CN204241219U - The wing detector probe of stagnation temperature stagnation pressure - Google Patents
The wing detector probe of stagnation temperature stagnation pressure Download PDFInfo
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- CN204241219U CN204241219U CN201420304506.7U CN201420304506U CN204241219U CN 204241219 U CN204241219 U CN 204241219U CN 201420304506 U CN201420304506 U CN 201420304506U CN 204241219 U CN204241219 U CN 204241219U
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- 239000000523 sample Substances 0.000 title claims abstract description 19
- 229910052751 metal Inorganic materials 0.000 claims abstract description 19
- 239000002184 metal Substances 0.000 claims abstract description 19
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 claims abstract description 12
- 229910052697 platinum Inorganic materials 0.000 claims abstract description 6
- 238000012360 testing method Methods 0.000 abstract description 15
- 238000000034 method Methods 0.000 abstract description 5
- 239000000284 extract Substances 0.000 abstract description 2
- 238000009434 installation Methods 0.000 abstract description 2
- 238000005259 measurement Methods 0.000 abstract description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 abstract 1
- 229910052802 copper Inorganic materials 0.000 abstract 1
- 239000010949 copper Substances 0.000 abstract 1
- 238000013016 damping Methods 0.000 abstract 1
- 238000012856 packing Methods 0.000 abstract 1
- 238000007906 compression Methods 0.000 description 12
- 230000006835 compression Effects 0.000 description 10
- 238000005219 brazing Methods 0.000 description 6
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 5
- 229910052709 silver Inorganic materials 0.000 description 5
- 239000004332 silver Substances 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000009530 blood pressure measurement Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000011076 safety test Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- Measuring Temperature Or Quantity Of Heat (AREA)
Abstract
The wing detector probe of a kind of stagnation temperature stagnation pressure, belongs to aeromotor aerodynamic parameter technical field of measurement and test, it is characterized in that, thermometric bar, wing housing, metal catheter and flange; Thermometric bar and wing housing fastening by flange, insert engine crankcase instrument connection, copper packing vibration damping seals.The accurate temperature sensing element of the built-in platinum resistance of thermometric rod member end, senses the gas flow temperature after wing housing air inlet and vent port stagnation, and housing bottom hemisphere socket bore extracts flow field stagnation pressure simultaneously.Compared with pneumatic gauging structural member in the past, the utility model advantage: flow resistance is little, intensity is high, avoids because test structure part causes disorder to uniform flow fields such as engine intakes; Stagnation temperature, stagnation pressure Parameters Integrated Survey Method are measured simultaneously, decrease the installation quantity of test structure part, alleviate weight, reduce the flow loss that the reasons such as runner blockage ratio and leakage cause.
Description
Technical field
The utility model belongs to aeromotor aerodynamic parameter technical field of measurement and test, especially for the aerodynamic parameter test in the uniform flow field such as engine or gas turbine inlet cross section devises the wing detector probe of a kind of stagnation temperature stagnation pressure.
Background technology
The research and development of aeromotor and gas turbine be unable to do without ground surface works checking repeatedly, need to measure a series of aerodynamic parameter in process of the test, as the key input parameters such as engine intake stagnation temperature, stagnation pressure for the experimental safe of engine and Performance Evaluation particularly important.The utility model of test structure part in the past if the patent No. is Zl201120299935.6 is not do not have the multiple test function of compound, though the utility model being Zl201110000317.1 as the patent No. exactly meets several functions demand, because cylinder pole tail brings new impact to flow field quality.Along with the continuous propelling of reseach of engine level, attitude for these influence factors also needs to face directly from ignoring to change into, while how integrated safe reliably records call parameter, reduce the interference because the intervention of plug-in type test structure part causes to the tested flow field of surrounding as far as possible, more and more become the new problem that current engineering technical personnel face.Both meeting Structural strength calls, under ensureing again the prerequisite of high-quality uniform flow field, accurately measure stagnation temperature, the stagnation pressure in the typical section flow fields such as engine intake, the development tool for new model engine is of great significance.
Utility model content
The purpose of this utility model is for above-mentioned Practical Project problem, is the wing detector probe of aerodynamic parameter test a kind of stagnation temperature stagnation pressure of design of the typical section such as aeromotor or gas turbine inlet uniform flow field.
