CN107631753A - A kind of aviation turbojet engine wake flow field test device - Google Patents
A kind of aviation turbojet engine wake flow field test device Download PDFInfo
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- CN107631753A CN107631753A CN201710838831.XA CN201710838831A CN107631753A CN 107631753 A CN107631753 A CN 107631753A CN 201710838831 A CN201710838831 A CN 201710838831A CN 107631753 A CN107631753 A CN 107631753A
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- measurement
- rake
- flow field
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Abstract
The present invention proposes a kind of aviation turbojet engine wake flow field test device, and the device includes measurement in a closed series rake, measurement rake mounting bracket, mounting bracket fixing device.Temperature probe and pressure measurement probe are disposed with measurement in a closed series rake, measurement in a closed series rake is fixed on measurement rake mounting bracket by coaster, moves left and right coaster, can obtain the Flow Field Distribution on vertical gas stream interface.Measurement rake mounting bracket is linked by long cap cable with earth anchor, by traverse measurement rake mounting bracket in the position in wake flow direction, can obtain the Flow Field Distribution of engine wake flow different cross section.The device of the present invention proposes new solution for the test of turbojet tail flow field, is effectively improved the measurement accuracy of temperature field, pressure field and velocity field, and the infrared signature for accurate analysis engine provides technical support.
Description
Technical field
The present invention relates to infrared test technology, and in particular to aviation turbojet engine infrared signature experiment
Wake flow field test device.
Background technology
China promulgated GJB241-87 from 1987, and the whirlpool newly developed is defined to military aviation turbojet
Wheel jet engine must carry out the test requirements document of infrared signature.Large-scale turbojet exhaust tail flow has height
Speed, the features such as high temperature and flow field scope are big, measurement apparatus needs to bear larger airload and thermic load in flow field is put into.
At present when carrying out the experiment of turbojet exhaust tail flow infrared signature, typically using netted rectangular grid
Grid measurement rake, including pressure measxurement rake and temperature survey rake, net is separately fixed at by pressure measxurement probe and temperature measurement probe
On shape square-grid, this mode is because netted square-grid quantity is more (measurement rake is more), and occupancy flow field area is big, measurement rake pair
The ponding of air-flow is obvious, influences measurement accuracy；And in order to bear larger airload, the volume of supporting construction
Also it is very big, the ponding increased to air-flow further.
It is domestic at present still without special infrared radiation of engine characteristic test test equipment, special test place and accordingly
Experiment test technology, although also having carried out the work of substantial amounts of numerical simulation and small-scale test research, obtained many valuable
Achievement in research, but on the whole, do not form systemic achievement also, technology maturity is relatively low, most computation models
Lack the checking of real engine measurement data, model and actual conditions have a different, and the confidence level of result of calculation is not high.This
A little factors have impact on exploitation and amendment that domestic infra-red radiation calculates model and software, and it is red seriously to constrain military aero-engine
The development of outer stealth technology.Therefore using actual aero-engine as experiment porch, rake technology is measured using multifunctional combination, carried out
Aviation turbojet engine infrared signature experimental study is significant.
The content of the invention
The present invention is aiming at the existing problems and shortcomings of the prior art, it is proposed that a kind of aviation turbojet engine tail flow field
Test device.The device moves left and right measurement rake, movable measurement rake mounting bracket by coaster, realizes that gamut tail flow field is surveyed
Examination, avoids the blocking to air-flow, improves measurement accuracy, and can meet high speed, high temperature gas flow, high under a wide range of environment
The test request of precision.
The technical scheme is that：
A kind of aviation turbojet engine wake flow field test device, it is characterised in that：Harrow, survey including measurement in a closed series
Amount rake mounting bracket and mounting bracket fixing device；
The measurement in a closed series rake is the tubular structure of one end closing, is provided with measurement in a closed series rake side wall some towards same
The temperature survey hole in direction and pick-up hole, temperature measurement probe is installed in temperature survey hole, installed in pick-up hole
There is pressure measxurement probe；An adjacent temperature survey hole and a pick-up hole forms a measuring unit, a measurement
The pitch-row of temperature survey hole and pick-up hole is not more than 10mm in unit；
The measurement rake mounting bracket includes supporting steel structure, coaster, guide rail and transmission mechanism；The vertical peace of measurement in a closed series rake
On coaster, and the direction of flow in the measuring unit face test flow field on measurement in a closed series rake；Measurement in a closed series rake passes through more
Support bar is supported, and support bar is in both sides and the back side of the measurement in a closed series rake relative to direction of flow；The coaster is in
On guide rail inside supporting steel structure, the transmission mechanism can move with fly block along guide rail；The guide rail flows perpendicular to test
The direction of flow of field；
The mounting bracket fixing device includes fastening stake, earth anchor and cable wire；Supporting steel structure both ends are fixed on by fastening stake
On installation base surface；Earth anchor is additionally provided with installation base surface, in one side of the supporting steel structure towards test flow field direction of flow, is led to
Long cable traction supporting steel structure top and earth anchor, supporting steel structure bottom and earth anchor are drawn by cap cable.
Further preferred scheme, a kind of aviation turbojet engine wake flow field test device, it is characterised in that：
All temperature survey holes are axially spacedly distributed along measurement in a closed series rake, and all pick-up holes are harrowed axially at equal intervals along measurement in a closed series
Distribution.
Further preferred scheme, a kind of aviation turbojet engine wake flow field test device, it is characterised in that：
The coaster buries mode inside supporting steel structure in using, and on the guide rail in supporting steel structure, the transmission mechanism
It can be moved with fly block along guide rail.
Further preferred scheme, a kind of aviation turbojet engine wake flow field test device, it is characterised in that：
The supporting steel structure is in the lower section plume of test flow field incoming.
Further preferred scheme, a kind of aviation turbojet engine wake flow field test device, it is characterised in that：
Temperature measurement probe uses the K-type thermocouple of armouring, and pressure measxurement probe uses Pitot tube.
Further preferred scheme, a kind of aviation turbojet engine wake flow field test device, it is characterised in that：
Radome for reducing radiation error is installed outside temperature measurement probe.
Beneficial effect
The advantage of the invention is that：On the measurement in a closed series rake of single tube form several temperature have been sequentially arranged by equi-spaced apart
Spend measuring probe and several pressure measxurements are popped one's head in, can be flowed by the way that moving left and right for coaster and supporting steel structure are movable
The gamut measurement of field, avoids the problem of netted square-grid large area takes flow field channel, has both been subtracted using such layout
The quantity of measurement rake is lacked, has greatly reduced the interference of measurement rake convection current field measurement again, that is, improve measurement accuracy.It is meanwhile right
The probe of measurement in a closed series rake is designed, i.e., carries out pressure measxurement using the measurement form of Pitot tube, using the K-type heat of armouring
Galvanic couple carries out temperature survey, makes the upper temperature measurement probe of measurement in a closed series rake and pressure measxurement probe near enough, on so each point
The speed being calculated can preferably reflect the true velocity of the point, that is, improve the measurement accuracy of velocity field.Secondly, it is such
Layout avoids one section of every measurement, and engine will stop, and after fixing netted square-grid, carries out engine again and rises
Dynamic, warming-up, carry out testing such a repetitive process again after reaching designated state, greatly reduce engine test time and
Number, reduce fuel consumption, i.e. economy is improved.
The additional aspect and advantage of the present invention will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Brief description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become in the description from combination accompanying drawings below to embodiment
Substantially and it is readily appreciated that, wherein：
Fig. 1：A kind of aviation turbojet engine wake flow field test device structural representation.
Including：1. measurement in a closed series is harrowed；2. temp probe；3 pressure probes；4. coaster；5. supporting steel structure；6. guide rail；7. pass
Dynamic chain；8. earth anchor；9. cable wire.
Embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from beginning to end
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to for explaining the present invention, and is not considered as limiting the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise " are based on orientation shown in the drawings or position relationship, are for only for ease of
Description is of the invention to be described with simplified, rather than the device or element of instruction or hint meaning must be with specific orientation, Yi Te
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
As shown in figure 1, a kind of aviation turbojet engine wake flow field test device in the present embodiment, including combination are surveyed
Amount rake, measurement rake mounting bracket and mounting bracket fixing device.
The measurement in a closed series rake is the tubular structure of one end closing, is provided with measurement in a closed series rake side wall towards same direction
5 temperature survey holes and 5 pick-up holes, temperature measurement probe is installed in temperature survey hole, pacified in pick-up hole
Popped one's head in equipped with pressure measxurement, it is contemplated that the degree of accuracy of flow field survey, pressure measxurement probe measure stagnation pressure and static pressure simultaneously, and temperature is surveyed
The outer radome being provided with for reducing radiation error of amount probe, reduce the air velocity of measuring point impression.Temperature in the present embodiment
Measuring probe uses the K-type thermocouple of armouring, and pressure measxurement probe uses Pitot tube.
