CN205670075U - A kind of airplane intake exit flow field measuring mechanism - Google Patents
A kind of airplane intake exit flow field measuring mechanism Download PDFInfo
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- CN205670075U CN205670075U CN201620379695.3U CN201620379695U CN205670075U CN 205670075 U CN205670075 U CN 205670075U CN 201620379695 U CN201620379695 U CN 201620379695U CN 205670075 U CN205670075 U CN 205670075U
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- support plate
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- pressure
- measurement mouth
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- 238000012360 testing method Methods 0.000 claims abstract description 49
- 238000005259 measurement Methods 0.000 claims abstract description 29
- 238000003466 welding Methods 0.000 claims abstract description 22
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims abstract description 18
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 13
- 239000000741 silica gel Substances 0.000 claims abstract description 12
- 229910002027 silica gel Inorganic materials 0.000 claims abstract description 12
- 238000009530 blood pressure measurement Methods 0.000 claims abstract description 11
- 229910052786 argon Inorganic materials 0.000 claims abstract description 9
- 238000012856 packing Methods 0.000 claims abstract description 9
- 238000007789 sealing Methods 0.000 claims description 5
- 230000010412 perfusion Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 5
- 239000000523 sample Substances 0.000 description 14
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 239000012141 concentrate Substances 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910000679 solder Inorganic materials 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000005496 tempering Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 230000001869 rapid Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
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- Measuring Fluid Pressure (AREA)
Abstract
The utility model discloses a kind of airplane intake exit flow field measuring mechanism, including the test support plate being arranged on inlet casing support plate, it is provided with measuring point on described test support plate, measured hole is offered at measuring point, it is provided with locating piece in described measured hole, locating piece is provided with measurement mouth, on described measurement mouth, dynamic pressure transducer is installed, stable state pressure measurement mouth and pressure-measuring pipe it is additionally provided with on described locating piece, described pressure-measuring pipe uses argon arc welding to be welded on measurement mouth, described dynamic pressure transducer is arranged on inside measurement mouth by packing ring, and with silica gel, dynamic pressure transducer is fixed on packing ring.Use measurement apparatus described in the utility model, take up room at external engine little, be increased without the technique air intake duct of special measurement, it is easy to accomplish；Structurally the space between test support plate and inlet casing support plate is relatively big, can lay the dynamic measuring point of multiple spot according to actual needs, there is not wire and pressure-measuring pipe etc. and lays the problem that time space is not enough.
Description
Technical field
This utility model belongs to field of measuring technique, is specifically related to a kind of airplane intake exit flow field measuring mechanism.
Background technology
In technical field of aerospace, part aircraft is when carrying out high-speed agility flight, and aeroplane nose often can produce the most quick-fried
Sound, send inside air intake duct " too " sound so that engine speed extremely unstable, little time big during thrust, through ground
The result checked shows that the main cause producing above-mentioned strong sonic boom is the matching problem between airplane intake and electromotor.Cause
This, the research and development of aircraft and electromotor are brought in airplane intake and engine compatibility design, checking into initially as key link
In system, domestic and international aero-engine expert is it is well recognized that the importance of air inlet/engine Compatibility Evaluation, and examines
One of important indicator of matching is exactly the synthetic distortion index in air intake port flow field.
Along with complexity, the raising day by day of mobility of aircraft aerodynamic configuration, air intake port flow field quality is to electromotor
The effect of work influence gradually manifests, and becomes one of principal element affecting electromotor job stability, due to modern computing
Machine emulation technology application in terms of flow field simulation, it is possible to have some reference values, actual in view of fluid boundary-layer and rapids
Stream cannot simulate (i.e. the turbulence level in flow field), so needing to measure the real flow field condition of air intake duct by test.
At present, the means measuring flow field aboard typically use insertion probe, it is contemplated that probe blockage ratio pair
The impact in flow field, and probe self fundamental frequency safety effects to electromotor close with engine speed operating frequency；
It is additionally inserted into formula probe exterior part and accounts for the space of electromotor profile, and cannot be internally installed more dynamic at insertion probe
State sensor so that dynamically measure-point amount is less, it is impossible to preferably reflect the turbulence level situation in flow field.
Utility model content
For solving above-mentioned technical problem, this utility model provides a kind of airplane intake exit flow field measuring mechanism, from
And reduce the impact of probe self-convection field, it is possible to and true and accurate reflection flow field actual state, overcome conventional probe measurement side
The deficiency that method cannot be installed because of external engine insufficient space.
This utility model is achieved by the following technical programs.
