CN209102327U - A kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test - Google Patents
A kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test Download PDFInfo
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- CN209102327U CN209102327U CN201821954628.5U CN201821954628U CN209102327U CN 209102327 U CN209102327 U CN 209102327U CN 201821954628 U CN201821954628 U CN 201821954628U CN 209102327 U CN209102327 U CN 209102327U
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Abstract
A kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test, including first throat, sampling air flow channel, second throat, stationary point measuring pressure passage, stationary point pressure-measuring pipe, the second measuring pressure passage, the second pressure-measuring pipe, exhaust pipe, thermocouple；The entrance in sample gas channel is located at end of probe, and first throat is formed after entrance, forms second throat when close to probe tails, is connected in probe tails with exhaust pipe；Stationary point measuring pressure passage one end is located at end of probe, and the other end is connect in probe tail portion with stationary point pressure-measuring pipe, for measuring experimental flow field stagnation pressure；Second measuring pressure passage one end is communicated with sampling air flow channel, connects the updrift side that point is located at close second throat, and the other end is connect in probe tail portion with the second pressure-measuring pipe；Thermocouple is between the connection point and second throat in the second measuring pressure passage and sampling air flow channel.It can be used for measuring the air-flow total enthalpy of experimental flow field using electro-arc heater or engine as the pneumatic thermal protection ground simulation test of the aerospace of heat source.
Description
Technical field
The utility model relates to a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test, belong to aerospace and fly
Row device Aerodynamic Heating ground simulation test device field.
Background technique
When carrying out Aerodynamic Heating ground simulation test to aircraft, air-flow total enthalpy is to need one of important parameter to be simulated.
The development of novel hypersonic aircraft proposes more Aerodynamic Heating and thermal protection experimental technique, testing equipment and measuring technology
Newly, higher requirement, adaptable data measuring method is also required to development and improves therewith.Currently, being measured for air-flow total enthalpy
The heat-flux conditions that are applicable in of probe it is lower, and need test of many times that could obtain whole parameters needed for calculated gas flow total enthalpy,
Measured air-flow total enthalpy is usually the preceding flow field of nozzle throat in the Aerodynamic Heating ground simulation test under middle high State of Thermal Liquid Based
Average volume enthalpy.Since air-flow is during the motion to the heattransfer effect of jet pipe, have centainly in the air-flow total enthalpy of outside nozzle
Loss, and on cross section have certain distribution, especially in the case where big nozzle exit, this Distribution Effect is more
Add obvious.In the case where increasingly stringent test accuracy condition requires, the loss of this air-flow total enthalpy and Distribution Effect cannot be by
Ignore, it is therefore desirable to develop a kind of suitable for air-flow total enthalpy at each position of experimental flow field can be measured under middle high State of Thermal Liquid Based
New tool.
Utility model content
Technical problem to be solved in the utility model: in view of the deficiencies of the prior art, a kind of be used for pneumatically thermally is provided
Double venturi total enthalpy probes of face simulation test can measure test in the Aerodynamic Heating ground simulation test under middle high State of Thermal Liquid Based
Air-flow total enthalpy at each position in flow field, eliminate as air-flow during the motion to the heat transfer of various testing equipments and caused by
Measurement error reduces the influence that air-flow total enthalpy Distribution Effect generates test accuracy, and can be calculated by once testing
Whole parameters needed for air-flow total enthalpy, eliminate test of many times between equipment run unstability caused by error.
The technical solution of the utility model includes: a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test, including the
One venturi, sampling air flow channel, cooling water channel, stationary point measuring pressure passage, water inlet pipe, stationary point pressure-measuring pipe, the second measuring pressure passage, thermoelectricity
Idol, second throat, the second pressure-measuring pipe, exhaust pipe and outlet pipe；Wherein:
The entrance in sampling air flow channel is located at end of probe, after following entrance closely, after the internal diameter in sampling air flow channel reduces
Expansion forms first throat, and when close to probe tails, internal diameter is expanded after reducing again, forms second throat；In probe tail
Portion, sampling air flow channel are connected with exhaust pipe；Stationary point measuring pressure passage one end is located at end of probe, the other end probe tail portion with stay
Point pressure-measuring pipe connection；Second measuring pressure passage one end is communicated with sampling air flow channel, is connected point and is located at close to the upstream of second throat
Direction, the other end are connect in probe tail portion with the second pressure-measuring pipe；Thermocouple is located at the second measuring pressure passage and sampling air flow channel
It connects between point and second throat.
