CN105738070B - A kind of airplane intake exit flow field measurement apparatus - Google Patents
A kind of airplane intake exit flow field measurement apparatus Download PDFInfo
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- CN105738070B CN105738070B CN201610277793.0A CN201610277793A CN105738070B CN 105738070 B CN105738070 B CN 105738070B CN 201610277793 A CN201610277793 A CN 201610277793A CN 105738070 B CN105738070 B CN 105738070B
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- support plate
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- pressure
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention discloses a kind of airplane intake exit flow field measurement apparatus, including the test support plate being arranged on inlet casing support plate, measuring point is provided with the test support plate, measured hole is offered at measuring point, locating piece is provided with the measured hole, measurement mouth is provided with locating piece, dynamic pressure transducer is installed on the measurement mouth, stable state pressure measurement mouth and pressure-measuring pipe are additionally provided with the locating piece, the pressure-measuring pipe is welded on measurement mouth using argon arc welding, the dynamic pressure transducer is arranged on inside measurement mouth by packing ring, and dynamic pressure transducer is fixed on packing ring with silica gel.Using measurement apparatus of the present invention, occupied little space in external engine, be increased without the technique air intake duct of special measurement, it is easy to accomplish；The space tested in structure between support plate and inlet casing support plate is larger, can lay multiple spot dynamic measuring point according to being actually needed, the problem of laying time space deficiency in the absence of wire and pressure-measuring pipe etc..
Description
Technical field
The invention belongs to field of measuring technique, is specifically related to a kind of airplane intake exit flow field measurement apparatus.
Background technology
In technical field of aerospace, when carrying out high-speed agility flight, aeroplane nose can often produce strong quick-fried part aircraft
Sound, sent inside air intake duct " too " sound so that engine speed is extremely unstable, small when big during thrust, by ground
The main reason for result of inspection shows to produce above-mentioned strong sonic boom is the matching problem between airplane intake and engine.Cause
This, airplane intake brings the research and development of aircraft and engine into engine compatibility design, checking initially as key link
In system, domestic and international aero-engine expert examines it is well recognized that the importance of air inlet/engine Compatibility Evaluation
One of important indicator of matching is exactly the synthetic distortion index in air intake port flow field.
With the increasingly raising of the complexity of aircraft aerodynamic configuration, mobility, air intake port flow field quality is to engine
The effect of work influence gradually shows, and as one of principal element for influenceing engine job stability, due to modern computing
Application of the machine emulation technology in terms of flow field simulation, there can be some reference values, it is actual to consider fluid boundary-layer and rapids
Stream can not simulate (i.e. the turbulence level in flow field), so needing that by experiment the real flow field condition of air intake duct could be measured.
At present, the means for measuring flow field aboard typically use insertion probe, due to consideration that probe blockage ratio pair
The influence in flow field, and probe itself fundamental frequency and the close safety effects to engine of engine speed working frequency；
The space that formula probe exterior part accounts for engine profile is additionally inserted into, and can not be installed inside insertion probe more dynamic
State sensor so that dynamic measure-point amount is less, it is impossible to the preferably turbulence level situation in reflection flow field.
The content of the invention
In order to solve the above technical problems, the invention provides a kind of airplane intake exit flow field measurement apparatus, so as to subtract
The influence of few probe self-convection field, can true and accurate reflection flow field actual state, overcome conventional probe measuring method because
The deficiency that external engine insufficient space can not be installed.
The present invention is achieved by the following technical programs.
A kind of airplane intake exit flow field measurement apparatus, 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, measured hole is offered at measuring point, locating piece is provided with the measured hole, in locating piece
On be provided with measurement mouth, dynamic pressure transducer is installed on the measurement mouth, stable state pressure measurement is additionally provided with the locating piece
Mouth and pressure-measuring pipe；The dynamic pressure transducer is arranged on inside measurement mouth by packing ring, and with silica gel by dynamic pressure sensing
Device is fixed on packing ring.
The pressure-measuring pipe is welded on measurement mouth using argon arc welding.
The wire of the pressure-measuring pipe and dynamic pressure transducer passes through the mounting hole on inlet casing to fix along test support plate,
And before welding in test branch intralamellar part perfusion silica gel sealing.
