CN103759915A - Test measurement method of local water collecting coefficient - Google Patents

Test measurement method of local water collecting coefficient Download PDF

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Publication number
CN103759915A
CN103759915A CN201410043799.2A CN201410043799A CN103759915A CN 103759915 A CN103759915 A CN 103759915A CN 201410043799 A CN201410043799 A CN 201410043799A CN 103759915 A CN103759915 A CN 103759915A
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infinitesimal
water collection
collection rate
section bar
ice
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CN103759915B (en
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曾飞雄
霍西恒
王大伟
南国鹏
李革萍
白穆
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Commercial Aircraft Corp of China Ltd
Shanghai Aircraft Design and Research Institute Commercial Aircraft Corporation of China Ltd
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Commercial Aircraft Corp of China Ltd
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Abstract

The invention provides a test method for acquiring the practical local water collecting rate of a sectional material. The method includes the following steps that the cross section of the sectional material is obtained in the direction parallel to the incoming flow direction of water drops, infinitesimal surfaces s are obtained on the outer surface, facing the incoming flow of the water drops, of the cross section with the equal interval d, and the equal interval d is equal to the height of infinitesimal incoming flow of the incoming flow of the water drops; a drop spraying system is started, and the water drops are jetted to the outer surface of the sectional material by the drop spraying system in the incoming flow direction of the water drops; water drop jetting of the drop spraying system is stopped after the designated time t; a measuring device is used for drawing an ice shape, corresponding to the cross section, of rime ice formed on the outer surface of the sectional material in a two-dimensional ice shape graph; the ice shape in the two-dimensional ice shape graph is divided into infinitesimal pillar surfaces corresponding to the infinitesimal surfaces s of the sectional material according to the equal interval d, the area of the infinitesimal pillar surfaces of the ice shape is calculated, and therefore the practical local water collecting rate W of the corresponding infinitesimal surface s of the sectional material is calculated. W=ds*rhoi, ds is the area of the infinitesimal pillar surfaces of the ice shape, and rhoi is the rime ice density of the infinitesimal pillar surfaces of the ice shape.

