CN104296957B - Method and system for measuring water drop collection coefficient of aerodynamic surface - Google Patents
Method and system for measuring water drop collection coefficient of aerodynamic surface Download PDFInfo
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- CN104296957B CN104296957B CN201410461886.XA CN201410461886A CN104296957B CN 104296957 B CN104296957 B CN 104296957B CN 201410461886 A CN201410461886 A CN 201410461886A CN 104296957 B CN104296957 B CN 104296957B
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 57
- 238000000034 method Methods 0.000 title claims abstract description 16
- 239000007788 liquid Substances 0.000 claims abstract description 22
- 238000010438 heat treatment Methods 0.000 claims abstract description 21
- 238000001704 evaporation Methods 0.000 claims description 9
- 230000035939 shock Effects 0.000 claims description 8
- 230000008020 evaporation Effects 0.000 claims description 5
- 239000003643 water by type Substances 0.000 claims 2
- 238000005259 measurement Methods 0.000 abstract description 10
- 230000004048 modification Effects 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 239000012530 fluid Substances 0.000 description 3
- 238000009413 insulation Methods 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000741 silica gel Substances 0.000 description 2
- 229910002027 silica gel Inorganic materials 0.000 description 2
- 241000532370 Atla Species 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 239000003086 colorant Substances 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000007447 staining method Methods 0.000 description 1
- 238000004781 supercooling Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention provides a method and system for measuring a water droplet collection coefficient of an aerodynamic surface. The method comprises the following steps: heating the aerodynamic surface to a predetermined outer surface temperature at a first power density at a specific speed and a specific temperature of dry air; heating the aerodynamic surface to the predetermined outer surface temperature at a second power density at the particular speed and the particular temperature of the humid air, the humid air having a particular liquid water content; and obtaining the water droplet collection coefficient of the aerodynamic surface based on the specific speed, the specific temperature, the liquid water content, the first power density, the second power density, and the predetermined outer surface temperature. The method and system of the invention enable continuous measurement of the water droplet collection coefficient of aerodynamic surfaces in any state, in particular for measuring the water droplet collection coefficient of aerodynamic surfaces of aircraft (e.g. wings, engine intakes, etc.).
Description
Technical field
The present invention relates to a kind of method and system for the drop collection coefficient for measuring aerodynamic surface.
Background technology
Carry out anti-icing or icing simulation analysis when, it is necessary to solve water evaporation radiating, heating super-cooling waterdrop needed for hot-fluid and
The hot-fluid of water droplet kinetic energy transformation, three hot-fluids need to solve the shock water for striking surface, and hitting water needs to solve the table
Face drop collection coefficient.Wherein, it is drop collection factor beta, air velocity V to hit water0With the Liquid water content LWC in air
Function.The accuracy of the drop collection coefficient calculated for checking software for calculation or program is, it is necessary to by testing to drop collection
Coefficient is measured.
Known drop collection coefficient method is blotting paper decoration method.Blotting paper is arranged in measurement surface, droplets impact
Many region blotting paper colors are more black, and the few field color of droplets impact is shallower.Shock water is checked according to colour atla, then basis
Hit water and time of measuring obtains drop collection coefficient.Bibliography " C.S.Bidwell, Cleveland, OH.,
S.R.Mohler, Jr.etc.. ' Collection Efficiency and Ice Accretion Calculations for
A Sphere, a Swept MS (1) -317Wing, a Swept NACA-0012Wing Tip, an Axisymmetric
Using this method in US National Aeronautics and Space Administration in Inlet, and a Boeing737-300Inlet ' AIAA-95-0755 "
(NASA) LEWIS icing tunnels respectively to spheroid, MS-317 aerofoil profiles, NACA-0012 aerofoil profiles, a kind of symmetrical engine intake and
B737-300 engine intakes, measure respective drop collection coefficient, to verify that LEWICE3D programs calculate drop collection
The accuracy of coefficient.
Blotting paper staining method is simple to operate, but is limited by the limitation of blotting paper water absorbing capacity, larger to Liquid water content
Humid air, blotting paper supersaturation in the short time, so that it cannot accurate measurement.And, it is necessary to change suction under each state
Black paper, therefore different conditions can not continuously be measured.