Double venturi enthalpy probes further include cooling water channel, water inlet pipe and outlet pipe, cooling water channel both ends be separately connected into
Water pipe and outlet pipe pass in and out cooling water by water inlet pipe and outlet pipe, and sampling air flow channel and stationary point measuring pressure passage are in cooling
During water channel surrounds.
The cooling water channel is the inside and outside double tubular pipeline configuration of detour, and water inlet pipe leads to internal layer, cooling water flow direction with
Sample gas flow direction is flowed out finally by outlet pipe on the contrary, cooling water is turned back in end of probe flows to the outer layer of cooling water channel.
High-pressure cooling water is passed through into cooling water channel by water inlet pipe to carry out sampling air flow channel and stationary point measuring pressure passage
It is cooling.
The sampling air flow channel is spirality pipe.
The first throat, sampling air flow channel, cooling water channel, stationary point measuring pressure passage, stationary point pressure-measuring pipe, second, which are surveyed to press, leads to
Road and second throat are integrally formed molding structure.
The integrated formed structure increases material Technology design using 3D printing metal and is fabricated.
The inner mold face of the first throat and second throat is designed using equivalent line style face Nozzle Design method.
The first throat and second throat area ratio value range are 0.51~0.83.
The probe shape is tack bicylindrical disjunctor, and sampling air flow channel and stationary point measuring pressure passage entrance are located at two cylinders
Within circle center line connecting.
The probe outer dimension, overall length are less than 300mm, and maximum outside diameter is less than 80mm.
Double venturi total enthalpy probes are made of red copper, aluminium alloy or high temperature alloy.
The utility model has the beneficial effects that
(1), the utility model increases the manufacture of material Technology design using 3D printing metal, which can be by first throat, sampling
The part such as airflow channel, cooling water channel, stationary point measuring pressure passage, the second measuring pressure passage and second throat is integrated in one, therefore can
By whole parameters needed for once testing acquisition calculated gas flow total enthalpy, the unstability that equipment is run between elimination test of many times is made
At error, and the design cycle can be effectively shortened, the intensity and reliability of lifting component integrated level and reinforcement structure.；
(2), the utility model cools down gas sampled using high pressure water, so as under middle high State of Thermal Liquid Based
Experimental flow field air-flow total enthalpy is measured in Aerodynamic Heating ground simulation test, to eliminate since air-flow is during the motion to examination
Test the heat transfer of equipment and caused by measurement error；
(3) the utility model is designed using spiral shape sampling air flow channel, and cooling cooling with bilayer using reverse flow
Sample gas is more efficiently cooled under the maximum temperature of sample requirement by structure；
(4), the utility model is using equivalent line style face Nozzle Design method design first throat and second throat, optimization sampling
Airflow channel flow field structure improves gas-flow measurement result accuracy；
(5) the utility model uses tack bicylindrical disjunctor shape, sampling air flow channel and stationary point measuring pressure passage entrance position
Within two cylinder circle center line connectings, under the premise of probe end hot-fluid is effectively reduced, guarantee sampling air flow parameter measurements
Accuracy and validity；
It (6), being capable of meter calculating by laying probe provided by the utility model at each position of experimental flow field
Air-flow total enthalpy at each position of experimental flow field is distributed to obtain the radial air-flow total enthalpy with axial cross section of experimental flow field, subtracts
The influence that little airflow total enthalpy Distribution Effect generates test accuracy.
Detailed description of the invention
Fig. 1 is double venturi total enthalpy probe side view structure diagrammatic cross-sections of the utility model, and arrow direction is cooling in figure
Water flow to.