Description

The experimental measurement method of partial water collection coefficient
Technical field
The present invention relates to a kind of experimental measurement method of partial water collection coefficient of experimental measurement method, especially air-foil of partial water collection coefficient of section bar.
Background technology
Aviation is put into practice and is shown, it is one of important flight safety hidden danger that aircraft freezes, and it becomes the problem that must pay close attention in aircraft industry.The icing state 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 normally obtains by cfdrc, although these computing method comparative maturity at present, the significant design input as fields such as aircraft anti-icing systems, still needs test measure or verify.Partial water collection coefficient β refers to the ratio of the lip-deep actual water collection rate of infinitesimal and the flood collection rate of the lip-deep theory of this infinitesimal, does not have ripe testing apparatus in the world for its verification experimental verification.The method of the at present generally acknowledged NASA of US National Aeronautics and Space Administration is the method that adopts dyeing, be about to anti-icing parts surface and cover one deck thieving paper, staining solution is atomized into water droplet by spraying system and is sprayed on anti-icing test specimen surface, then thieving paper is extracted from test specimen surfacial spalling to the amount of dyestuff.The extracting method of data has successively experienced tintmeter method, laser reflection spectroscopic methodology and CCD(charge couple device) reflectometer method.The physical/chemical data of extracting dyestuff from thieving paper, 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 is obtained the partial water collection coefficient of section bar, especially air-foil fast, simultaneously can obtain more accurate actual partial water collection rate.
For this reason, provide a kind of method of testing of obtaining the actual partial water collection rate of section bar, described method comprises the steps:
(1) in the direction that is parallel to water droplet incoming flow, obtain the xsect of described section bar, in the direction perpendicular to water droplet incoming flow, this xsect in the face of usining equidistant d on the outside surface of water droplet incoming flow, obtain infinitesimal face arc length as the infinitesimal face s of section bar outside surface, described equidistant d equals the infinitesimal incoming flow height of described water droplet incoming flow;
(2) described section bar is put into the environment that can simulate, starting characteristics test, after stablize in the flow field in this environment, opens drop spraying system, makes this drop spraying system come flow path direction to spray water droplet towards the outside surface of described section bar along water droplet, carries out timing simultaneously;
(3) water droplet that at the appointed time stops drop spraying system after t sprays, and now on the outside surface of section bar, forms rime ice;
(4) utilize measurement mechanism that the ice type corresponding to described xsect that is formed on the rime ice on section bar outside surface is depicted as to 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 corresponding to the infinitesimal surface s of section bar, calculates the area of the described infinitesimal cylinder of described ice type, thereby calculate the actual partial water collection rate W of the corresponding infinitesimal face s of described section bar,
W=ds·ρ i
In formula,
Ds is the area of the infinitesimal cylinder of ice type,
ρ irime ice density for the infinitesimal cylinder of ice type.
Preferably, in step (5), adopt center line method of approximation to calculate the area of described infinitesimal cylinder,
W=d·h·ρ i
In formula,
D be described equidistantly, i.e. the width of the infinitesimal cylinder corresponding to 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), drop spraying system sprays water droplet and meets following condition: under low temperature environment, droplets impact its will not exist overflow at Surface of profile, completely collected by described surface and form described rime ice.
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 the ice type being formed on section bar outside surface is depicted as to two-dimentional ice type figure.
Preferably, described water droplet come flow path direction perpendicular to the exhibition of described wing to.
Preferably, described water droplet comes flow path direction perpendicular to the direction extending longitudinally of the leading edge of described air-foil.
Preferably, described water droplet comes flow path direction to be parallel to the heading of described aircraft.
Preferably, described water droplet comes flow path direction perpendicular to the outside surface of described section bar.
A kind of experimental measurement method of obtaining the partial water collection coefficient of section bar is also provided, comprises the steps,
(a) according to said method, obtain the actual partial water collection rate W of section bar;
(b) at flow velocity v, the Liquid water content LWC of water droplet incoming flow and test duration t, respectively under the test condition identical with flow velocity, Liquid water content, water-mass density and the test duration of water droplet incoming flow in claim 1, calculate the maximum partial water collection rate of the theory W of the above-mentioned infinitesimal incoming flow height d of infinitesimal incoming flow height 0
W 0=d·LWC·v·t
(c) by actual local collection rate W and theoretical maximum collection rate W 0ratio calculation obtain partial water collection coefficient β
β = W W 0
Preferably, in described step (a), the actual partial water collection rate W obtaining by above-mentioned preferred embodiment calculates partial water collection coefficient β.
Preferably, the maximum partial water collection rate of this theory W 0by icing tunnel, demarcate to verify its data reliability.
Accompanying drawing explanation
Fig. 1 illustrates the track of water droplet incoming flow shock air-foil leading edge with the exhibition of air-foil to the xsect of direction;
Fig. 2 is schematic diagram according to an embodiment of the invention, shows the infinitesimal pattern and the infinitesimal pattern that is formed on the ice type in leading edge of air-foil leading edge outside surface.
Embodiment
