CN105738070A - Airplane admission passage outlet flow field measuring device - Google Patents
Airplane admission passage outlet flow field measuring device Download PDFInfo
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- CN105738070A CN105738070A CN201610277793.0A CN201610277793A CN105738070A CN 105738070 A CN105738070 A CN 105738070A CN 201610277793 A CN201610277793 A CN 201610277793A CN 105738070 A CN105738070 A CN 105738070A
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- support plate
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- flow field
- dynamic 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 an airplane admission passage outlet flow field measuring device which comprises a testing supporting plate that is arranged on an air inlet casing supporting plate. The testing supporting plate is provided with a measuring point. The measuring point is provided with a measuring hole which is internally provided with a positioning block. The positioning block is provided with a measuring nozzle on which a dynamic pressure sensor is mounted. The positioning block is also provided with a stable-state pressure measuring nozzle and a pressure measuring pipe. The pressure measuring pipe is welded on the measuring nozzle through argon arc welding. The dynamic pressure sensor is mounted in the measuring nozzle through a gasket. Furthermore the dynamic pressure sensor is fixed on the gasket through silica gel. According to the measuring device, small outer occupation space of an engine is realized, and a specialized measuring technological admission passage is not required, and easy realization is obtained. A relatively large space exists between the testing supporting plate and the air inlet casing supporting plate. A plurality of dynamic measuring points can be configured according to an actual requirement. A problem of insufficient space in configuring leads and pressure measuring pipes is settled.
Description
Technical field
The invention belongs to field of measuring technique, be specifically related to a kind of airplane intake exit flow field measurement apparatus.
Background technology
In technical field of aerospace; part aircraft is when carrying out high-speed agility flight; aeroplane nose often can produce strong sonic boom; send inside air intake duct " too " sound; make engine speed extremely unstable; during thrust big time little, the result through ground check shows that the main cause producing above-mentioned strong sonic boom is the matching problem between airplane intake and electromotor.Therefore, airplane intake and engine compatibility design, checking are brought in the R&D mode of aircraft and electromotor initially as key link, domestic and international aero-engine expert is it is well recognized that the importance of air inlet/engine Compatibility Evaluation, and one of important indicator examining matching is exactly the synthetic distortion index in air intake port flow field.
Raising day by day along with the complexity of aircraft aerodynamic configuration, mobility, the effect of electromotor work influence is manifested by air intake port flow field quality gradually, and become one of principal element of affecting electromotor job stability, due to Emulation Technology in Modern Computer application in flow field simulation, can there be some reference values, actual consider that fluid boundary-layer and turbulent flow cannot simulate (i.e. the turbulence level in flow field), so requiring over test could measure the real flow field condition of air intake duct.
At present, the means measuring flow field aboard are generally adopted insertion probe, it is contemplated that the impact of probe blockage ratio stream 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 at the internally installed more dynamic pickup of insertion probe so that dynamically measure-point amount is less, it is impossible to better reflect the turbulence level situation in flow field.
Summary of the invention
For solving above-mentioned technical problem, the invention provides a kind of airplane intake exit flow field measurement apparatus, thus reducing the impact of probe self-convection field, it is possible to true and accurate reflection flow field actual state, overcome the deficiency that conventional probe measuring method cannot be installed because of external engine insufficient space.
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, described test support plate is provided with measuring point, measured hole is offered at measuring point place, it is provided with locating piece in described measured hole, locating piece is 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 dynamic pressure transducer is arranged on inside measurement mouth by packing ring, and is fixed on packing ring by dynamic pressure transducer with silica gel.
Described pressure-measuring pipe adopts argon arc welding to be welded on measurement mouth.
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 adopting welding manner to fix test support plate and inlet casing support plate, wherein the weld seam of test support plate and inlet casing support plate initiates from test support plate with inside and outside casing connecting portion, and every section of weld seam length is 20-25mm, and spacing is 8-10mm.
Described weld seam does not highlight the surface of test support plate, and the continuous position of weld seam is used that X-ray examination.
The beneficial effects of the present invention is:
Compared with prior art, adopt measurement apparatus of the present invention that airplane intake exit flow field is contrasted, there is following remarkable advantage:
(1) present invention compares with employing probe measurement flow field mode, takes up room at external engine little, is increased without the technique air intake duct of special measurement, it is easy to accomplish；At engine interior, simply engine charge casing support plate is lengthened in the axial direction, the blockage ratio of stream field can be ignored substantially, traditional socle beam probe and double; two fixed pivot probe, be all difficult to eliminate probe fundamental frequency and can not avoid engine speed frequency range, the problem easily causing resonance, risk is higher, therefore in security reliability, the present invention is safer reliably, verifies that examination is passed through on ground and altitude test.