Fig. 2 is double venturi total enthalpy probe plan structure diagrammatic cross-sections of the utility model, and arrow direction is cooling in figure
Water flow to.
Fig. 3 is the outline structural diagram of the utility model, and it is internal structure that light lines, which sketch out, in figure.
Specific embodiment
Below in conjunction with attached drawing and specific implementation, the utility model is described in more detail.
The present invention provides a kind of double venturi total enthalpy probes for Aerodynamic Heating ground simulation test, institutes as shown in Figure 1, Figure 2
Show, including first throat 1, sampling air flow channel 2, cooling water channel 3, stationary point measuring pressure passage 4, water inlet pipe 5, stationary point pressure-measuring pipe 6,
Two measuring pressure passages 7, thermocouple 8, second throat 9, the second pressure-measuring pipe 10, exhaust pipe 11 and outlet pipe 12.
The entrance in sampling air flow channel 2 is located at end of probe, and after following entrance closely, the internal diameter in sampling air flow channel 2 reduces
After expand, formed first throat 1, when close to probe tails, internal diameter is expanded after reducing again, formation second throat 9；In probe
Tail portion, sampling air flow channel 2 are connected with exhaust pipe 11；Measuring pressure passage 4 one end in stationary point is located at end of probe, and the other end is in probe tail
Portion is connect with stationary point pressure-measuring pipe 6；Second measuring pressure passage, 7 one end is communicated with sampling air flow channel 2, is connected point and is located at close to the second larynx
The updrift side in road 9, the other end are connect in probe tail portion with the second pressure-measuring pipe 10；Thermocouple 8 is located at the second measuring pressure passage 7 and adopts
Between the connection point and second throat 9 of sample airflow channel 2.3 both ends of cooling water channel are separately connected water inlet pipe 5 and outlet pipe 12, lead to
It crosses water inlet pipe 5 and outlet pipe 12 passes in and out cooling water, sampling air flow channel 2 and stationary point measuring pressure passage 4 are in the encirclement of cooling water channel 3
In.
Specifically, be continually fed into high pressure water into cooling water channel 3 from water inlet pipe 5 when probe face, and from 12 row of outlet pipe
Out.When probe is placed in experimental flow field, it is total through stationary point pressure-measuring pipe 6 experimental flow field air-flow can be measured by stationary point measuring pressure passage 4
Pressure.When air-flow enters sampling air flow channel 2, the sample gas flow in sampling air flow channel 2 is entered by the limitation of first throat 1.Through
Sample gas becomes the velocity of sound when crossing first throat 1, and is expanded into spiral shape sampling air flow channel 2, the height in cooling water channel 3
580K is cooled fast under pressure water cooling effect hereinafter, and making gas velocity be reduced to the velocity of sound hereinafter, heat before second throat 9
Sample gas temperature is measured at galvanic couple 8, measures sample gas pressure through the second pressure-measuring pipe 10 at the second measuring pressure passage 7, later
Sample gas becomes the velocity of sound again at second throat 9, and is expanded into the discharge of exhaust pipe 11.According to sample gas in the first larynx
Road 1 and speed at second throat 9 are the velocity of sound and the identical feature of flow, the experimental flow field air-flow stagnation pressure obtained by measurement, and
The area of sampling air flow temperature and pressure and first throat 1 and second throat 9 before two venturis 9, calculates experimental flow field gas
The total enthalpy of stream.
When experimental flow field air-flow total enthalpy is 5.8 × 102KJ/kg~2.3 × 103When within the scope of kJ/kg, double venturi enthalpy probes
Working strategy formula it is as follows:
Wherein:
H0- experimental flow field air-flow total enthalpy, unit: kJ/kg；
P0- experimental flow field air-flow stagnation pressure, unit: Pa；
Sampling air flow pressure before P-second throat, unit: Pa；
A1 *The sectional area of-first throat, unit: m2；
A2 *The sectional area of-second throat, unit: m2；
Sampling air flow temperature before T-second throat, unit: K.
