CN103759915B - The test measuring method of partial water collection coefficient - Google Patents
The test measuring method of partial water collection coefficient Download PDFInfo
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- CN103759915B CN103759915B CN201410043799.2A CN201410043799A CN103759915B CN 103759915 B CN103759915 B CN 103759915B CN 201410043799 A CN201410043799 A CN 201410043799A CN 103759915 B CN103759915 B CN 103759915B
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- section bar
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Abstract
The invention provides a kind of method of testing obtaining the actual partial water collection rate of section bar, comprise the steps: in the direction being parallel to water droplet incoming flow, obtain the xsect of section bar, at the infinitesimal incoming flow height equaling water droplet incoming flow on the outside surface of water droplet incoming flow with equidistant d acquisition infinitesimal face s, equidistant d of this xsect; Open droplet spray system, make this droplet spray system carry out the outside surface injection water droplet of flow path direction towards section bar along water droplet; The water droplet of droplet spray system is at the appointed time stopped to spray after t; Utilize measurement mechanism that the ice type corresponding to xsect of the rime ice be formed on section bar outside surface is depicted as two-dimentional ice type figure; According to equidistant d, the ice type in two-dimentional ice type figure is divided into the infinitesimal cylinder of the infinitesimal surface s corresponding to section bar, calculates the area of the infinitesimal cylinder of ice type, thus calculate the actual partial water collection rate W of the corresponding infinitesimal face s of section bar, then W=ds ρ
i, ds is the area of the infinitesimal cylinder of ice type, ρ
ifor the rime ice density of the infinitesimal cylinder of ice type.
Description
Technical field
The present invention relates to a kind of test measuring method of partial water collection coefficient of section bar, especially the test measuring method of the partial water collection coefficient of air-foil.
Background technology
Aviation practice shows, it is one of important flight safety hidden danger that aircraft freezes, and it becomes the problem must paid close attention in aircraft industry.The icing condition of aircraft wing is relevant with the partial water collection coefficient of aircraft wing, and this coefficient is the important content of wing For Determining The Droplet Trajectories, is also the significant design input parameter of wing anti-ice system design.
At present, the partial water collection coefficient of the leading edge of a wing is normally obtained by cfdrc, although these computing method comparative maturity at present, the significant design as fields such as aircraft anti-icing system inputs, and still needs test to carry out to measure or verify.Partial water collection coefficient β refers to the ratio of the most flood collection rate of actual water collection rate on infinitesimal surface and the theory on this infinitesimal surface, in the world for the testing apparatus that its verification experimental verification is unripe.The method of the US National Aeronautics and Space Administration NASA generally acknowledged at present is the method adopting dyeing, by anti-ice components surface coverage one deck thieving paper, staining solution is atomized into water droplet by spraying system and is sprayed on anti-icing surface of test piece, then thieving paper is peeled off the amount of rear extraction dyestuff from surface of test piece.The extracting method of data successively experienced by colorimeter method, laser reflection spectroscopic methodology and CCD(chargecoupledevice) reflectometer method.From thieving paper, extract the physical/chemical data of dyestuff, data handling procedure is more complicated, and application engineering difficulty is very large.
Summary of the invention
For this reason, the present invention to provide a kind of easy, test method to be to obtain the partial water collection coefficient of section bar, especially air-foil fast, can obtain more accurate actual partial water collection rate simultaneously.
For this reason, provide a kind of method of testing obtaining the actual partial water collection rate of section bar, described method comprises the steps:
(1) in the direction being parallel to water droplet incoming flow, obtain the xsect of described section bar, on the direction perpendicular to water droplet incoming flow, the outside surface of water droplet incoming flow faced by this xsect obtains the infinitesimal face s of infinitesimal face arc length as section bar outside surface using equidistant d, and described equidistant d equals the infinitesimal incoming flow height of described water droplet incoming flow;
(2) described section bar is put into an environment that can simulate, starting characteristics test, after the flow field in this environment is stable, open droplet spray system, make this droplet spray system carry out the outside surface injection water droplet of flow path direction towards described section bar along water droplet, carry out timing simultaneously;
(3) at the appointed time stop the water droplet of droplet spray system to spray after t, now on the outside surface of section bar, form rime ice;
(4) utilize measurement mechanism that the ice type corresponding to described xsect of the rime ice be formed on section bar outside surface is depicted as two-dimentional ice type figure;
(5) according to equidistant d, the ice type in two-dimentional ice type figure is divided into the infinitesimal cylinder of the infinitesimal surface s corresponding to section bar, calculates the area of the described infinitesimal cylinder of described ice type, thus calculate the actual partial water collection rate W of the corresponding infinitesimal face s of described section bar, then
W=ds·ρ
i
In formula,
Ds is the area of the infinitesimal cylinder of ice type,
ρ
ifor the rime ice density of the infinitesimal cylinder of ice type.