A kind of airplane intake exit flow field measuring mechanism, including the test support plate being arranged on inlet casing support plate 1, institute
State and be provided with measuring point on test support plate, at measuring point, offer measured hole, be provided with locating piece in described measured hole, at locating piece
On be provided with measurement mouth, described measurement mouth is provided with dynamic pressure transducer, described locating piece is additionally provided with stable state pressure measurement
Mouth and pressure-measuring pipe.
Described pressure-measuring pipe uses argon arc welding to be welded on measurement mouth.
Described dynamic pressure transducer is arranged on inside measurement mouth by packing ring, and with silica gel, dynamic pressure transducer is solid
It is scheduled on packing ring.
The wire of described pressure-measuring pipe and dynamic pressure transducer is fixed along test support plate through the installing hole on inlet casing,
And before welding at test intralaminar part perfusion silica gel sealing.
Described using welding manner to fix test support plate and inlet casing support plate, wherein test support plate and inlet casing prop up
The weld seam of plate initiates with inside and outside casing connecting portion from test support plate, and every section of a length of 20-25mm of weld seam, spacing is 8-10mm.
Described weld seam does not highlights the surface of test support plate, and X-ray examination is all used at the continuous position of weld seam.
The beneficial effects of the utility model are:
Compared with prior art, use measurement apparatus described in the utility model that airplane intake exit flow field is carried out right
Ratio, has a following remarkable advantage:
(1) this utility model is compared with employing probe measurement flow field mode, takes up room at external engine little, need not increase
Add the technique air intake duct of special measurement, it is easy to accomplish；At engine interior, to engine charge casing support plate the most in the axial direction
Lengthening, the blockage ratio of stream field can be ignored substantially, traditional socle beam probe and double fixed pivot probe, is all difficult to disappear
Except probe fundamental frequency can not avoid engine speed frequency range, the problem easily causing resonance, risk is higher, therefore in safety
Reliability aspect, this utility model is safer reliably, verifies that examination is passed through on ground and altitude test.
(2) dynamically measure-point amount is the most, more can reflect the turbulence level situation in flow field, traditional probe due to space structure without
Method installs more dynamic pickup on probe, and this utility model structurally increases the space between support plate and former support plate newly
Relatively big, the dynamic measuring point of multiple spot can be laid according to actual needs, there is not wire and pressure-measuring pipe etc. and lay the problem that time space is not enough.
(3) measurement apparatus described in the utility model has carried out flow field survey on part aircraft, successfully measures multi rack
The flight parameter of secondary aircraft different conditions.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model；
Fig. 2 is close-up schematic view at the A of Fig. 1.
In figure: 1-inlet casing support plate, 2-tests support plate, and 3-measures mouth, 4-packing ring, 5-dynamic pressure transducer, and 6-is fixed
Position block, 7-pressure-measuring pipe, 8-silica gel.
Detailed description of the invention
The technical solution of the utility model is described further below, but claimed scope is not limited to described.
As shown in Figure 1 and Figure 2, a kind of airplane intake exit flow field measuring mechanism described in the utility model, including arranging
Test support plate 2 on inlet casing support plate 1, described test support plate 2 is provided with measuring point, offers measured hole at measuring point,
It is provided with locating piece 6 in described measured hole, locating piece 6 is provided with measurement mouth 3, described measurement mouth 3 is provided with dynamically pressure
Force transducer 5, described locating piece 6 is additionally provided with stable state pressure measurement mouth (not shown) and pressure-measuring pipe 7.Use this technical side
Case, decreases the impact of conventional probe self-convection field, it is possible to true and accurate reflection flow field actual state；And solve general spy
The drawback that pin cannot be installed because of external engine insufficient space；Enough spaces are had so that it is energy by installing modified test support plate 2 additional
Enough fill more dynamic pressure transducer 5, and then the turbulence level in flow field can be measured more accurately.Used on test support plate 2
Measurement mouth 2 ensure that measurement error is little, and locating piece 6 can be accurately positioned measurement position, and use silica gel can expire
The requirement of foot sealing reliability.
Described pressure-measuring pipe 7 uses argon arc welding to be welded on measurement mouth 3.In actual fabrication, measure mouth 3 and test support plate 2
Material all identical with the support plate on engine charge casing, the material i.e. measuring mouth 3 and test support plate 2 all props up with inlet casing
Plate 1 is identical, and is titanium alloy material, it is easy to welding.In actual production, owing to pressure-measuring pipe 7 is to use 1Cr8Ni9Ti stainless
Steel material, be difficult to use soldering or, use argon arc welding sealing effectiveness the most bad.
It is internal that described dynamic pressure transducer 5 is arranged on measurement mouth 3 by packing ring 4, and with silica gel 8 by dynamic pressure sensing
Device 5 is fixed on packing ring 4.When being so possible to prevent below dynamic pressure transducer 5 to be installed, bear the aperture of pressure by silica gel 8
Block and lose pressure measurement effect.