The content of the invention
It is an object of the invention to provide a kind of method for the drop collection coefficient for measuring aerodynamic surface, this method can
Continuously measure the drop collection coefficient of the aerodynamic surface under any state, the particularly air force for survey aircraft
The drop collection coefficient on surface (for example, wing, engine intake etc.).
According to an aspect of the invention, there is provided a kind of side for being used to measure the drop collection coefficient of aerodynamic surface
Method, the described method comprises the following steps：It is described with the heating of the first power density under the dry air of specific speed and specified temp
Aerodynamic surface is to predetermined hull-skin temperature；Under the humid air of the specific speed and the specified temp, with the second work(
Rate density heats the aerodynamic surface to the predetermined hull-skin temperature, and the humid air has particular liquid water content；
And based on the specific speed, the specified temp, the Liquid water content, first power density, second work(
Rate density and the predetermined hull-skin temperature, obtain the drop collection coefficient of the aerodynamic surface.
In one embodiment, first power density is unified value, and second power density is distribution, described pre-
It is distribution to determine hull-skin temperature.
In another embodiment, first power density is distribution, and second power density is distribution, described pre-
Hull-skin temperature is determined for unified value.
The predetermined hull-skin temperature is arranged to so that the subcooled water for striking the aerodynamic surface is hitting
Locate evaporating completely.For example, the predetermined hull-skin temperature is more than 40 DEG C.
Advantageously, the obtaining step includes：
- it is based on the second power density qsWith the first power density qg, and according to following formula, calculate power density and increase
Measure Δ q
Δ q=qs-qg；
- it is based on the power density increment Delta q, the predetermined hull-skin temperature ts, the specified temp t0With it is described specific
Speed V0, and according to following formula, calculate and hit water W
Wherein described κ is coefficient of efficiency, and the power density and heating power that sign is delivered to the aerodynamic surface are close
The ratio of degree, the CwFor the specific heat of water, the LeFor the evaporation latent heat of water；
- based on the shock water W, the Liquid water content LWC and the specific speed V0, and according to following formula, calculate
The drop collection factor beta
There is provided a kind of drop collection coefficient for being used to measure aerodynamic surface according to another aspect of the present invention
System, the system includes：Heater assembly, it is arranged on the aerodynamic surface, and it is described to be configured as heating
Aerodynamic surface；Temperature sensor assembly, it is arranged on the aerodynamic surface, and is configured as measuring the sky
The hull-skin temperature of aerodynamic surfaces；And controller, it is respectively coupled to the heater assembly and the temperature sensor
Component, and be configured as：Based on the feedback of the temperature sensor assembly, control the heater assembly in specific speed and
Under the dry air of specified temp, the aerodynamic surface is heated to predetermined hull-skin temperature with the first power density；Adjustment institute
The power density of heater assembly is stated, and under the humid air of the specific speed and the specified temp, with the second power
Density heats the aerodynamic surface to the predetermined hull-skin temperature, and the humid air has particular liquid water content；With
And based on the specific speed, the specified temp, the Liquid water content, first power density, second power
Density and the predetermined hull-skin temperature, calculate the drop collection coefficient of the aerodynamic surface.
In one embodiment, first power density is unified value, and second power density is distribution, Yi Jisuo
It is distribution to state predetermined hull-skin temperature.
In another embodiment, first power density is distribution, and second power density is distribution, described pre-
Hull-skin temperature is determined for unified value.
Advantageously, the heater assembly includes one group of heating being attached on the inner surface of the aerodynamic surface
Device, the temperature sensor assembly includes one group of temperature sensor being attached on the outer surface of the aerodynamic surface, and
And each temperature sensor is correspondingly arranged on the center of each heater.
Two kinds of heating modes described above are only two embodiments for realizing the goal of the invention of the present invention, it is possible to understand that
It is that heating mode of the invention is not limited to above-mentioned ad hoc fashion.
Advantageously, the controller is configured as individually adjusting the work(of each heater in one group of heater
Rate density.
Advantageously, the system also includes：Insulating barrier, its be located at the aerodynamic surface and the heater assembly it
Between；Heat insulation layer, it is located at the heater assembly inner surface.