(2) dynamically measure-point amount is more many, more can reflect the turbulence level situation in flow field, traditional probe cannot install more dynamic pickup due to space structure on probe, and the present invention structurally newly-increased space between support plate and former support plate is bigger, the dynamic measuring point of multiple spot can be laid according to actual needs, be absent from wire and pressure-measuring pipe etc. and lay the problem that time space is not enough.
(3) measurement apparatus of the present invention has carried out flow field survey on part aircraft, successfully measures the flight parameter of many sorties aircraft different conditions.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the A place close-up schematic view 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, 6-locating piece, 7-pressure-measuring pipe, 8-silica gel.
Detailed description of the invention
Technical scheme be described further below, but described in the scope claimed is not limited to.
As shown in Figure 1 and Figure 2, a kind of airplane intake exit flow field measurement apparatus of the present invention, including the test support plate 2 being arranged on inlet casing support plate 1, described test support plate 2 is provided with measuring point, offer measured hole at measuring point place, in described measured hole, be provided with 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 (not shown) and pressure-measuring pipe 7；It is internal that described dynamic pressure transducer 5 is arranged on measurement mouth 3 by packing ring 4, and is fixed on packing ring 4 by dynamic pressure transducer 5 with silica gel 8.When being so possible to prevent to install dynamic pressure transducer 5 below, the aperture bearing pressure is blocked by silica gel 8 and is lost pressure measurement effect.Adopt the technical program, decrease the impact of conventional probe self-convection field, it is possible to true and accurate reflection flow field actual state；And solve the drawback that general probe cannot be installed because of external engine insufficient space；Enough spaces are had so that it is more dynamic pressure transducer 5 can be filled, and then the turbulence level in flow field can be measured more accurately by installing modified test support plate 2 additional.The measurement mouth 2 used on test support plate 2 ensure that measurement error is little, and locating piece 6 can be accurately positioned measurement position, and uses silica gel to disclosure satisfy that the requirement of sealing reliability.
Described pressure-measuring pipe 7 adopts argon arc welding to be welded on measurement mouth 3.In actual fabrication, measure mouth 3 all identical with the support plate on engine charge casing with the material of test support plate 2, namely measure mouth 3 all identical with inlet casing support plate 1 with the material of test support plate 2, and be titanium alloy material, it is easy to welding.In actual production, due to pressure-measuring pipe 7 be adopt 1Cr8Ni9Ti stainless steel material, not easily adopt soldering or, use argon arc welding sealing effectiveness also bad.
Such as Fig. 1, shown in Fig. 2, measurement apparatus installation procedure of the present invention is: first fixed along test support plate 2 through the installing hole on inlet casing by the wire of pressure-measuring pipe 7 and dynamic pressure transducer 5, then inside test support plate 2, silica gel 8 is irrigated after splitting, seal to test support plate 2 is internal, after silica gel 8 solidifies, test support plate 2 is arranged on inlet casing support 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, allow during welding test support plate 2 is carried out local reconditioning, two plate welding seams are from testing support plate 2 with interior, outer casing connecting portion initiates, every section of weld seam length is 20-25mm, spacing is 8-10mm.Weld 2 points in spacer portion site after having welded, solder joint is uniformly distributed, and weld 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 used that X-ray examination, the wire of pressure-measuring pipe 7 and dynamic pressure transducer 5 is numbered fixing being attached on the engine.Namely the assembling procedure of this measurement apparatus is completed.The solder technology used can not the tempering problem of bringing stress to concentrate after solving welding.
The specific embodiment of the present invention is: wait anchor ring distribution stagnation pressure measuring point according to 6, electromotor AIP cross section, namely installs 5 pressure measurement mouths on each inlet casing support plate 1；On electromotor wall, the side of each inlet casing support plate 1 is respectively distributed two static pressure mouths measurement static pressure；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 a dynamic measuring point, air-flow is caused the steady state sensor place (not shown) being arranged on outside electromotor by stable state measuring point by pressure-measuring pipe 7；Dynamic measuring point is that dynamic pressure transducer 5 is arranged on measurement mouth 3 inside；Measure mouth 3 tested on support plate 2 by locating piece 6 erecting and welding；The test support plate 2 structural design according to engine intake inlet casing support plate, by argon arc welding, spot welding balanced welding welds.Namely test support plate 2 is redesigned by the original inlet casing support plate of electromotor along profile normal direction, then dress measurement mouth 3 on test support plate 2 is again being processed, and between fresh processed test support plate 2 and original inlet casing support plate, lay the wire of dynamic pressure transducer 5 and the pressure-measuring pipe 7 of stable state measuring point, then pass through silica gel sealing, the test support plate 2 redesigned, as it is shown in figure 1, be finally weldingly fixed on former inlet casing support plate.