5 temperature survey holes are axially spacedly distributed along measurement in a closed series rake, and 5 pick-up holes are harrowed axially along measurement in a closed series
It is spacedly distributed.An adjacent temperature survey hole and a pick-up hole forms a measuring unit, a measuring unit
The pitch-row of interior temperature survey hole and pick-up hole is not more than 10mm.A middle measuring unit is in aeroturbine jet and started
Tail jet pipe position of center line.Measurement in a closed series rake in the present embodiment avoids netted square-grid large area and takes flow field channel
Deficiency.
The measurement rake mounting bracket includes supporting steel structure, coaster, guide rail and transmission mechanism；The vertical peace of measurement in a closed series rake
On coaster, and the direction of flow in the measuring unit face test flow field on measurement in a closed series rake；Measurement in a closed series rake passes through three
Support bar is supported by the way of supported at three point, and support bar be in measurement in a closed series rake relative to direction of flow both sides and
The back side, avoid impacting incoming, and measurement in a closed series can be improved and harrow the fixed degree in high velocity air；The cunning
Car buries mode inside supporting steel structure, and on the guide rail in supporting steel structure in using, and the transmission mechanism being capable of band
Fly block moves along guide rail；Direction of flow of the guide rail perpendicular to test flow field；In the present embodiment, coaster moves along guide rail
Maximum moving distance is-2 -+2 meters, can so measure the Flow Field Distribution on vertical gas stream interface, and is moved along before and after direction of flow
Dynamic supporting steel structure can measure the Flow Field Distribution of engine wake flow different cross section.
The mounting bracket fixing device includes fastening stake, earth anchor and cable wire.Supporting steel structure both ends are fixed on by fastening stake
On installation base surface；Earth anchor is additionally provided with installation base surface, in one side of the supporting steel structure towards test flow field direction of flow, is led to
Long cable traction supporting steel structure top and earth anchor, supporting steel structure bottom and earth anchor are drawn by cap cable.Due to aeroturbine
The exhaust velocity of jet engine nozzle is up to 0.8 Mach, and resulting aerodynamic force reaches up to ten thousand kilograms, such fixation side
Formula, on the one hand reduce the influence of high-frequency excitation stream field measurement accuracy caused by high velocity air, on the other hand make supporting steel structure
It is able to firm fixation.
The supporting steel structure is in the lower section plume of test flow field incoming, such device and layout, is on the one hand reduced
The quantity of flow field survey rake, on the other hand reduces the interference of structure stream field, improves measurement accuracy.
The present invention operation principle be：(calibration) temperature recovery coefficient is tested using hot air wind tunnel, utilizes measurement in a closed series
Stagnation temperature pops one's head in obtain stagnation temperature on rake, thus calculates the static temperature of air-flow；Upper pressure probe, which is harrowed, using measurement in a closed series obtains air-flow
Total static pressure, using the correlation between total static pressure and static temperature, the M numbers and velocity coeffficient λ of air-flow can be calculated, you can really
Make the size of air velocity.Utilize moving left and right for measurement in a closed series rake set a distance, you can obtain the temperature on vertical gas stream interface
Field, pressure field and speed field distribution.Utilize the movable of measurement rake mounting bracket, you can obtain different sections of engine wake flow direction
Temperature field, pressure field and the speed field distribution in face.
When jet flow field is tested, measurement in a closed series rake is fixed on measurement rake mounting bracket first, measurement rake mounting bracket is consolidated
It is scheduled in mounting bracket fixing device, checks coaster situation of movement, determines the position of measurement rake mounting bracket (such as distance by test requirements document
Engine tail nozzle 5m, coaster is in the position of nozzle middle 0), you can the engine for carrying out the position drives to test.Pass through a left side
Fly block is moved to right, the Flow Field Distribution on vertical gas stream interface can be obtained；Traverse measurement harrows mounting bracket in wake flow direction diverse location
(such as apart from engine tail nozzle 8m), with the method for equally moving left and right coaster, you can obtain engine wake flow different cross section
Flow Field Distribution.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is not departing from the principle and objective of the present invention
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (6)
- A kind of 1. aviation turbojet engine wake flow field test device, it is characterised in that：Harrowed including measurement in a closed series, measurement rake peace Shelve and mounting bracket fixing device；The measurement in a closed series rake is the tubular structure of one end closing, is provided with measurement in a closed series rake side wall some towards same direction Temperature survey hole and pick-up hole, temperature measurement probe is installed in temperature survey hole, pressure is installed in pick-up hole Power measuring probe；An adjacent temperature survey hole and a pick-up hole forms a measuring unit, a measuring unit The pitch-row of interior temperature survey hole and pick-up hole is not more than 10mm；The measurement rake mounting bracket includes supporting steel structure, coaster, guide rail and transmission mechanism；The measurement in a closed series rake is vertically installed at On coaster, and the direction of flow in the measuring unit face test flow field on measurement in a closed series rake；Measurement in a closed series rake passes through more supports Bar is supported, and support bar is in both sides and the back side of the measurement in a closed series rake relative to direction of flow；The coaster is in support On guide rail inside steel structure, the transmission mechanism can move with fly block along guide rail；The guide rail is perpendicular to test flow field Direction of flow；The mounting bracket fixing device includes fastening stake, earth anchor and cable wire；Supporting steel structure both ends are fixed on installation by fastening stake On basal plane；Earth anchor is additionally provided with installation base surface, in one side of the supporting steel structure towards test flow field direction of flow, passes through length Cable traction supporting steel structure top and earth anchor, supporting steel structure bottom and earth anchor are drawn by cap cable.