It is described to fix test support plate using welding manner with inlet casing support plate, wherein test support plate and inlet casing branch
The weld seam of plate originates from test support plate and inside and outside casing connecting portion, every section of weld seam a length of 20-25mm, spacing 8-10mm.
The surface of the not prominent test support plate of the weld seam, and X-ray examination is used at the continuous position of weld seam.
The beneficial effects of the present invention are：
Compared with prior art, airplane intake exit flow field is contrasted using measurement apparatus of the present invention,
With following remarkable advantage：
(1) present invention is compared with using probe measurement flow field mode, is occupied little space in external engine, is increased without specially
With the technique air intake duct of measurement, it is easy to accomplish；In engine interior, simply engine charge casing support plate is carried out in the axial direction
Lengthen, the blockage ratio of stream field can be ignored substantially, traditional socle beam probe and double fixed pivot probes, be difficult to eliminate and visit
Pin fundamental frequency can not avoid engine speed frequency range, easily cause the problem of resonance, and risk is higher, therefore safe and reliable
Property aspect, the present invention is safer reliable, passes through on ground and altitude test checking examination.
(2) dynamic measure-point amount is more, can more reflect the turbulence level situation in flow field, traditional probe due to space structure without
Method installs more dynamic pickups on probe, and the present invention increased newly in structure space between support plate and former support plate compared with
Greatly, can according to be actually needed lay multiple spot dynamic measuring point, in the absence of wire and pressure-measuring pipe etc. lay time space deficiency the problem of.
(3) measurement apparatus of the present invention carries out flow field survey on the aircraft of part, successfully measures more sorties and flies
The flight parameter of machine different conditions.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention；
Fig. 2 is close-up schematic view at Fig. 1 A.
In figure：1- inlet casing support plates, 2- test support plates, 3- measurement mouths, 4- packing rings, 5- dynamic pressure transducers, 6- are fixed
Position block, 7- pressure-measuring pipes, 8- silica gel.
Embodiment
Be described further below technical scheme, but claimed scope be not limited to it is described.
As shown in Figure 1 and Figure 2, a kind of airplane intake exit flow field measurement apparatus of the present invention, including be arranged on into
Test support plate 2 on mechanism of qi casket support plate 1, described test on support plate 2 is provided with measuring point, measured hole is offered at measuring point, described
Locating piece 6 is provided with measured hole, measurement mouth 3 is provided with locating piece 6, dynamic pressure biography is installed on the measurement mouth 3
Sensor 5, stable state pressure measurement mouth (not shown) and pressure-measuring pipe 7 are additionally provided with the locating piece 6；The dynamic pressure transducer
5 are arranged on inside measurement mouth 3 by packing ring 4, and dynamic pressure transducer 5 is fixed on packing ring 4 with silica gel 8.So can be with
When preventing installation dynamic pressure transducer 5 below, the aperture for bearing pressure is blocked by silica gel 8 and loses pressure measurement effect.Using this
Technical scheme, reduce the influence of conventional probe self-convection field, being capable of true and accurate reflection flow field actual state；And solve
General probe because external engine insufficient space can not install the drawbacks of；There are enough spaces by installing modified test support plate 2 additional,
More dynamic pressure transducers 5 can be filled, and then can more accurately measure the turbulence level in flow field.Test on support plate 2
Used measurement mouth 2 can ensure that measurement error is small, and locating piece 6 can be accurately positioned measurement position, and use silica gel
It disclosure satisfy that the requirement of sealing reliability.
The pressure-measuring pipe 7 is welded on measurement mouth 3 using argon arc welding.In actual fabrication, measurement mouth 3 and test support plate 2
Material it is identical with the support plate on engine charge casing, that is, measure mouth 3 and test support plate 2 material with inlet casing branch
Plate 1 is identical, and is titanium alloy material, is easy to weld.In actual production, because pressure-measuring pipe 7 is stainless using 1Cr8Ni9Ti
Steel material, it is not easy using soldering or, also bad using argon arc welding sealing effectiveness.