Such as Fig. 1, shown in Fig. 2, measurement apparatus installation procedure described in the utility model is: first by pressure-measuring pipe 7 and dynamic pressure
The wire of sensor 5 is fixed along test support plate 2 through the installing hole on inlet casing, after then splitting inside test support plate 2
Perfusion silica gel 8, seals to test support plate 2 is internal, after silica gel 8 solidifies, test support plate 2 is arranged on inlet casing and props up
On plate 1, after drawing the wire of pressure-measuring pipe 7 and dynamic pressure transducer 5, test support plate 2 and inlet casing support plate 1 are welded, weldering
Allowing to carry out test support plate 2 local reconditioning when connecing, two plate welding seams initiate with inside and outside casing connecting portion from test support plate 2,
Every section of a length of 20-25mm of weld seam, spacing is 8-10mm.Weld 2 points after having welded in spacer portion site, solder joint is uniformly distributed, weldering
Seam does not allow the surface of prominent test support plate 2, if prominent need to polishing flushes, and the continuous position of weld seam is all with X-ray examination, to survey
Fixing being attached numbered on the engine by the wire of pressure pipe 7 and dynamic pressure transducer 5.I.e. complete the group of this measurement apparatus
Dress operation.The solder technology used can not be tempered, after solving welding, the problem bringing stress to concentrate.
Detailed description of the invention of the present utility model is: wait anchor ring distribution stagnation pressure measuring point according to 6, electromotor AIP cross section, i.e.
5 pressure measurement mouths are installed on each inlet casing support plate 1；On electromotor wall, the side of each inlet casing support plate 1 is respectively distributed two
Individual static pressure mouth measures static pressure；Move as in figure 2 it is shown, the point position of each total pressure measurement mouth 3 divides equally a stable state measuring point and one
State measuring point, air-flow is caused (not shown) at the steady state sensor being arranged on outside electromotor by pressure-measuring pipe 7 by stable state measuring point；
Dynamically measuring point is that dynamic pressure transducer 5 is arranged on measurement mouth 3 inside；Measure mouth 3 by locating piece 6 erecting and welding in test
On plate 2；Test support plate 2 designs according to the structure of engine intake inlet casing support plate, and by argon arc welding, spot welding balanced welding welds
Connect.I.e. redesign test support plate 2 by electromotor original inlet casing support plate along profile normal direction, then re-working
On test support plate 2, mouth 3 measured by dress, and lays dynamic pressure between fresh processed test support plate 2 and original inlet casing support plate
The wire of sensor 5 and the pressure-measuring pipe 7 of stable state measuring point, then by silica gel sealing, the test support plate 2 of redesign, such as Fig. 1 institute
Show, be finally weldingly fixed on former inlet casing support plate.
When making above-mentioned test support plate 2, test support plate 2 is along the thickening of profile relative theory profile of profile normal direction
Or thinning be not more than 0.2mm, should seamlessly transit between profile point, and carry out dye penetration inspection.
The chamber of pressure-measuring pipe 7 tube chamber of the stable state measuring point of pressure measurement mouth and installation dynamic pressure transducer 5 is passed through the pressure of 0.5MPa
Power, time 3min, product No leakage and deformation, and pressure measurement mouth air inlet face are from the width of the minimum range with pressure measurement mouth testing support plate 2
The ratio of degree is more than 3, and when mounted, the measuring point of each pressure measurement mouth ensures on the same plane of vertical engine import.
The titanium alloy material (TA7) identical with rectification test support plate 2 is used when the pressure gauge of assembled formation,
Upper lower edge welds along Zhou Caiyong argon arc welding；Along test support plate 2 whole section of welding of radially adjacent outer casing position argon arc welding, lean on
In near, casing position and test support plate 2 radially use argon arc welding spot welding, it is possible to safety is firm, stablize work effectively to ensure it
Make；Owing to entirety weldering can cause stress to concentrate needs tempering to eliminate, tempering causes dynamic pressure transducer 5 to damage, spot welding
It is avoided that the problem that stress is concentrated.
Described test support plate 2 is provided with perforate with outer casing contact position, is used for wearing pressure-measuring pipe 7 and dynamic pressure transducer 5
Wire, the size in hole is difficult to excessive, has air-flow to have an impact jet flow field diametrically too greatly, the area in hole and can not surpassing
Cross engine charge face area one thousandth.
This utility model is provided with a stable state measuring point and a dynamic measuring point rather than at flow field 0.9R at each point position
Distribution dynamic measuring point at radius.Such it is advantageous in that the turbulence level that can not only more measure whole flow field, and is used for
Can substitute with dynamic measuring point data during stable state measuring point cisco unity malfunction during computational flow circumferential asymmetry evenness, and same position
Put and can be compared.