Preferably, in step (5), center line method of approximation is adopted to calculate the area of described infinitesimal cylinder, then
W=d·h·ρ
i
In formula,
D is equidistantly described, i.e. the width corresponding to the infinitesimal cylinder of infinitesimal incoming flow height of ice type,
H is the equivalent height of the infinitesimal cylinder of ice type.
Preferably, in described step (2) and (3), droplet spray system sprays water droplet and meets following condition: at low ambient temperatures, droplets impact its will not exist overflow at Surface of profile, forms described rime ice completely collected by described surface.
Preferably, described section bar is the air-foil of aircraft, and the outside surface of described section bar is the outside surface of described aerofoil profile leading edge.
Preferably, the equivalent height h of the infinitesimal cylinder of described ice type is the height of the d/2 midline of described infinitesimal cylinder.
Preferably, in described step (4), utilize ice type to measure clamp and the ice type be formed on section bar outside surface is depicted as two-dimentional ice type figure.
Preferably, described water droplet come flow path direction perpendicular to described wing exhibition to.
Preferably, described water droplet comes the extending longitudinally direction of flow path direction perpendicular to the leading edge of described air-foil.
Preferably, described water droplet carrys out the heading that flow path direction is parallel to described aircraft.
Preferably, described water droplet carrys out the outside surface of flow path direction perpendicular to described section bar.
A kind of test measuring method obtaining the partial water collection coefficient of section bar is also provided, comprises the steps,
A () obtains the actual partial water collection rate W of section bar according to said method;
B (), under the test condition that flow velocity v, Liquid water content LWC and the test duration t of water droplet incoming flow are identical with the test duration with the flow velocity of the water droplet incoming flow in claim 1, Liquid water content, water-mass density respectively, calculates the maximum partial water collection rate W of theory of the above-mentioned infinitesimal incoming flow height d of infinitesimal incoming flow height
0
W
0=d·LWC·v·t
C () is by actual local collection rate W and the maximum collection rate W of theory
0ratio calculation obtain partial water collection coefficient β
Preferably, in described step (a), calculate partial water collection coefficient β with the actual partial water collection rate W that above-mentioned preferred embodiment obtains.
Preferably, this theoretical maximum partial water collection rate W
0demarcated by icing tunnel and verify its data reliability.
Accompanying drawing explanation
To the xsect in direction, Fig. 1 illustrates that water droplet incoming flow clashes into the track of air-foil leading edge with the exhibition of air-foil;
Fig. 2 is schematic diagram according to an embodiment of the invention, shows the infinitesimal pattern of air-foil leading edge outside surface and is formed in the infinitesimal pattern of the ice type in leading edge.
Embodiment
Icing amount under low temperature environment based on simulation on (being usually less than-25 DEG C) testpieces position is obtained the actual water collection rate of local location by the method that the present invention relates to, more indirectly obtains partial water collection coefficient by the most flood collection rate of theory.A specific embodiment of the present invention will be realized by icing mnncl tcst.
As can be seen here, the present invention relates to the most flood collection rate of local location theory and the actual water collection rate of local location.The theoretical maximum partial water collection rate of local location obtains by calculating, and the actual partial water collection rate of local location is obtained by test.
Ultimate principle
Partial water collection coefficient β is the ratio of the actual partial water collection rate on infinitesimal surface and the maximum partial water collection rate of theory on this infinitesimal surface.Theoretical maximum partial water collection rate can calculate acquisition by the correlation parameter of icing mnncl tcst (flow velocity, Liquid water content, test duration etc.), this calculated value can be demarcated by icing tunnel and verify its data reliability, icing tunnel is demarcated and is adopted external high precision apparatus to check data such as flow velocitys, guarantees that it measures correct, accurate.Actual partial water collection rate needs by obtaining the ice type measurement be formed on tested part in icing mnncl tcst.
Actual partial water collection rate computing method
These computing method are based on two hypothesis: a. at low temperatures, overflow (overflow phenomena: when the water droplet temperature in the water smoke that spraying plant ejects is higher will not be there is in droplets impact its at airfoil surface, droplets impact its flows after can not freezing at once and then produce on airfoil surface, freeze owing to flowing through in journey after wind-tunnel effect of environmental temperature water droplet subsequently, this becomes overflow ice, and this ice is generally the light ice of transparent shape), completely collected by surface and form rime ice, shown in droplets impact its track 10 as shown in Figure 1, it is highly d
0infinitesimal impinging jet the leading edge surface of aerofoil profile 20 infinitesimal surface S
oon completely absorb by this infinitesimal surface and do not form overflow, and the track 11 in figure does not impinge upon on the surface; B. ignore the impact of wing exhibition to direction, namely only represent typical surperficial For Determining The Droplet Trajectories with wing along exhibition to xsect (hereafter claiming xsect) the place two dimensional surface in direction, refer to partial water collection coefficient in the present invention.