Such as Fig. 1, shown in Fig. 2, measurement apparatus installation procedure of the present invention is：First by pressure-measuring pipe 7 and dynamic pressure sensing
The wire of device 5 passes through the mounting hole on inlet casing to fix along test support plate 2, is irrigated after then splitting inside test support plate 2
Silica gel 8, to being sealed inside test support plate 2, after the solidification of silica gel 8, test support plate 2 is arranged on inlet casing support plate 1
On, after the wire for drawing pressure-measuring pipe 7 and dynamic pressure transducer 5, test support plate 2 and inlet casing support plate 1 are welded, during welding
Allow to carry out local reconditioning to test support plate 2, two plate welding seams originate from test support plate 2 and inside and outside casing connecting portion, every section
Weld seam a length of 20-25mm, spacing 8-10mm.Weld at 2 points in spacer portion site after the completion of welding, solder joint is uniformly distributed, and weld seam is not
Allow the surface of prominent test support plate 2, flushed if protrusion need to polish, and X-ray examination is used at the continuous position of weld seam, to pressure-measuring pipe
7 and dynamic pressure transducer 5 wire number on the engine fixation be attached.Complete the assembling work of the measurement apparatus
Sequence.Used welding technique, which solves the problems, such as to be tempered after welding, brings stress concentration.
The present invention embodiment be：According to engine AIP sections, 6 are waited anchor ring distribution stagnation pressure measuring point, i.e., each
5 pressure measurement mouths are installed on inlet casing support plate 1；Respectively distribution two is quiet on the side of each inlet casing support plate 1 on engine wall
Pressure mouth measures static pressure；As shown in Fig. 2 the point position of each total pressure measurement mouth 3 divides equally a stable state measuring point and a dynamic is surveyed
Air-flow is led to (not shown) at the steady state sensor outside engine by point, stable state measuring point by pressure-measuring pipe 7；Dynamically
Measuring point is that dynamic pressure transducer 5 is arranged on inside measurement mouth 3；Mouth 3 is measured by the erecting and welding of locating piece 6 in test support plate 2
On；Structure design of the support plate 2 according to engine intake inlet casing support plate is tested, passes through argon arc welding, the welding of spot welding balanced welding.I.e.
Test support plate 2 is redesigned along type face normal direction by the original inlet casing support plate of engine, is then re-working test
Dress measurement mouth 3 on support plate 2, and lay dynamic pressure sensing between fresh processed test support plate 2 and original inlet casing support plate
The wire of device 5 and the pressure-measuring pipe 7 of stable state measuring point, then by silica gel sealing, the test support plate 2 of redesign, as shown in figure 1,
Finally it is weldingly fixed on former inlet casing support plate.
When making above-mentioned test support plate 2, type face relative theory type face of the test support plate 2 along type face normal direction thickens
Or be thinned and be not more than 0.2mm, it should be seamlessly transitted between type millet cake, and carry out dye penetration inspection.
The tube chamber of pressure-measuring pipe 7 of the stable state measuring point of pressure measurement mouth and the chamber of installation dynamic pressure transducer 5 are passed through 0.5MPa pressure
Power, time 3min, product No leakage and deformation, and pressure measurement mouth air inlet face is from the minimum range of test support plate 2 and the width of pressure measurement mouth
The ratio between 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.
Used in the device for pressure measurement of assembled formation and test the identical titanium alloy material (TA7) of support plate 2 with rectification,
Upper lower edge welds along Zhou Caiyong argon arc weldings；Along the whole section of welding of radially adjacent outer casing position argon arc welding of test support plate 2, lean on
Casing position and test support plate 2 radially use argon arc welding spot welding near, can effectively ensure that its safe firm, stable work
Make；Because overall weldering can cause the tempering of stress concentration needs to eliminate, tempering causes dynamic pressure transducer 5 to damage, spot welding
The problem of being avoided that stress concentration.
The test support plate 2 is provided with perforate with outer casing contact position, for wearing pressure-measuring pipe 7 and dynamic pressure transducer 5
Wire, the size in hole is not easy excessive, diametrically has air-flow to have an impact jet flow field greatly very much, the area in hole and can not surpass
Cross engine charge face area one thousandth.
The present invention is provided with a stable state measuring point and a dynamic measuring point in each point position, rather than in flow field 0.9R radiuses
Locate distribution dynamic measuring point.It is such to be advantageous in that the turbulence level that more measure whole flow field, and for calculating
Dynamic measuring point data can be used to substitute during stable state measuring point cisco unity malfunction during the circumferential asymmetry evenness of flow field, and same position can
To be compared.