Brief description of the drawings
The further feature and advantage of the present invention will be more preferable by the preferred embodiment being described in detail below in conjunction with accompanying drawing
Ground understands, in accompanying drawing, and identical reference identifies same or analogous part, wherein：
Fig. 1 shows the schematic diagram of aerodynamic surface according to an embodiment of the invention；
Fig. 2 shows that the drop collection coefficient of measurement aerodynamic surface according to an embodiment of the invention is
System.
Embodiment
The structure spy according to the system of the drop collection coefficient for measuring aerodynamic surface of the invention is detailed below
Levy, operation principle and the course of work.Herein, the structural design drawing of example is used merely to facilitate the understanding present invention, rather than to this hair
Bright architectural feature makes specific restriction.In addition, in following specific descriptions, the term of directionality, such as upper and lower, top
Used etc. the direction described in equal refer to the attached drawing, the term of these directionality illustrates rather than limitation.Therefore, the knot of example
The embodiment that structure design drawing and the following description present invention are combined is not intended as all embodiments of the limit according to the present invention.
Fig. 1 shows the schematic diagram of aerodynamic surface according to an embodiment of the invention.The air of example in figure
Aerodynamic surface is aircraft wing.It is understood that the aerodynamic surface being related in the present invention is not limited to aircraft wing, its
It can also be aircraft engine air inlet etc..The technical scheme of various embodiments of the present invention is used for the exemplary air for measuring Fig. 1
The drop collection coefficient of aerodynamic surface.
The system that Fig. 2 shows the drop collection coefficient of measurement aerodynamic surface according to an embodiment of the invention
20.The system 20 includes heater assembly 201, and it is arranged on aerodynamic surface 30, the interior table of such as aerodynamic surface 30
On face 301, for heating aerodynamic surface.Advantageously, the inner surface 301 of heater assembly 201 and aerodynamic surface 30
Between can arrange an insulating barrier 205, and heater assembly 201 on the another side of aerodynamic surface 30 relative to can then arrange one
Heat insulation layer 206.
The heater assembly 201 can be for example including one group of heater.Advantageously, thermal insulation can be disposed between each heater
With insulating materials 207.Heater can be any appropriate heater element such as resistance wire, resistive film.The number of heater can be with
Determined according to the area of measured aerodynamic surface.Generally, aerodynamic surface has certain curvature (referring to Fig. 1),
Hence it is advantageous to, heater is flexible, so as to be adjacent to the inner surface of aerodynamic surface.Heater can be used
Heat conductive silica gel is bonded on the inner surface of aerodynamic surface, certainly, and other appropriate connected modes are equally applicable to heat
Device is connected on the inner surface of aerodynamic surface.
Referring now still to Fig. 2, system 20 also includes temperature sensor assembly 202, and it is arranged on aerodynamic surface 30, such as empty
On the outer surface 303 of aerodynamic surfaces 30, the hull-skin temperature for measuring aerodynamic surface.For example, temperature sensor group
Part 202 can include one group of temperature sensor.Advantageously, each temperature sensor correspondingly can be arranged in each heater
Heart position.
Temperature sensor can be the sensor of the micro volume type such as thermocouple.Temperature sensor can be using viscous
Knot or other suitable connected modes are fixed on aerodynamic surface., advantageously, can be in air in order to not influence surface flow field
Multiple grooves are set on the outer surface 303 of aerodynamic surface 30, each temperature sensor are embedded in groove, and fill heat conductive silica gel
Or milling is put down after other highly heat-conductive materials.
System 20 also includes controller 203, and it is respectively coupled to heater assembly 201 and temperature sensor assembly 202, uses
In the control heating aerodynamic surface 30 of heater assembly 201, and for obtaining the sky that temperature sensor assembly 202 is measured
The hull-skin temperature of aerodynamic surfaces 30.For example, for one group of temperature sensor in temperature sensor assembly 202, it can be with
Connecting line is set to be connected to controller 203 by the pore of respective bottom portion of groove and through the inner surface of aerodynamic surface respectively.
One group of heater in heater assembly 201 can be connected to controller by connecting line respectively.Advantageously, heater assembly
The heating power of each heater in 201 can be individually controlled by controller 203.
In operation, each heater in the control of controller 203 heater assembly 201 is in specific speed and specified temp
Dry air under, aerodynamic surface 30 is heated to predetermined hull-skin temperature with the first power density；Then controller 203 is adjusted
The power density of each heater in heater assembly 201, and in identical specific speed and identical specified temp, with
And under the humid air of particular liquid water content, aerodynamic surface 30 is heated to the predetermined outer surface temperature with the second power density
Degree.
The predetermined hull-skin temperature is arranged to so that striking the subcooled water of the aerodynamic surface at shock
Evaporating completely.For example, the predetermined hull-skin temperature is more than 40 DEG C.
In one embodiment, controller 203 controls each heater in heater assembly 201 with identical one first
Power density (that is, each power density values in the first power density are identical) heating aerodynamic surface 30 is planted, and passes through temperature
The degree measurement of sensor cluster 202 obtains predetermined hull-skin temperature.Due to the local flow field and droplets impact of aerodynamic surface
Characteristic is different, therefore, and each heater is with making a reservation for that measurement after a kind of power density heating aerodynamic surface of identical is obtained
Hull-skin temperature is distribution, that is, the hull-skin temperature of the aerodynamic surface in whole heating region is with locus
Change and it is different.Then, in identical specific speed and the humid air of identical specified temp and particular liquid water content
Under, (each power in the second power density is close to another power density for the power density of each heater of the adjustment of controller 203
Angle value is different) to heat aerodynamic surface 30, and the predetermined outer surface temperature is obtained by the measurement of temperature sensor assembly 202
Spend (that is, consistent with the hull-skin temperature being heated under dry air).
In another embodiment, controller 203 adjusts the power density of each heater in heater assembly 201 first
To heat aerodynamic surface 30, make the temperature of each measurement point identical, and made a reservation for by the measurement of temperature sensor assembly 202
Hull-skin temperature (the predetermined hull-skin temperature is that the hull-skin temperature in unified value, namely whole heating region is consistent).Due to
The local flow field of aerodynamic surface is different with Determining The Droplet Trajectories, to reach identical Temperature Distribution, each heater institute
The heating power density needed is different (that is, each power density values in the first power density are different).Then, it is special in identical
Under the humid air of constant speed degree and identical specified temp and particular liquid water content, controller 203 adjusts each heater
Power density heats aerodynamic surface 30 to the second power density (each power density values in the second power density are different),
And measured by temperature sensor assembly 202 obtain the predetermined hull-skin temperature (that is, with the outer surface that is heated under dry air
Temperature is consistent).
Finally, controller 203 is based on specific speed, specified temp, Liquid water content, the first power density, the second power
Density and predetermined hull-skin temperature, obtain the drop collection coefficient of aerodynamic surface 30.
For example, controller 203 can obtain the drop collection coefficient of aerodynamic surface 30 in the following manner.Specifically
Ground, first, controller 203 are based on the second power density qsWith the first power density qg, and according to following formula, calculate power density and increase
Measure Δ q
Δ q=qs-qg。
Then, controller 203 is based on power density increment Delta q, predetermined hull-skin temperature ts, specified temp t0With specific speed
Spend V0, and according to following formula, calculate and hit water W
Wherein, κ is coefficient of efficiency, characterizes the ratio of the power density for being delivered to aerodynamic surface and heating power density
Value, CwFor the specific heat of water, LeFor the evaporation latent heat of water.
Then, controller 203 is based on hitting water W, Liquid water content LWC and specific speed V0, and according to following formula, calculate
Drop collection factor beta
Controller 203 can be such as microprocessor.
The technology contents and technical characterstic of the present invention are had revealed that as above, it should be appreciated that above-mentioned embodiment, which exists, to be permitted
Many modification modes, these modes are apparent for various equivalent modifications.These modification/modifications fall into the present invention's
In association area, it should also in the scope for being included in appended claim.