The technical scheme that the utility model is dealt with problems is: so-called aerofoil profile, as the term suggests same or similar with aircraft wing shape, as everyone knows, the wing streamline profile of aircraft is through repetition test and checking, can reduce flow resistance to greatest extent, there is good aeroperformance, principle whereby, utility model designs the wing detector probe of a kind of stagnation temperature stagnation pressure, and it comprises: thermometric bar 1, wing housing 2, metal catheter 3 and flange.
There is flange on wing housing 2 top, and top to bottom has a main through hole 4, and through-bore axis is positioned at housing middle section and the aerofoil profile leading edge 2mm ~ 4mm of distance housing; Wing leading edge has air admission hole 5, and trailing edge has vent port 6, is communicated with respectively with main through hole, and leading edge air admission hole and the trailing edge vent port centre of form align, and leading edge air admission hole sectional area is greater than trailing edge vent port sectional area; Top to bottom also has a secondary through hole 7, and between main through hole and airfoil trailing edge, secondary through hole has one section to be communicated with at wing housing bottom and main through hole, is not communicated with other each holes; Metal catheter 3 is through secondary through hole and above-mentioned Connectivity Section 8; The wing leading edge locus of Connectivity Section corresponding housing has a bottom through-hole 9 be communicated with main through hole;
Bottom through-hole 9 leading edge opening is half ball-and-socket type, and the diameter of bottom through-hole is less than the diameter of half ball-and-socket type opening 10;
Metal catheter 3, through secondary through hole 7 and Connectivity Section 8, inserts in bottom through-hole 9, with half ball-and-socket type opening 10 bottom connection;
Thermometric bar 1 is flanged, has accurate temperature sensing element lead-in wire electrical connector above flange; The below of flange is hollow stepped cylindrical;
Thermometric bar 1 inserts main through hole 4, the built-in accurate temperature sensing element of its cylinder thin segment, corresponding with aerofoil profile housing air admission hole 5 and vent port 6 position, forms a ring cavity with main through-hole wall; The thick section of cylinder and the same diameter of main through hole, clearance fit;
Thermometric bar 1 and aerofoil profile housing 2 are fastenedly connected by flange.
The wing detector probe of stagnation temperature stagnation pressure, is characterized in that: described accurate temperature sensing element is the A grade platinum resistances such as Pt100 or Pt1000.
The wing detector probe of stagnation temperature stagnation pressure, is characterized in that: described electrical connector is four-core electric connector.
The wing detector probe of stagnation temperature stagnation pressure, is characterized in that: described aerofoil profile housing bottom welds airtight with closeouts.
Its main operational principle is: when air-flow is through test detector probe, tested air-flow is divided into three strands, and wherein most of air-flow passes through along the wing outer wall profile of housing, very little by disturbance; Fraction air-flow enters wing leading edge air admission hole, is discharged by wing trailing edge vent port, and because port is pre-large post-small, air-flow slows down stagnation in ring cavity, and senses incoming flow stagnation temperature by temperature sensing element accurate in thermometric bar; Small part enters the air-flow of bottom through-hole, causes to wing housing tip by metal catheter, extracts incoming flow stagnation pressure.
The beneficial effect of the utility model compared with prior art utility model is:
1. detector probe is combined with aerofoil profile aerodynamic configuration, both ensure that intensity, again reduces the interference to around flow field uniformity, especially greatly reduces inlet distortion when engine intake is measured, for the safety test of engine and steady running significant.
2. while detector probe aeroperformance improves, can to the aerodynamic parameter such as stagnation temperature, stagnation pressure integrated testing in engine runner, reduce the installation quantity of test structure part and the number of openings of casing instrument connection, alleviate impost, reduce the blockage ratio in cross section, prevent the flow leakage loss because test perforate too much causes, the Performance Evaluation for engine is significant simultaneously.