When experimental flow field air-flow total enthalpy is 2.3 × 103KJ/kg~2.3 × 104When within the scope of kJ/kg, double venturi enthalpy probes
Working strategy formula it is as follows:
Physical quantity unit is identical as (1) formula in formula.
Preferably, the structure increases material Technology design using 3D printing metal and is fabricated, which can be by the first larynx
Road 1, sampling air flow channel 2, cooling water channel 3, stationary point measuring pressure passage 4, stationary point pressure-measuring pipe 6, the second measuring pressure passage 7 and second throat
9 are integrally formed molding structure, and can effectively shorten the design cycle, the intensity of lifting component integrated level and reinforcement structure and reliable
Property.
Preferably, when the probe 3D printing metal increases material Technology design, overall length is less than 300mm, and maximum outside diameter is less than
80mm, when manufacture, red copper, aluminium alloy or high temperature alloy can be selected in metal material used.
Preferably, the cooling water channel 3 is the inside and outside double tubular pipeline configuration of detour, and water inlet pipe 5 leads to internal layer, cooling
Water flow to sample gas flow direction on the contrary, cooling water is turned back in end of probe flows to the outer layer of cooling water channel 3, finally by going out
Water pipe 12 flows out.The sampling air flow channel 2 is spirality pipe.This reverse flow cooling and double-layer cooling structure, in addition
The cooling heat transferring area that helical structure is significantly increased can be more efficiently cooling by sample gas under the cooling of high pressure water
To the maximum temperature of sample requirement, and test can be flowed in the Aerodynamic Heating ground simulation test under middle high State of Thermal Liquid Based
Field air-flow total enthalpy measures.
Preferably, the first throat 1 and second throat 9 are using equivalent line style face Nozzle Design method design.Optimization sampling
Airflow channel flow field structure improves gas-flow measurement result accuracy.The first throat 1 and 9 area ratio of second throat
Value range is 0.51~0.83.
As shown in figure 3, the probe shape is tack bicylindrical disjunctor, sampling air flow channel 2 and stationary point measuring pressure passage 4 enter
Mouth is located within two cylinder circle center line connectings.Under the premise of probe end hot-fluid is effectively reduced, guarantee sampling air flow parameter measurement
As a result accuracy and validity.
The probe is arranged in each position in the radial and axial section of experimental flow field, each position of experimental flow field can be measured
The air-flow total enthalpy at place is set, is distributed to obtain the radial air-flow total enthalpy with axial cross section of experimental flow field, reduces the distribution of air-flow total enthalpy
The influence that effect generates wind tunnel test precision.
The specific structure of the utility model illustrates and verification experimental verification all demonstrates the utility model and has the special feature that, Neng Gou
In Aerodynamic Heating ground simulation test under middle high State of Thermal Liquid Based measure each position of experimental flow field at air-flow total enthalpy, eliminate due to
Air-flow during the motion to the heat transfer of various testing equipments and caused by measurement error, reduce air-flow total enthalpy Distribution Effect to examination
The influence of precision generation is tested, and test of many times can be eliminated by parameter needed for a test measurement whole calculated gas flow total enthalpy
Between equipment run unstability caused by error.
The above is only the preferred embodiment of the present invention, is not used to limit the protection scope of the utility model.
For those skilled in the art, without creative efforts, the utility model can be made several
Modification and replacement, all such modifications and replacement should be covered within the scope of the utility model.
Claims (12)
1. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test, it is characterised in that: including first throat (1), adopt
Sample airflow channel (2), cooling water channel (3), stationary point measuring pressure passage (4), water inlet pipe (5), stationary point pressure-measuring pipe (6), second, which are surveyed to press, leads to
Road (7), thermocouple (8), second throat (9), the second pressure-measuring pipe (10), exhaust pipe (11) and outlet pipe (12)；Wherein:
The entrance in sampling air flow channel (2) is located at end of probe, and after following entrance closely, the internal diameter of sampling air flow channel (2) reduces
After expand, formed first throat (1), when close to probe tails, internal diameter is expanded after reducing again, formation second throat (9)；?