Claims (6)
1. an airplane intake exit flow field measuring mechanism, it is characterised in that: include being arranged on inlet casing support plate (1)
Test support plate (2), described test support plate (2) is provided with measuring point, offers measured hole at measuring point, arranges in described measured hole
There is locating piece (6), locating piece (6) is provided with measurement mouth (3), described measurement mouth (3) is provided with dynamic pressure transducer
(5), described locating piece (6) is additionally provided with stable state pressure measurement mouth and pressure-measuring pipe (7).
A kind of airplane intake exit flow field measuring mechanism the most according to claim 1, it is characterised in that: described pressure-measuring pipe
(7) argon arc welding is used to be welded in measurement mouth (3).
A kind of airplane intake exit flow field measuring mechanism the most according to claim 1, it is characterised in that: described dynamic pressure
It is internal that force transducer (5) is arranged on measurement mouth (3) by packing ring (4), and is fixed by dynamic pressure transducer (5) with silica gel (8)
On packing ring (4).
A kind of airplane intake exit flow field measuring mechanism the most according to claim 1, it is characterised in that: described pressure-measuring pipe
(7) fix through the installing hole on inlet casing along test support plate (2) with the wire of dynamic pressure transducer (5), and in welding
Front in test support plate (2) internal perfusion silica gel (8) sealing.
A kind of airplane intake exit flow field measuring mechanism the most according to claim 1, it is characterised in that: described test is propped up
Plate (2) and inlet casing support plate (1) use welding manner to fix, and wherein test support plate (2) and the weld seam of inlet casing support plate (1)
Initiateing with inside and outside casing connecting portion from test support plate (2), every section of a length of 20-25mm of weld seam, spacing is 8-10mm.
A kind of airplane intake exit flow field measuring mechanism the most according to claim 5, it is characterised in that: described weld seam is not
Highlight the surface of test support plate (2), and X-ray examination is all used at the continuous position of weld seam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620379695.3U CN205670075U (en) | 2016-04-28 | 2016-04-28 | A kind of airplane intake exit flow field measuring mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620379695.3U CN205670075U (en) | 2016-04-28 | 2016-04-28 | A kind of airplane intake exit flow field measuring mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN205670075U true CN205670075U (en) | 2016-11-02 |
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ID=57193869
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620379695.3U Active CN205670075U (en) | 2016-04-28 | 2016-04-28 | A kind of airplane intake exit flow field measuring mechanism |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105738070A (en) * | 2016-04-28 | 2016-07-06 | 贵州航空发动机研究所 | Airplane admission passage outlet flow field measuring device |
| CN106768818A (en) * | 2016-12-29 | 2017-05-31 | 中国航天空气动力技术研究院 | Mixed gas flow operational factor preparation method in a kind of shock tunnel |
| CN110411706A (en) * | 2019-07-01 | 2019-11-05 | 天津大学 | Device for optical measurement calibration in wall flow field close at the top of combustion chambers of internal combustion engines |
-
2016
- 2016-04-28 CN CN201620379695.3U patent/CN205670075U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105738070A (en) * | 2016-04-28 | 2016-07-06 | 贵州航空发动机研究所 | Airplane admission passage outlet flow field measuring device |
| CN105738070B (en) * | 2016-04-28 | 2018-02-16 | 贵州航空发动机研究所 | A kind of airplane intake exit flow field measurement apparatus |
| CN106768818A (en) * | 2016-12-29 | 2017-05-31 | 中国航天空气动力技术研究院 | Mixed gas flow operational factor preparation method in a kind of shock tunnel |
| CN106768818B (en) * | 2016-12-29 | 2019-04-30 | 中国航天空气动力技术研究院 | Mixed gas incoming flow operating parameter preparation method in a kind of shock tunnel |
| CN110411706A (en) * | 2019-07-01 | 2019-11-05 | 天津大学 | Device for optical measurement calibration in wall flow field close at the top of combustion chambers of internal combustion engines |
| CN110411706B (en) * | 2019-07-01 | 2020-09-01 | 天津大学 | Device for optical measurement and calibration of near-wall flow field at top of combustion chamber of internal combustion engine |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 550000 No. 602, Yuntan North Road, guanshanhu District, Guiyang City, Guizhou Province Patentee after: AVIC GUIZHOU ENGINE DESIGN INSTITUTE Address before: 550000 No. 602, Yuntan North Road, Jinyang New District, Guiyang City, Guizhou Province Patentee before: GUIZHOU AERONAUTICAL ENGINE INSTITUTE |