The method the present invention relates to is obtained the actual water collection rate of local location by (being usually less than-25 ℃) locational icing amount of testpieces under the low temperature environment based on simulation, more indirectly obtains partial water collection coefficient by the flood collection rate of theory.A specific embodiment of the present invention will be tested to realize by icing tunnel.
As can be seen here, the present invention relates to the 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 obtains by test.
Ultimate principle
Partial water collection coefficient β is the ratio of the lip-deep actual partial water collection rate of infinitesimal and the maximum partial water collection rate of the lip-deep theory of this infinitesimal.The correlation parameter (flow velocity, Liquid water content, test duration etc.) that theoretical maximum partial water collection rate can be tested by icing tunnel calculates and obtains, this calculated value can demarcate to verify its data reliability by icing tunnel, icing tunnel is demarcated and is adopted external high precision apparatus to check data such as flow velocitys, guarantees that its measurement is correct, accurate.Actual partial water collection rate need to be by obtaining the ice type measurement being formed on tested part in icing tunnel test.
Actual partial water collection rate computing method
These computing method based on two hypothesis: a. under low temperature condition, at airfoil surface, will not there is not overflow (overflow phenomena: when water droplet temperature in the water smoke that spraying plant ejects is higher in droplets impact its, droplets impact its does not flow after can not freezing at once and then produce on airfoil surface, subsequently owing to flowing through in journey and freezing after wind-tunnel effect of environmental temperature water droplet, this becomes overflow ice, and this ice is generally the light ice that is transparence), 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 at the infinitesimal surface of the leading edge surface of aerofoil profile 20 S oon by this infinitesimal surface, absorbed completely and do not form overflow, and track 11 in figure does not clash into from the teeth outwards; B. ignore wing exhibition to the impact of direction, only with wing, xsect (below claiming xsect) the place two dimensional surface along exhibition to direction represents typical surperficial For Determining The Droplet Trajectories, refers in the present invention partial water collection coefficient.
As shown in Figure 2, aerofoil profile 20 surfaces are parallel to (being the plane shown in Fig. 2) in the plane at xsect place of direction (as shown in the horizontal arrow in Fig. 2) of incoming flow 30 at it to be represented with infinitesimal face arc length S according to the infinitesimal surface s(being divided into perpendicular to water droplet incoming flow 30 directions corresponding to the equidistant d of infinitesimal incoming flow height), at the appointed time the water yield of the interior infinitesimal surface collection of t can obtain by obtaining the infinitesimal cylindricality area (shadow region in Fig. 2) of rime ice.Obtain the method for infinitesimal cylindricality area and can do free selection, 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, and the infinitesimal cylindricality area equivalent height h by infinitesimal ice type is similar to area integral.Take these computing method below as basic description one embodiment of the present of invention.
Embodiment
1) the icing tunnel testing equipment of choosing is demarcated, be ready to aerofoil profile to be measured and ice type and measure clamp;
2) set rational trystate point (low temperature environment is usually less than-25 ℃), by flow velocity v, Liquid water content LWC and test duration t, calculate the maximum partial water collection rate of the theory W 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 tunnel testing equipment, starting characteristics test, after flow field is stable, open the drop spraying system in icing tunnel testing equipment, 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, the flow velocity v of incoming flow 30, Liquid water content LWC and test duration t are identical when obtaining theoretical maximum partial water collection rate;
4) drop that stops spraying system after fixed time t sprays, and stops subsequently icing tunnel testing equipment;
5) utilize ice type to measure clamp, draw the two-dimentional ice type figure of the ice type on airfoil surface that is formed on, an example of ice type is as shown in the Reference numeral 40 in Fig. 2;
With equidistant d, divide ice type 40, obtain the infinitesimal cylinder on the infinitesimal surface s that is formed on aerofoil profile, adopt suitable method to calculate actual partial water collection rate W (the W=ds ρ of this infinitesimal surface S i), if adopt center line method of approximation, the cylindricality height (i.e. the cylindricality height at 1/2nd equidistant d places) of midline of getting 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 theoretical maximum collection rate W 0ratio calculation obtain partial water collection coefficient β
β = W W 0
Also can select drop to come flow path direction perpendicular to the leading edge of a wing, in this case, the infinitesimal surface s(that airfoil surface is divided into equidistant d according to the direction perpendicular to carrying out flow path direction at it in perpendicular to the plane at the xsect place on leading edge of a wing surface represents by infinitesimal face arc length S).It can also be other directions except above-mentioned two kinds that drop carrys out flow path direction, for example, is parallel to the heading of aircraft, and the selection on infinitesimal surface is also that so this can select according to specific needs under inventive principle of the present invention.
By method above-mentioned in the present invention, by test, in a controllable simulated environment, obtain the partial water collection coefficient of wing.
Above-mentioned exemplary embodiment shows an embodiment in the technical scheme that solves the technical problem to be solved in the present invention.Under the example of this embodiment, other equivalence and similar means that meet the principle of the invention all belong in the scope of protection of the invention.Inventive principle of the present invention is, first will in a three dimensions, collect in a data reduction Cheng Yi two-dimensional plane and collect data, thus, first calculate theoretical maximum partial water collection rate, then, in a simulated environment, obtain the true ice type on this local location xsect, thereby calculate actual partial water collection rate.Thereby obtain the collection efficiency of this local location.