Probe tails, sampling air flow channel (2) are connected with exhaust pipe (11)；Measuring pressure passage (4) one end in stationary point is located at end of probe, another
End is connect in probe tail portion with stationary point pressure-measuring pipe (6)；Second measuring pressure passage (7) one end is communicated with sampling air flow channel (2), is connected
Point is located at the updrift side close to second throat (9), and the other end is connect in probe tail portion with the second pressure-measuring pipe (10)；Thermocouple
(8) between the connection point and second throat (9) of the second measuring pressure passage (7) and sampling air flow channel (2).
2. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 1, it is characterised in that
It further include cooling water channel (3), water inlet pipe (5) and outlet pipe (12), cooling water channel (3) both ends are separately connected water inlet pipe (5) and go out
Water pipe (12) passes in and out cooling water, sampling air flow channel (2) and stationary point measuring pressure passage (4) by water inlet pipe (5) and outlet pipe (12)
In cooling water channel (3) encirclement.
3. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 2, it is characterised in that
The cooling water channel (3) is the inside and outside double tubular pipeline configuration of detour, and water inlet pipe (5) leads to internal layer, and cooling water is flowed to and adopted
Sample gas flow flows to the outer layer of cooling water channel (3) on the contrary, cooling water is turned back in end of probe, flows finally by outlet pipe (12)
Out.
4. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 2, it is characterised in that
High-pressure cooling water is passed through to sampling air flow channel (2) and stationary point measuring pressure passage (4) into cooling water channel (3) by water inlet pipe (5)
It is cooled down.
5. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 1, it is characterised in that
The sampling air flow channel (2) is spirality pipe.
6. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 1, it is characterised in that:
The first throat (1), sampling air flow channel (2), cooling water channel (3), stationary point measuring pressure passage (4), stationary point pressure-measuring pipe (6),
Two measuring pressure passages (7) and second throat (9) are integrally formed molding structure.
7. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 6, it is characterised in that:
The integrated formed structure increases material Technology design using 3D printing metal and is fabricated.
8. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 6, it is characterised in that:
The inner mold face of the first throat (1) and second throat (9) is designed using equivalent line style face Nozzle Design method.
9. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 1, it is characterised in that:
The first throat (1) and second throat (9) area ratio value range are 0.51~0.83.
10. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 1, feature exist
In: the probe shape is tack bicylindrical disjunctor, and sampling air flow channel (2) and stationary point measuring pressure passage (4) entrance are located at two circles
Within column circle center line connecting.
11. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 7, feature exist
In: the probe outer dimension, overall length are less than 300mm, and maximum outside diameter is less than 80mm.
12. a kind of double venturi enthalpy probes for Aerodynamic Heating ground simulation test according to claim 7, feature exist
In: it is made of red copper, aluminium alloy or high temperature alloy.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110697076A (en) * | 2019-10-21 | 2020-01-17 | 中国航天空气动力技术研究院 | Integrated throat model support rod for subsonic velocity shroud ablation test |
| CN110712764A (en) * | 2019-10-21 | 2020-01-21 | 中国航天空气动力技术研究院 | Subsonic velocity envelope ablation test device used under high enthalpy condition |
| CN112747886A (en) * | 2020-12-29 | 2021-05-04 | 中国航天空气动力技术研究院 | Thin-wall throat |
-
2018
- 2018-11-26 CN CN201821954628.5U patent/CN209102327U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110697076A (en) * | 2019-10-21 | 2020-01-17 | 中国航天空气动力技术研究院 | Integrated throat model support rod for subsonic velocity shroud ablation test |
| CN110712764A (en) * | 2019-10-21 | 2020-01-21 | 中国航天空气动力技术研究院 | Subsonic velocity envelope ablation test device used under high enthalpy condition |
| CN112747886A (en) * | 2020-12-29 | 2021-05-04 | 中国航天空气动力技术研究院 | Thin-wall throat |
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