- A kind of 2. aviation turbojet engine wake flow field test device according to claim 1, it is characterised in that：All temperature Degree measured hole is axially spacedly distributed along measurement in a closed series rake, and all pick-up holes are axially spacedly distributed along measurement in a closed series rake.
- A kind of 3. aviation turbojet engine wake flow field test device according to claim 1, it is characterised in that：The cunning Car buries mode inside supporting steel structure, and on the guide rail in supporting steel structure in using, and the transmission mechanism being capable of band Fly block moves along guide rail.
- A kind of 4. aviation turbojet engine wake flow field test device according to claim 3, it is characterised in that：The branch Steel structure is supportted to be in the lower section plume of test flow field incoming.
- A kind of 5. aviation turbojet engine wake flow field test device according to claim 2, it is characterised in that：Temperature is surveyed Amount probe uses the K-type thermocouple of armouring, and pressure measxurement probe uses Pitot tube.
- A kind of 6. aviation turbojet engine wake flow field test device according to claim 5, it is characterised in that：Temperature is surveyed The outer radome being provided with for reducing radiation error of amount probe.
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| CN201710838831.XA CN107631753A (en) | 2017-09-18 | 2017-09-18 | A kind of aviation turbojet engine wake flow field test device |
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| CN201710838831.XA CN107631753A (en) | 2017-09-18 | 2017-09-18 | A kind of aviation turbojet engine wake flow field test device |
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| CN201710838831.XA Pending CN107631753A (en) | 2017-09-18 | 2017-09-18 | A kind of aviation turbojet engine wake flow field test device |
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| CN108709576A (en) * | 2018-06-05 | 2018-10-26 | 中国航发沈阳发动机研究所 | A kind of rake instrument |
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| CN110044549A (en) * | 2019-04-10 | 2019-07-23 | 常州大学 | A kind of experimental provision leaked for studying underwater gas |
| CN110441023A (en) * | 2019-07-30 | 2019-11-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of miniature measurement rake and its 3D printing method for wind tunnel test |
| CN112033688A (en) * | 2020-05-26 | 2020-12-04 | 中国科学院工程热物理研究所 | System for measuring temperature flow field outside jet lobe of aircraft engine and control method thereof |
| CN114459768A (en) * | 2022-02-09 | 2022-05-10 | 绵阳诺达佳工业控制技术有限公司 | Engine ground flow field testing device |
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Cited By (10)
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| CN108760221A (en) * | 2018-05-31 | 2018-11-06 | 北京空天技术研究所 | Wind tunnel test guiding device |
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| CN110441023A (en) * | 2019-07-30 | 2019-11-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of miniature measurement rake and its 3D printing method for wind tunnel test |
| CN112033688A (en) * | 2020-05-26 | 2020-12-04 | 中国科学院工程热物理研究所 | System for measuring temperature flow field outside jet lobe of aircraft engine and control method thereof |
| CN112033688B (en) * | 2020-05-26 | 2022-02-15 | 中国科学院工程热物理研究所 | System for measuring temperature flow field outside jet lobe of aircraft engine and control method thereof |
| CN114459768A (en) * | 2022-02-09 | 2022-05-10 | 绵阳诺达佳工业控制技术有限公司 | Engine ground flow field testing device |
| CN114459768B (en) * | 2022-02-09 | 2023-11-14 | 绵阳诺达佳工业控制技术有限公司 | Engine ground flow field testing device |
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Application publication date: 20180126 |