When making above-mentioned test support plate 2, test support plate 2, along the thickening or the thinning 0.2mm that is not more than of profile relative theory profile of profile normal direction, 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 passes into the pressure of 0.5MPa, time 3min, product No leakage and deformation, and pressure measurement mouth air inlet face from the ratio of the test minimum range of support plate 2 and the width of pressure measurement mouth more than 3, when mounted, the measuring point of each pressure measurement mouth ensures on the same plane of vertical engine import.
Adopt the titanium alloy material (TA7) identical with rectification test support plate 2 when the pressure gauge of assembled formation, weld along Zhou Caiyong argon arc welding at upper lower edge；Along test support plate 2 whole section of welding of radially adjacent outer casing position argon arc welding, radially using argon arc welding spot welding near interior casing position and test support plate 2, it is possible to effectively ensure its firm, steady operation of safety；Needing tempering to eliminate owing to entirety weldering can cause that stress is concentrated, tempering causes that dynamic pressure transducer 5 damages, and spot welding is avoided that the problem that stress is concentrated.
Described test support plate 2 is provided with perforate with outer casing contact position, for wearing pressure-measuring pipe 7 and the wire of dynamic pressure transducer 5, the size in hole is not easily excessive, has air-flow that jet flow field has impact diametrically too greatly, the area in hole and not can exceed that engine charge face area one thousandth.
The present invention is provided with a stable state measuring point and a dynamic measuring point at each point position, rather than at 0.9R radius place, flow field distribution dynamic measuring point.Such turbulence level that can not only more measure whole flow field that is advantageous in that, and can substitute with dynamic measuring point data during stable state measuring point cisco unity malfunction when being used for computational flow circumferential asymmetry evenness, and same position can be compared.
Claims (5)
1. an airplane intake exit flow field measurement apparatus, it is characterized in that: include the test support plate (2) being arranged on inlet casing support plate (1), described test support plate (2) is provided with measuring point, measured hole is offered at measuring point place, locating piece (6) it is provided with in described measured hole, 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)；It is internal that described dynamic pressure transducer (5) is arranged on measurement mouth (3) by packing ring (4), and is fixed on packing ring (4) by dynamic pressure transducer (5) with silica gel (8).
2. a kind of airplane intake exit flow field measurement apparatus according to claim 1, it is characterised in that: described pressure-measuring pipe (7) adopts argon arc welding to be welded in measurement mouth (3).
3. a kind of airplane intake exit flow field measurement apparatus according to claim 1, it is characterized in that: the wire of described pressure-measuring pipe (7) and dynamic pressure transducer (5) installing hole along test support plate (2) through inlet casing is fixed, and seals in test support plate (2) internal perfusion silica gel (8) before welding.
4. a kind of airplane intake exit flow field measurement apparatus according to claim 1, it is characterized in that: described support plate (2) of testing adopts welding manner to fix with inlet casing support plate (1), the weld seam wherein testing support plate (2) and inlet casing support plate (1) initiates from test support plate (2) with inside and outside casing connecting portion, every section of weld seam length is 20-25mm, and spacing is 8-10mm.
5. a kind of airplane intake exit flow field measurement apparatus according to claim 4, it is characterised in that: described weld seam does not highlight the surface of test support plate (2), and the continuous position of weld seam is used that X-ray examination.
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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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| 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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| CN105738070A true CN105738070A (en) | 2016-07-06 |
| CN105738070B 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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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111323161A (en) * | 2018-12-14 | 2020-06-23 | 罗斯蒙特航天公司 | Optical pressure integrated atmospheric data probe |
| CN111537183A (en) * | 2020-05-19 | 2020-08-14 | 刘祥 | Ventilation model internal resistance supporting and measuring system |
| CN113138061A (en) * | 2021-06-21 | 2021-07-20 | 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 |
| CN113720911A (en) * | 2021-09-01 | 2021-11-30 | 中国航发沈阳黎明航空发动机有限责任公司 | Positioning tool for detecting weld defects of air inlet casing and judging method |
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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 |
| JP2001174363A (en) * | 1999-12-20 | 2001-06-29 | Kawada Kogyo Kk | Measuring probe orientating device |
| 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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2016
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
| JP2001174363A (en) * | 1999-12-20 | 2001-06-29 | Kawada Kogyo Kk | Measuring probe orientating device |
| 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 |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111323161A (en) * | 2018-12-14 | 2020-06-23 | 罗斯蒙特航天公司 | Optical pressure integrated atmospheric data probe |
| CN111537183A (en) * | 2020-05-19 | 2020-08-14 | 刘祥 | Ventilation model internal resistance supporting and measuring system |
| CN113138061A (en) * | 2021-06-21 | 2021-07-20 | 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 |
| 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 |
| CN113720911A (en) * | 2021-09-01 | 2021-11-30 | 中国航发沈阳黎明航空发动机有限责任公司 | Positioning tool for detecting weld defects of air inlet casing and judging method |
| 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 |
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| CN105738070B (en) | 2018-02-16 |
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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 |
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