Claims (3)
- A kind of 1. airplane intake exit flow field measurement apparatus, it is characterised in that：Including being arranged on inlet casing support plate (1) Support plate (2) is tested, measuring point is provided with the test support plate (2), measured hole is offered at measuring point, is set in the measured hole There is locating piece (6), measurement mouth (3) is provided with locating piece (6), dynamic pressure transducer is installed on the measurement mouth (3) (5) stable state pressure measurement mouth and pressure-measuring pipe (7), are additionally provided with the locating piece (6)；The dynamic pressure transducer (5) passes through pad Enclose (4) and be arranged on measurement mouth (3) inside, and dynamic pressure transducer (5) is fixed on packing ring (4) with silica gel (8)；The survey Pressure pipe (7) is welded on measurement mouth (3) using argon arc welding；The wire of the pressure-measuring pipe (7) and dynamic pressure transducer (5) edge is surveyed Examination support plate (2) is fixed through the mounting hole on inlet casing, and perfusion silica gel (8) is close inside test support plate (2) before welding Envelope.
- A kind of 2. airplane intake exit flow field measurement apparatus according to claim 1, it is characterised in that：The test branch Plate (2) is fixed with inlet casing support plate (1) using welding manner, wherein the weld seam of test support plate (2) and inlet casing support plate (1) Originated from test support plate (2) and inside and outside casing connecting portion, every section of weld seam a length of 20-25mm, spacing 8-10mm.
- A kind of 3. airplane intake exit flow field measurement apparatus according to claim 2, it is characterised in that：The weld seam is not The surface of prominent test support plate (2), and X-ray examination is used at the continuous position of weld seam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201610277793.0A CN105738070B (en) | 2016-04-28 | 2016-04-28 | A kind of airplane intake exit flow field measurement apparatus |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610277793.0A CN105738070B (en) | 2016-04-28 | 2016-04-28 | A kind of airplane intake exit flow field measurement apparatus |
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| Publication Number | Publication Date |
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| CN105738070A CN105738070A (en) | 2016-07-06 |
| CN105738070B true CN105738070B (en) | 2018-02-16 |
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| CN201610277793.0A Active CN105738070B (en) | 2016-04-28 | 2016-04-28 | A kind of airplane intake exit flow field measurement apparatus |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10823753B2 (en) * | 2018-12-14 | 2020-11-03 | Rosemount Aerospace Inc. | Air data probe with optical pressure integration |
| CN111537183B (en) * | 2020-05-19 | 2021-09-24 | 刘祥 | Ventilation model internal resistance supporting and measuring system |
| CN113138061B (en) * | 2021-06-21 | 2021-08-13 | 中国航空工业集团公司沈阳空气动力研究所 | Improved wind tunnel air inlet channel test model supporting system |
| CN113720911B (en) * | 2021-09-01 | 2024-02-06 | 中国航发沈阳黎明航空发动机有限责任公司 | Positioning tool and judging method for detecting weld defects of air inlet casing |
Citations (4)
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|---|---|---|---|---|
| US3699811A (en) * | 1971-07-27 | 1972-10-24 | Nasa | Flow velocity and direction instrument |
| US5756892A (en) * | 1997-02-27 | 1998-05-26 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Apparatus for measuring ambient pressure within a gaseous flow field |
| CN201688962U (en) * | 2010-03-29 | 2010-12-29 | 南京航空航天大学 | Air inlet duct testing device capable of measuring on same model |
| CN205670075U (en) * | 2016-04-28 | 2016-11-02 | 贵州航空发动机研究所 | A kind of airplane intake exit flow field measuring mechanism |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001174363A (en) * | 1999-12-20 | 2001-06-29 | Kawada Kogyo Kk | Measuring probe orientating device |
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2016
- 2016-04-28 CN CN201610277793.0A patent/CN105738070B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3699811A (en) * | 1971-07-27 | 1972-10-24 | Nasa | Flow velocity and direction instrument |
| US5756892A (en) * | 1997-02-27 | 1998-05-26 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Apparatus for measuring ambient pressure within a gaseous flow field |
| CN201688962U (en) * | 2010-03-29 | 2010-12-29 | 南京航空航天大学 | Air inlet duct testing device capable of measuring on same model |
| CN205670075U (en) * | 2016-04-28 | 2016-11-02 | 贵州航空发动机研究所 | A kind of airplane intake exit flow field measuring mechanism |
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| CN105738070A (en) | 2016-07-06 |
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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 |