Claims (4)
1. a kind of method for being used to measure the drop collection coefficient of aerodynamic surface, the described method comprises the following steps：
- under the dry air of specific speed and specified temp, the aerodynamic surface is heated to predetermined with the first power density
Hull-skin temperature；
- under the humid air of the specific speed and the specified temp, the air force table is heated with the second power density
Face to the predetermined hull-skin temperature, the humid air has particular liquid water content；
- it is based on the specific speed, the specified temp, the Liquid water content, first power density, second work(
Rate density and the predetermined hull-skin temperature, obtain the drop collection coefficient of the aerodynamic surface,
Wherein, the obtaining step includes：
- second power density and first power density are based on, and according to following formula, calculate power density increment
Δ q=qs-qg,
Wherein qgRepresent first power density, qsSecond power density is represented, Δ q represents power density increment；
- it is based on the power density increment, the predetermined hull-skin temperature, the specified temp and the specific speed, and root
According to following formula, calculate and hit water
Wherein tsRepresent the predetermined hull-skin temperature, t0Represent the specified temp, V0The specific speed is represented, W represents to hit
The amount of striking waters, κ is coefficient of efficiency, characterizes the ratio of the power density for being delivered to the aerodynamic surface and heating power density,
CwFor the specific heat of water, LeFor the evaporation latent heat of water；
- based on the shock water, the Liquid water content and the specific speed, and according to following formula, calculate the water droplet and receive
Collect coefficient
Wherein, LWC represents the Liquid water content, and β represents the drop collection coefficient.
2. according to the method described in claim 1, it is characterised in that the predetermined hull-skin temperature is arranged to hit
To the aerodynamic surface subcooled water at shock evaporating completely.
3. a kind of system for being used to measure the drop collection coefficient of aerodynamic surface, the system includes：
Heater assembly, it is arranged on the aerodynamic surface, and is configured as heating the aerodynamic surface；
Temperature sensor assembly, it is arranged on the aerodynamic surface, and is configured as measuring the air force table
The hull-skin temperature in face；
Controller, it is respectively coupled to the heater assembly and the temperature sensor assembly, and is configured as：
Based on the feedback of the temperature sensor assembly, the heater assembly is controlled in specific speed and the dry sky of specified temp
Under gas, the aerodynamic surface is heated to predetermined hull-skin temperature with the first power density；
The power density of the heater assembly is adjusted, and under the humid air of the specific speed and the specified temp,
The aerodynamic surface is heated to the predetermined hull-skin temperature with the second power density, the humid air has particular liquid
Water content；And
Based on the specific speed, the specified temp, the Liquid water content, first power density, second work(
Rate density and the predetermined hull-skin temperature, calculate the drop collection coefficient of the aerodynamic surface,
Wherein, the controller is configured to：
- second power density and first power density are based on, and according to following formula, calculate power density increment
Δ q=qs-qg,
Wherein qgRepresent first power density, qsSecond power density is represented, Δ q represents power density increment；
- it is based on the power density increment, the predetermined hull-skin temperature, the specified temp and the specific speed, and root
According to following formula, calculate and hit water
Wherein tsRepresent the predetermined hull-skin temperature, t0Represent the specified temp, V0The specific speed is represented, W represents to hit
The amount of striking waters, κ is coefficient of efficiency, characterizes the ratio of the power density for being delivered to the aerodynamic surface and heating power density,
CwFor the specific heat of water, LeFor the evaporation latent heat of water；
- based on the shock water, the Liquid water content and the specific speed, and according to following formula, calculate the water droplet and receive
Collect coefficient
Wherein, LWC represents the Liquid water content, and β represents the drop collection coefficient.
4. system according to claim 3, it is characterised in that the predetermined hull-skin temperature is arranged to hit
To the aerodynamic surface subcooled water at shock evaporating completely.
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| US10435161B1 (en) | 2018-05-02 | 2019-10-08 | Rosemount Aerospace Inc. | Surface sensing for droplet size differentiation |
| US11639954B2 (en) | 2019-05-29 | 2023-05-02 | Rosemount Aerospace Inc. | Differential leakage current measurement for heater health monitoring |
| US11472562B2 (en) * | 2019-06-14 | 2022-10-18 | Rosemount Aerospace Inc. | Health monitoring of an electrical heater of an air data probe |
| US11930563B2 (en) | 2019-09-16 | 2024-03-12 | Rosemount Aerospace Inc. | Monitoring and extending heater life through power supply polarity switching |
| 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 |
| CN111537182B (en) * | 2020-05-28 | 2022-03-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Power configuration method for hypersonic wind tunnel directly-heated electric heater |
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| CN202947855U (en) * | 2012-09-25 | 2013-05-22 | 南京航空航天大学 | Tester for researching on icing and anti-icing of aeroengine radome in icing wind tunnel |
| CN103759915B (en) * | 2014-01-29 | 2016-03-16 | 中国商用飞机有限责任公司 | Test measurement method for local water collection coefficient |
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