Claims (13)

1. a method of testing of obtaining the actual partial water collection rate of section bar, described method comprises the steps:
(1) in the direction that is parallel to water droplet incoming flow (30), obtain the xsect of described section bar, in the direction perpendicular to water droplet incoming flow (30), this xsect in the face of usining equidistant d on the outside surface of water droplet incoming flow (30), obtain infinitesimal face arc length as the infinitesimal face s of section bar outside surface, described equidistant d equals the infinitesimal incoming flow height of described water droplet incoming flow (30);
(2) described section bar is put into the environment that can simulate, starting characteristics test, after stablize in the flow field in this environment, opens drop spraying system, make the outside surface of this drop spraying system along water droplet incoming flow (30) direction towards described section bar spray water droplet, carry out timing simultaneously;
(3) water droplet that at the appointed time stops drop spraying system after t sprays, and now on the outside surface of section bar, forms rime ice;
(4) utilize measurement mechanism that the ice type (40) corresponding to described xsect that is formed on the rime ice on section bar outside surface is depicted as to 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 corresponding to the infinitesimal face s of section bar, calculate the area of the described infinitesimal cylinder of described ice type (40), thereby calculate the actual partial water collection rate W of the corresponding infinitesimal face s of described section bar,
W=ds·ρ i
In formula,
Ds is the area of the infinitesimal cylinder of ice type (40),
ρ irime ice density for 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,
W=d·h·ρ i
In formula,
D be described equidistantly, i.e. the width of the infinitesimal cylinder corresponding to 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), drop spraying system sprays water droplet and meets following condition: under low temperature environment, to not there is not overflow at Surface of profile in droplets impact its, completely collected by described surface and form described rime ice.
4. the method for testing of partial water collection rate as claimed in claim 3, 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, 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 the ice type (40) being formed on section bar outside surface is depicted as to 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 the exhibition of described wing 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 flow path direction perpendicular to the direction extending longitudinally of 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 comes flow path direction to be parallel to the heading of 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 comes flow path direction perpendicular to the outside surface of described section bar.
11. 1 kinds of experimental measurement methods of 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), at flow velocity v, the Liquid water content LWC of water droplet incoming flow and test duration t respectively under the test condition identical with flow velocity, Liquid water content and the test duration of water droplet incoming flow in claim 1, calculating infinitesimal incoming flow height is the maximum partial water collection rate of the theory W of the infinitesimal incoming flow height d in claim 1 0
W 0=d·LWC·v·t
(c) by actual local collection rate W and theoretical maximum collection rate W 0ratio calculation obtain partial water collection coefficient β
β = W W 0
The experimental measurement method of 12. partial water collection coefficients as claimed in claim 11, it is characterized in that, in described step (a), with the actual partial water collection rate W as any one claim obtained in claim 2-10, calculate partial water collection coefficient β.
The experimental measurement method of 13. partial water collection coefficients as described in claim 11 or 12, is characterized in that, the maximum partial water collection rate of this theory W 0by icing tunnel, demarcate to verify its data reliability.
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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104296957A (en) * 2014-09-11 2015-01-21 中国商用飞机有限责任公司 Method and system for measuring water drop collecting coefficient of aerodynamic surface
CN107702879A (en) * 2017-09-20 2018-02-16 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 Forecasting Methodology
CN111307406A (en) * 2020-05-06 2020-06-19 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
CN111323200A (en) * 2020-05-11 2020-06-23 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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009025578A1 (en) * 2007-08-14 2009-02-26 Central Institute Of Aviation Motors (Ciam) Method for ground testing of aerospace engineering objects exposed to icing and a device for carrying out said method
CN102663238A (en) * 2012-03-21 2012-09-12 南京航空航天大学 Ice surface roughness measuring method based on liquid water distribution
CN102853987A (en) * 2012-09-25 2013-01-02 南京航空航天大学 Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel
CN103048109A (en) * 2012-11-28 2013-04-17 中国商用飞机有限责任公司 Wing test element for ice wind tunnel of anti-icing system for aircraft wing
CN103434652A (en) * 2013-07-15 2013-12-11 中国商用飞机有限责任公司 Method of forming and detecting supercooled water droplet in ground ice-formation condition simulation system, and target simulation device
CN103471804A (en) * 2013-07-15 2013-12-25 中国商用飞机有限责任公司 Method and device for water-mist uniformity control

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009025578A1 (en) * 2007-08-14 2009-02-26 Central Institute Of Aviation Motors (Ciam) Method for ground testing of aerospace engineering objects exposed to icing and a device for carrying out said method
CN102663238A (en) * 2012-03-21 2012-09-12 南京航空航天大学 Ice surface roughness measuring method based on liquid water distribution
CN102853987A (en) * 2012-09-25 2013-01-02 南京航空航天大学 Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel
CN103048109A (en) * 2012-11-28 2013-04-17 中国商用飞机有限责任公司 Wing test element for ice wind tunnel of anti-icing system for aircraft wing
CN103434652A (en) * 2013-07-15 2013-12-11 中国商用飞机有限责任公司 Method of forming and detecting supercooled water droplet in ground ice-formation condition simulation system, and target simulation device
CN103471804A (en) * 2013-07-15 2013-12-25 中国商用飞机有限责任公司 Method and device for water-mist uniformity control

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
张威等: "MVD对翼型冰形及气动性能影响数值模拟", 《直升机技术》 *
张强等: "采用欧拉两相流法对翼型表面霜冰的数值模拟", 《北京航空航天大学学报》 *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104296957A (en) * 2014-09-11 2015-01-21 中国商用飞机有限责任公司 Method and system for measuring water drop collecting coefficient of aerodynamic surface
CN107702879A (en) * 2017-09-20 2018-02-16 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 Forecasting Methodology
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
CN111307406A (en) * 2020-05-06 2020-06-19 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
CN111323200A (en) * 2020-05-11 2020-06-23 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
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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