3. detector probe structure is simplified, and total pressure measurement passage designs completely in wing enclosure interior, achieves the integrated of stagnation temperature and total pressure measurement and is independent of each other.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model
Fig. 2 is the partial enlarged drawing of Fig. 1
Fig. 3 is the front view of assembly 2 in Fig. 2
Fig. 4 is the vertical view of Fig. 2
Fig. 5 is that the C of Fig. 2 is to partial view
Fig. 6 is the enlarged drawing of Fig. 2 local I
Fig. 7 is the enlarged drawing of Fig. 2 local I I
Wherein: 1-thermometric bar, 2-aerofoil profile housing, 3-metal catheter, the main through hole of 4-, 5-air admission hole, 6-vent port, the secondary through hole of 7-, 8-Connectivity Section, 9-bottom through-hole, 10-half ball-and-socket type opening, 11-compression fittings, the small linear slit of 12-, 13-step trough, 14-compression fittings bearing, 15-closeouts, 16-90 ° of cone mouth
Embodiment
As shown in Figure 1 and Figure 2, the wing detector probe of stagnation temperature stagnation pressure of the present utility model is designed to thermometric bar and wing housing two large divisions, and primary clustering comprises: thermometric bar 1, wing housing 2, metal catheter 3 and flange.What air-flow entered wing housing is divided into two-way, leads up to square air admission hole 5 and vent port 6, and with the heat interchange of hollow stepped cylindrical, the resistance of its built-in temperature sensing element Pt100 platinum resistance changes with temperature of incoming flow change, calculates temperature value through follow-up metering circuit; Another road enters bottom through-hole 9, warp
metal catheter 3 causes compression fittings 11, and compression fittings 11 is connected with pressure transducer or the pressure scanning valve with preposition docking pipeline, obtains pressure magnitude.All the other most of air-flows flow through along the wing outer wall of housing, and wing is a kind of contour structures of approximate wing, due to good aerodynamic configuration, makes surrounding flow be disturbed degree low.Wing front and rear edge radius ratio can with reference to 3 to 2; Flange and engine crankcase are tested perforate and are installed end face and coordinate, and are the fixed sturctures of whole detector probe, and flange is installed through hole centre distance can not be waited arrange simultaneously, increase direction error-disable function.The main through hole 4 of wing housing 2 inside should be tried one's best near leading edge, and the wall thickness of guarantee and leading edge center line is the most suitable between 2mm ~ 4mm, and to reduce thermometric heat transfer errors, improve temperature-responsive, wall thickness meets the design needs of bottom through-hole 9 simultaneously; Air admission hole 5 and the vent port 6 of wing front and rear edge, pre-large post-small, sectional area ratio can with reference to 2 to 1, and shape is similar, and the centre of form aligns, so that diffusion, make itself and temperature sensitive bar heat exchange fully, reduce thermometric velocity error, improve measuring accuracy.Hollow stepped cylindrical is packaged with the cylinder thin segment of Pt100 platinum resistance, with the port aligned in position of front and rear edge, it is thickness stepped is because cylinder thin segment and main through hole 4 inwall form annular air-flow path, and the thick section of cylinder and main through hole 4 ensure that clearance fit is located; Pt100 platinum resistance in thermometric bar 1 and the four-core electric connector wiring on top.Wing physical location between main through hole 4 and trailing edge is that metal catheter 3 processes a passage, for reducing difficulty of processing, cuts out at the position line of cylindrical inner wall at a distance of 1.5mm through main through hole 2 inwall
secondary through hole 7, the small linear slit 12 of wire technique, opens 8.5mm bottom main through hole 2 and secondary through hole 7 dark
counterbore, forms Connectivity Section 8 and also ensures that its minimum widith is not less than 1.3mm, so that metal catheter 3 passes, the bottom through-hole 9 that the leading edge outer wall midline position of Connectivity Section 8 correspondence processes 90 ° of cone mouths 15 is communicated with main through hole 2, aperture 1.1mm, guarantee
metal catheter 3 can insert 90 ° of cone mouths 15.Half ball-and-socket type opening 10 is to inserting
type of integrally repairing after 90 ° of cone mouths 15 silver brazing of metal catheter obtains,
metal catheter is T-shape duct in main through hole 2, Connectivity Section 8, secondary through hole 7, step trough 12 and compression fittings bearing 14, and air-flow is introduced in compression fittings 11, wherein: step trough 12 is processed on the flange face on aerofoil profile housing 2 top, makes to pass secondary through hole 7
metal catheter 3 can enter in the through hole in the compression fittings bearing 14 on it; The correspondence position with step trough 12 on end face of flange is fixed in compression fittings bearing 14 silver brazing;
after metal catheter 3 passes from compression fittings bearing 14 T-shape duct horizontal segment, fix with its high temperature brazing, the silver brazing shutoff of top, T-shape duct, compression fittings 11 inserts
positioning round table and compression fittings bearing 14 silver brazing are fixed, and the two ensures the temperature staggered floor in welding technology order.So far,
after metal catheter 3 installs, wing housing 2 end and closeouts 15 silver brazing, closeouts 15 is identical with wing housing 2 bottom cross sectional shape.The flange of thermometric bar 1 dodges breach, and it is corresponding with above-mentioned compression fittings bearing 14 position relationship, do not interfered, and thermometric bar 1 docks fastening with wing housing 2 by flange when ensureing that thermometric bar 1 inserts the main through hole 4 of wing housing 2.