As shown in Figure 2, aerofoil profile 20 surface is parallel to (plane namely shown in Fig. 2) in the plane at the xsect place in the direction (as shown in the horizontal arrow in Fig. 2) of incoming flow 30 at it represent according to the infinitesimal surface s(infinitesimal face arc length S be divided into perpendicular to water droplet incoming flow 30 direction corresponding to the equidistant d of infinitesimal incoming flow height), at the appointed time in t, the infinitesimal cylindricality area (shadow region in Fig. 2) of the water yield of infinitesimal surface collection namely by obtaining rime ice obtains.The method obtaining infinitesimal cylindricality area can make unrestricted choice, include but not limited to image forming analysis, curvilinear function matching integration, center line approximate treatment etc., wherein shortcut calculation is center line approximate treatment the most easily, namely carrys out similar area integration by the infinitesimal cylindricality area equivalent height h of infinitesimal ice type.Based on these computing method, one embodiment of the present of invention are described below.
Embodiment
1) the icing mnncl tcst equipment chosen is demarcated, get out aerofoil profile to be measured and ice type measurement clamp;
2) set rational trystate point (low temperature environment is usually less than-25 DEG C), calculate by flow velocity v, Liquid water content LWC and test duration t the maximum partial water collection rate W of theory that infinitesimal incoming flow height is d
0
W
0=d·LWC·v·t
3) aerofoil profile to be measured is put into proven icing mnncl tcst equipment, starting characteristics test, the droplet spray system in icing mnncl tcst equipment is opened after flow field is stablized, to carry out flow path direction guide vane type 20 leading edge liquid droplets perpendicular to spanwise shown in Fig. 2, and start timing, wherein, flow velocity v, the Liquid water content LWC of incoming flow 30 are identical with during the theoretical maximum partial water collection rate of acquisition with test duration t;
4) stop the drop of spraying system to spray after fixed time t, stop icing mnncl tcst equipment subsequently;
5) utilize ice type to measure clamp, draw the two-dimentional ice type figure of the ice type be formed on airfoil surface, an example of ice type is as shown in the Reference numeral 40 in Fig. 2;
Divide ice type 40 with equidistant d, obtain the infinitesimal cylinder on the surperficial s of the infinitesimal being formed in aerofoil profile, adopt suitable method to calculate actual partial water collection rate W (the W=ds ρ of this infinitesimal surface S
i), according to center line method of approximation, the cylindricality height (i.e. the cylindricality height at 1/2nd equidistant d places) namely getting the midline of the infinitesimal cylinder of this ice type 40 is infinitesimal cylinder equivalent height h,
W=d·h·ρ
i
In formula,
Ds is the area of infinitesimal cylinder
D is the width of infinitesimal cylinder, i.e. infinitesimal incoming flow height
H is infinitesimal cylinder equivalent height,
ρ
ifor rime ice density;
6) by actual local collection rate W and the maximum collection rate W of theory
0ratio calculation obtain partial water collection coefficient β
Also drop can be selected to carry out flow path direction perpendicular to the leading edge of a wing, in this case, airfoil surface is represented according to the infinitesimal surface s(infinitesimal face arc length S being divided into equidistant d perpendicular to the direction carrying out flow path direction in its plane perpendicular to the xsect place on leading edge of a wing surface).It can also be other directions except above-mentioned two kinds that drop carrys out flow path direction, and such as, be parallel to the heading of aircraft, the selection on infinitesimal surface is also like this, and this can select according to specific needs under inventive principle of the present invention.
By method above-mentioned in the present invention, in a controllable simulated environment, obtained the partial water collection coefficient of wing by test.
Above-mentioned exemplary embodiment shows an embodiment in the technical scheme solving the technical problem to be solved in the present invention.Under the example of this embodiment, other meets the equivalence of the principle of the invention and similar means all belong in the scope of protection of the invention.Inventive principle of the present invention is, first will collect in a three dimensions in a data reduction Cheng Yi two-dimensional plane and collect data, thus, the partial water collection rate that the first theory of computation is maximum, then, in a simulated environment, obtain the true ice type on this local location xsect, thus calculate actual partial water collection rate.Thus obtain the collection efficiency of this local location.
Claims (13)
1. obtain a method of testing for the actual partial water collection rate of section bar, described method comprises the steps:
(1) in the direction being parallel to the water droplet incoming flow (30) with flow velocity and Liquid water content, obtain the xsect of described section bar, on the direction perpendicular to water droplet incoming flow (30), the outside surface of water droplet incoming flow (30) faced by this xsect obtains the infinitesimal face s of infinitesimal face arc length as section bar outside surface using equidistant d, and described equidistant d equals the infinitesimal incoming flow height of described water droplet incoming flow (30);
(2) described section bar is put into an environment that can simulate, starting characteristics test, after the flow field in this environment is stable, opens droplet spray system, make this droplet spray system spray water droplet along water droplet incoming flow (30) direction towards the outside surface of described section bar, carry out timing simultaneously;
(3) at the appointed time stop the water droplet of droplet spray system to spray afterwards, now on the outside surface of section bar, form rime ice;
(4) utilize measurement mechanism that the ice type (40) corresponding to described xsect of the rime ice be formed on section bar outside surface is depicted as two-dimentional ice type figure;
(5) according to equidistant d, the ice type (40) in two-dimentional ice type figure is divided into the infinitesimal cylinder of the infinitesimal face s corresponding to section bar, calculate the area of the described infinitesimal cylinder of described ice type (40), thus calculate the actual partial water collection rate W of the corresponding infinitesimal face s of described section bar, then
W＝ds·ρ
i
In formula,
Ds is the area of the infinitesimal cylinder of ice type (40),
ρ
ifor the rime ice density of the infinitesimal cylinder of ice type (40).
2. the method for testing of partial water collection rate as claimed in claim 1, is characterized in that, in step (5), adopts center line method of approximation to calculate the area of described infinitesimal cylinder, then
W＝d·h·ρ
i
In formula,
D is equidistantly described, i.e. the width corresponding to the infinitesimal cylinder of infinitesimal incoming flow height of ice type (40),
H is the equivalent height of the infinitesimal cylinder of ice type (40).
3. the method for testing of partial water collection rate as claimed in claim 2, it is characterized in that, in described step (2) and (3), droplet spray system sprays water droplet and meets following condition: at low ambient temperatures, to not there is overflow at Surface of profile in droplets impact its, form described rime ice collected by the described surface completely.
4. the method for testing of partial water collection rate as claimed in claim 3, it is characterized in that, described section bar is the air-foil of aircraft, and the outside surface of described section bar is the outside surface of described aerofoil profile leading edge.
5. the method for testing of partial water collection rate as claimed in claim 4, it is characterized in that, the equivalent height h of the infinitesimal cylinder of described ice type (40) is the height of the d/2 midline of described infinitesimal cylinder.
6. the method for testing of partial water collection rate as claimed in claim 1, is characterized in that, in described step (4), utilizes ice type to measure clamp and the ice type (40) be formed on section bar outside surface is depicted as two-dimentional ice type figure.
7. the method for testing of the partial water collection rate as described in claim 4 or 5, is characterized in that, described water droplet incoming flow (30) direction perpendicular to described wing exhibition to.
8. the method for testing of the partial water collection rate as described in claim 4 or 5, is characterized in that, described water droplet comes the extending longitudinally direction of flow path direction perpendicular to the leading edge of described air-foil.
9. the method for testing of the partial water collection rate as described in claim 4 or 5, is characterized in that, described water droplet carrys out the heading that flow path direction is parallel to described aircraft.
10. the method for testing of the partial water collection rate as described in any one in claim 1-6, is characterized in that, described water droplet carrys out the outside surface of flow path direction perpendicular to described section bar.
11. 1 kinds of test measuring methods obtaining the partial water collection coefficient of section bar, comprise the steps,
A () method according to claim 1 obtains the actual partial water collection rate W of section bar;
B (), under the test condition that flow velocity v, Liquid water content LWC and the test duration t of water droplet incoming flow are identical with the fixed time with the flow velocity of the water droplet incoming flow in claim 1, Liquid water content respectively, calculates the maximum partial water collection rate W of theory that infinitesimal incoming flow height is the equidistant d in claim 1
0, wherein
W
0＝d·LWC·v·t；
C () is by actual partial water collection rate W and the maximum partial water collection rate W of theory
0ratio calculation obtain partial water collection coefficient β, wherein
The test measuring method of 12. partial water collection coefficients as claimed in claim 11, it is characterized in that, in described step (a), with as any one claim in claim 2-10 the actual partial water collection rate W that obtains calculate partial water collection coefficient β.
The test measuring method of 13. partial water collection coefficients as described in claim 11 or 12, is characterized in that, this theoretical maximum partial water collection rate W
0demarcated by icing tunnel and verify its data reliability.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104296957B (en) * | 2014-09-11 | 2017-08-11 | 中国商用飞机有限责任公司 | Measure the method and system of the drop collection coefficient of aerodynamic surface |
| CN107702879B (en) * | 2017-09-20 | 2019-06-18 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of aircraft dynamic ice ice type microstructure features prediction technique |
| CN111307406B (en) * | 2020-05-06 | 2020-11-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing wind tunnel liquid water content measuring method |
| CN111323200B (en) * | 2020-05-11 | 2020-08-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing area calculation method for icing wind tunnel test |
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