake passing generator |
| CN106640619B (en) * | 2017-01-09 | 2018-11-20 | 大连海事大学 | A kind of Compressor Cascades experimental system with suction baffle arrangement |
| CN106837840B (en) * | 2017-01-22 | 2018-02-13 | 大连海事大学 | It is a kind of to be used for the fan-shaped cascade experiment system that stator blade aeroperformance is studied in Non-uniform Currents |
| CN108757433B (en) * | 2018-05-31 | 2019-08-27 | 大连海事大学 | A kind of cantilever Varied clearance plane cascade experimental provision |
| CN108775850B (en) * | 2018-06-11 | 2024-01-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Planar blade cascade test device capable of continuously changing blade top gap and test method thereof |
| CN108931363A (en) * | 2018-07-05 | 2018-12-04 | 西安交通大学 | A kind of plane and D remote sensing tele-experimentation device |
| CN109374252B (en) * | 2018-09-28 | 2020-11-20 | 西北工业大学 | Compressor tandem cascade experimental device |
| CN109372678B (en) * | 2018-11-12 | 2021-02-12 | 江苏大学 | Transient flow experimental device for water turbine |
| CN111075513B (en) * | 2019-11-12 | 2022-04-29 | 沈阳航空航天大学 | Fan-shaped blade cascade tester and method for changing air inlet angle of fan-shaped blade cascade |
| CN113252279A (en) * | 2021-06-28 | 2021-08-13 | 哈尔滨工业大学 | Pneumatic test simulation device for impeller machinery |
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Granted publication date: 20090527 Termination date: 20100611 |