Claims (4)
1. the wing detector probe of stagnation temperature stagnation pressure, is characterized in that: comprise thermometric bar, wing housing, metal catheter and flange;
Described wing housing tip has flange, and top to bottom has a main through hole, and through-bore axis is positioned at housing middle section and the wing leading edge 2mm ~ 4mm of distance housing; Wing leading edge has air admission hole, and trailing edge has vent port, is communicated with respectively with main through hole, and leading edge air admission hole and the trailing edge vent port centre of form align, and leading edge air admission hole sectional area is greater than trailing edge vent port sectional area; Top to bottom also has a secondary through hole, and between main through hole and airfoil trailing edge, secondary through hole has one section to be communicated with at wing housing bottom and main through hole, is not communicated with other each holes; Metal catheter is through secondary through hole and above-mentioned Connectivity Section; The wing leading edge locus of Connectivity Section corresponding housing has a bottom through-hole be communicated with main through hole;
Described bottom through-hole leading edge opening is half ball-and-socket type, and the diameter of bottom through-hole is less than the diameter of half ball-and-socket type opening;
Described metal catheter, through secondary through hole and Connectivity Section, inserts in bottom through-hole, connects with half ball-and-socket type open bottom;
Described thermometric bar is flanged, has accurate temperature sensing element lead-in wire electrical connector above flange; The below of flange is hollow stepped cylindrical;
Described thermometric bar inserts main through hole, the built-in accurate temperature sensing element of its cylinder thin segment, corresponding with aerofoil profile housing air admission hole and vent port position, forms a ring cavity with main through-hole wall; The thick section of cylinder and the same diameter of main through hole, clearance fit;
Described thermometric bar and aerofoil profile housing are fastenedly connected by flange.
2. the wing detector probe of stagnation temperature stagnation pressure according to claim 1, is characterized in that: described accurate temperature sensing element is the A grade platinum resistances such as Pt100 or Pt1000.
3. the wing detector probe of stagnation temperature stagnation pressure according to claim 1 and 2, is characterized in that: described electrical connector is four-core electric connector.
4. the wing detector probe of stagnation temperature stagnation pressure according to claim 1, is characterized in that: described aerofoil profile housing bottom welds airtight with closeouts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420304506.7U CN204241219U (en) | 2014-06-09 | 2014-06-09 | The wing detector probe of stagnation temperature stagnation pressure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420304506.7U CN204241219U (en) | 2014-06-09 | 2014-06-09 | The wing detector probe of stagnation temperature stagnation pressure |
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| CN204241219U true CN204241219U (en) | 2015-04-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420304506.7U Expired - Lifetime CN204241219U (en) | 2014-06-09 | 2014-06-09 | The wing detector probe of stagnation temperature stagnation pressure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034532A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Total temperature and total pressure wing-shaped sensing part |
| CN109540228A (en) * | 2018-12-09 | 2019-03-29 | 中国航发南方工业有限公司 | It is a kind of for measuring the device of microspur hole flow |
| CN109682485A (en) * | 2019-01-08 | 2019-04-26 | 中国航发沈阳发动机研究所 | Temperature test probe, experimental provision |
| US11473508B2 (en) | 2020-03-13 | 2022-10-18 | Rosemount Aerospace Inc. | Flush-mount combined static pressure and temperature probe with flow enhancement feature |
-
2014
- 2014-06-09 CN CN201420304506.7U patent/CN204241219U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034532A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Total temperature and total pressure wing-shaped sensing part |
| CN104034532B (en) * | 2014-06-09 | 2016-06-08 | 中国航空工业集团公司沈阳发动机设计研究所 | Total temperature wing detector probe of total pressure |
| CN109540228A (en) * | 2018-12-09 | 2019-03-29 | 中国航发南方工业有限公司 | It is a kind of for measuring the device of microspur hole flow |
| CN109540228B (en) * | 2018-12-09 | 2020-05-19 | 中国航发南方工业有限公司 | Device for measuring microspur hole flow |
| CN109682485A (en) * | 2019-01-08 | 2019-04-26 | 中国航发沈阳发动机研究所 | Temperature test probe, experimental provision |
| US11473508B2 (en) | 2020-03-13 | 2022-10-18 | Rosemount Aerospace Inc. | Flush-mount combined static pressure and temperature probe with flow enhancement feature |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |