CN207717325U - A kind of measuring device of fanjet nacelle spillage drag - Google Patents
A kind of measuring device of fanjet nacelle spillage drag Download PDFInfo
- Publication number
- CN207717325U CN207717325U CN201721847300.9U CN201721847300U CN207717325U CN 207717325 U CN207717325 U CN 207717325U CN 201721847300 U CN201721847300 U CN 201721847300U CN 207717325 U CN207717325 U CN 207717325U
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- nacelle
- isolation cover
- measuring device
- cone
- balance
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Abstract
The utility model discloses a kind of measuring devices of fanjet nacelle spillage drag, which is characterized in that including：It is equipped with isolation cover between nacelle and throttling cone；Distance piece is equipped between nacelle and isolation cover；Annular groove is arranged in the area of isolation of distance piece；The inner surface of groove is equipped with sealing copper sheet, and sealing copper sheet is used to be sealed the air-flow for entering groove；Pressure measurement rake is in contact with area of isolation, and pressure measurement rake is set in isolation cover, and the total pressure and static pressure for measuring multiple spot at nacelle outlet are harrowed in the pressure measurement；Strut is through nacelle, isolation cover and throttling cone, and throttling cone is for adjusting the gas flow in nacelle；The top of strut is set to inside nacelle, and is in contact with balance；The top of balance is equipped with bolt；Fiaring cone is fixed on the outer rim of bolt.The spillage drag of nacelle can be accurately measured using measuring device provided by the utility model.
Description
Technical field
The utility model is related to fanjet nacelle fields of measurement, more particularly to a kind of fanjet nacelle overflow
The measuring device of resistance.
Background technology
With the rapid development of aeronautical technology, need the performance for more accurately assessing aircraft and engine, especially into
Matching problem between air flue and engine is even more to be related to that aircraft is pneumatic and the key technology of power performance.Engine nacelle is made
For the main resistance component of aircraft, it is extremely necessary to carry out accurate analog study for aerodynamic drag thereon.It is putting into practice
Middle discovery, when the working condition for changing engine, i.e., when governor valve changes charge flow rate, the pneumatic resistance suffered by engine nacelle
Power has significant change, particularly evident in across the supersonic speed stage.In aircraft aerodynamic analysis, usually aircraft engine is simplified to lead to
Shortness of breath cabin carries out drag prediction by wall surface integral.And actual airplane engine is since air intake duct and jet pipe flow are adjustable,
Its Resistance Value and the drag overall value in aircraft band logical shortness of breath cabin have apparent difference.When aircraft normals cruise flight, with Mach number
Difference, the discharge coefficient variation range of aircraft is about 0.6~2.0.Within this range, discharge coefficient changes to aircraft/start
Machine drag effects are smaller.But when air traffic flow coefficient is far from cruise point, when discharge coefficient strongly reduces, Inlet drag drastically increases
Add, is sharply increased to the drag overall of aircraft, when especially engine is in windmill condition, windmill spillage drag sharply increases.
For installing the transonic speed large aircraft of large-bypass-ratio engine, the phenomenon is particularly evident.
Spillage drag is an augmented resistance relative to the aerodynamic drag under engine standard working condition, it be due to
When changing engine work caused by charge flow rate, the spillage drag for accurately measuring fanjet nacelle inlet is special
Property, provide reference for aircraft global design so that aircraft flight is safer.Spillage drag is mainly using calculating fluid force at present
Numerical calculations are learned to obtain, but precision is limited by computational methods and turbulence model etc., the spillage drag being calculated
Precision is low.
Utility model content
The purpose of this utility model is to provide a kind of measuring device of fanjet nacelle spillage drag, existing to solve
The low problem of spillage drag precision to fanjet nacelle in technology.
To achieve the above object, the utility model provides following scheme：
A kind of measuring device of fanjet nacelle spillage drag, including：Nacelle, sealing copper sheet, pressure measurement rake, isolation
Cover, throttling cone, strut, balance, bolt and fiaring cone；
It is equipped with the isolation cover between the nacelle and throttling cone；
Distance piece is equipped between the nacelle and the isolation cover；
Annular groove is arranged in the area of isolation of the distance piece；The inner surface of the groove is equipped with the sealing copper sheet, institute
Sealing copper sheet is stated to be used to be sealed the air-flow for entering the groove；
The pressure measurement rake is in contact with the area of isolation, and pressure measurement rake is set in the isolation cover, the pressure measurement
Harrow the total pressure and static pressure for measuring multiple spot at the nacelle outlet；
The strut is bored through the nacelle, the isolation cover and the throttling, and the throttling cone is for adjusting
State the gas flow in nacelle；
The top of the strut is set to inside the nacelle, and is in contact with the balance；The top of the balance is equipped with
Bolt；The fiaring cone is fixed on the outer rim of the bolt.
Optionally, the nacelle specifically includes nacelle front, nacelle rear portion, cross frame and the first pin；
The one end at the nacelle rear portion is covered in one end of the nacelle front, and fixes the nacelle by the first screw
Front and the nacelle rear portion；
First pin sequentially passes through the nacelle rear portion and the nacelle front, for position the nacelle front and
The nacelle rear portion；
The cross frame is set to the nacelle rear portion, and the cross-shaped is fixed in the nacelle rear portion by the second screw
Frame, and one end of the cross frame is in contact with the nacelle front.
Optionally, the cross frame is internally provided with the first through hole；First through hole matches with the strut.
Optionally, the bolt is fastened on by first through hole on the cross frame, and the bolt is used for will
The nacelle and the cross frame are fixed on the strut.
Optionally, the top of the balance matches with first through hole；The outer surface of the balance is equipped with balance
Protective cover.
Optionally, the outer surface of the isolation cover is equipped with sleeve；
The isolation cover is internally provided with bush support, and the second through hole is equipped in the bush support；The sleeve branch
Frame is used to support the sleeve.
Optionally, the isolation cover further includes：Second pin, third screw；
Second pin sequentially passes through the sleeve and the bush support, and second pin is for positioning the set
Cylinder and the bush support；
The third screw sequentially passes through the sleeve and the bush support, and the third screw is for connecting the set
Cylinder and the bush support.
Optionally, the isolation cover is cylinder.
Optionally, the throttling cone specifically includes：Upper throttling cone, lower throttling cone and soket head cap screw；
The upper throttling cone is connected with the lower throttling cone by the soket head cap screw.
Optionally, the distance piece connects the nacelle and the isolation cover using the structure of labyrinth seal.
According to specific embodiment provided by the utility model, the utility model discloses following technique effects：This practicality is new
Type provides a kind of measuring device of fanjet nacelle spillage drag, reduces throttling cone to the pneumatic of nacelle using isolation cover
Interference, to obtain the spillage drag for being free of any interference under variable water volume flow, to improve the measurement accuracy of spillage drag.
Description of the drawings
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only the utility model
Some embodiments for those of ordinary skill in the art without having to pay creative labor, can also basis
These attached drawings obtain other attached drawings.
Fig. 1 is measuring device structure chart provided by the utility model；
Fig. 2 is balance structural schematic diagram provided by the utility model；
Fig. 3 is nacelle structure schematic diagram provided by the utility model；
Fig. 4 is isolation cover internal structure schematic diagram provided by the utility model；
Fig. 5 is distance piece structural schematic diagram provided by the utility model；
Fig. 6 is throttling wimble structure schematic diagram provided by the utility model；
Fig. 7 is spillage drag provided by the utility model with discharge coefficient variation rule curve figure.
Specific implementation mode
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
The every other embodiment obtained, shall fall within the protection scope of the present invention.
The purpose of this utility model is to provide a kind of measuring device of fanjet nacelle spillage drag, is filled by measuring
It sets and the spillage drag of nacelle is measured, improve the measurement accuracy of spillage drag.
To keep the above objects, features, and advantages of the utility model more obvious and easy to understand, below in conjunction with the accompanying drawings and have
Body embodiment is described in further detail the utility model.
Nacelle is the bridge of engine and body, and nacelle interior conduit provides air intake duct and duct, difference flight for engine
Air intake duct working characteristics had both influenced engine blower performance under state, also influenced full machine performance.Pod drag is with inlet air flow quantitative change
Change different, pod drag is usually known as spillage drag characteristic with the characteristic of changes in flow rate, is nacelle performance basic performance
One of, the utility model proposes a kind of measuring device of fanjet nacelle spillage drag, which really exists
Nacelle spillage drag is measured in high-speed wind tunnel.
Measuring device includes target nacelle, force balance and support, internal resistance measurement device, isolation cover, flow-rate adjustment cone etc..
Measurement method：Wind-tunnel provides incoming simulated conditions, and nacelle, which is directly ventilated, simulates nacelle air inlet, in isolation cover endpiece cloth
It sets flow-rate adjustment cone and changes charge flow rate；Nacelle aerodynamic force is directly measured using balance, total static pressure detection is arranged in nacelle outlet
Device measures the total static pressure in outlet, for calculating discharge coefficient and internal resistance.
Fig. 1 is measuring device structure chart provided by the utility model, as shown in Figure 1, a kind of fanjet nacelle overflows
The measuring device of flow resistance power, including：Nacelle 1, sealing copper sheet 2, pressure measurement rake 3, isolation cover 4, throttling cone 5, strut 6, balance protection
Cover 7, balance 8, bolt 9 and fiaring cone 10；It is equipped with the isolation cover 4 between the nacelle 1 and throttling cone 5；It is described short
Distance piece is equipped between cabin 1 and the isolation cover 4；Annular groove is arranged in the area of isolation of the distance piece；The groove it is interior
Surface is equipped with sealing copper sheet 2, and the sealing copper sheet 2 is used to be sealed the air-flow for entering the groove；Pressure measurement rake 3 with
The area of isolation is in contact, and pressure measurement rake 3 is set in the isolation cover 4, and the pressure measurement rake 3 is for measuring the nacelle
The total pressure and static pressure of multiple spot at 1 outlet；The strut 6 is through the nacelle 1, the isolation cover 4 and described
Throttling cone 5, the throttling cone 5 is for adjusting the gas flow in the nacelle 1；The top of the strut 6 is set to the nacelle 1
Inside, and be in contact with the balance 8；The top of the balance 8 is equipped with bolt 9；The fiaring cone 10 is fixed on the bolt 9
Outer rim.
In measurement process, the aerodynamic force being subject on nacelle 1 is transmitted on balance 8, and Fig. 2 is provided by the utility model
Balance structural schematic diagram, as shown in Fig. 2, being strained by balance 8 pneumatic suffered by generated curent change acquisition nacelle 1
Power, since 8 internal structure of balance is more accurate and fragile, the outer surface of balance 8 is equipped with balance protective cover 7, for protecting balance 8
Internal structure.Nacelle 1 is close with isolation cover 4 but does not contact, and is added by sealing copper sheet 2 among groove machined by proximal end face
Enter to carry out the sealing of air-flow in groove.Pressure measurement rake 3 measures the stagnation pressure and static pressure of multiple spot at 1 outlet of nacelle, is closed by constant entropy
It is the internal resistance that formula and momentum theorem etc. can calculate nacelle 1.Throttling cone 5 can replace different diameters, to adjust in nacelle 1
Flow.Holder realizes the adjusting of 1 angle of attack of nacelle for being connected with the angle of attack mechanism of wind-tunnel.Bolt 9 be used for nacelle 1 and
Cross frame is fixed on strut 6, and fiaring cone 10 is fixed on 9 outer rim of bolt, larger divide occurs with to avoid flowing in nacelle 1
From.
Fig. 3 is nacelle structure schematic diagram provided by the utility model, as shown in figure 3, the nacelle 1 specifically includes nacelle
Front 11, cross frame 12, nacelle rear portion 13, the first screw 14 and the first pin 15；It covers the one end at the nacelle rear portion 13
One end in the nacelle front 11 is covered, and the nacelle front 11 and the nacelle rear portion 13 are fixed by the first screw 14；
First pin 15 sequentially passes through the nacelle rear portion 13 and the nacelle front 11, for positioning 11 He of nacelle front
The nacelle rear portion 13；The cross frame 12 is set to the nacelle rear portion 13, and the nacelle rear portion 13 passes through the second screw 16
The fixed cross frame 12, and one end of the cross frame 12 is in contact with the nacelle front 11；
First screw 14 includes two or more, and first pin 15 includes two or more, second spiral shell
Nail 16 includes two or more, and first screw 14, first pin 15 and second screw 16 occur in pairs.
In practical applications, the bolt 9 is fastened on by first through hole on the cross frame 12, the spiral shell
Bolt 9 is used to the nacelle and the cross frame 12 being fixed on the strut 6.
Fig. 4 is isolation cover internal structure schematic diagram provided by the utility model, as shown in figure 4, the isolation cover 4 is outer
Surface is equipped with sleeve 41；The isolation cover 4 is internally provided with bush support, and the second through hole is equipped in the bush support；Institute
It states bush support and is used to support the sleeve；The isolation cover 4 further includes：Second pin, third screw；Second pin according to
Secondary to pass through the sleeve and the bush support, second pin is for positioning the sleeve and the bush support；It is described
Third screw sequentially passes through the sleeve and the bush support, and the third screw is for connecting the sleeve and the sleeve
Holder；The isolation cover 4 is cylinder.
Aerodynamic interference of the flow-rate adjustment cone to nacelle is reduced using cylindrical isolation cover, it is " dry to obtain under variable water volume flow
Net " spillage drag.Isolation cover length takes 2-3 times of nacelle outlet diameter length, and labyrinth seal, figure are being used with nacelle intersection
5 be distance piece structural schematic diagram provided by the utility model, as shown in figure 5, outlet is divided into internal Sein, outside by distance piece
Seout flows, and when changing internal Sein flows using different cone positions, the static pressure of external Seout can be held essentially constant.Meanwhile
Isolation cover can partial simulation nacelle output flow.
Fig. 6 is throttling wimble structure schematic diagram provided by the utility model, as shown in fig. 6, throttling cone 5 specifically wraps
It includes：Upper throttling cone 51, lower throttling cone 52 and soket head cap screw 53；The upper throttling cone 51 and the lower throttling cone 52 pass through institute
Soket head cap screw 53 is stated to be connected.
Spillage drag is modified with formula (1)
Xt(Ma, φ ...)=X'-Xein-Xeout-Xin (1)
Wherein, XtFor nacelle axial force；X ' is balance axial force measured value；XinIt is always quiet using outlet for nacelle internal resistance
Pressure measured value is calculated according to momentum theorem；XeinFor bottom inner face viscous drag correction item；Xeout
For bottom outer end face viscous drag correction item；
It is applied in real life using above-mentioned measuring device, such as：Carry out experiment in certain 2 meters of magnitude transonic wind tunnel,
Desired effect is reached, Fig. 7 is spillage drag provided by the utility model with discharge coefficient variation rule curve figure, such as Fig. 7
It is shown, first, flow can be easily adjusted by flow-rate adjustment cone, second is that isolation cover and maze trough reach the inside and outside flowing of separation
Function, under identical inlet flow conditions, ventilation flow rate change when, XeoutIt is held essentially constant, illustrates that nacelle back segment pressure is distributed
The interference of introducing is smaller.
The spillage drag of nacelle can be accurately measured using measuring device provided by the utility model, be airplane design
Reference is provided.
Each embodiment is described by the way of progressive in this specification, the highlights of each of the examples are with other
The difference of embodiment, just to refer each other for identical similar portion between each embodiment.
Specific case used herein is expounded the principles of the present invention and embodiment, above example
Explanation be merely used to help understand the method and its core concept of the utility model；Meanwhile for the general technology of this field
Personnel, according to the thought of the utility model, there will be changes in the specific implementation manner and application range.In conclusion
The content of the present specification should not be construed as a limitation of the present invention.
Claims (10)
1. a kind of measuring device of fanjet nacelle spillage drag, which is characterized in that including：Nacelle, sealing copper sheet, pressure measurement
Rake, isolation cover, throttling cone, strut, balance, bolt and fiaring cone；
It is equipped with the isolation cover between the nacelle and throttling cone；
Distance piece is equipped between the nacelle and the isolation cover；
Annular groove is arranged in the area of isolation of the distance piece；The inner surface of the groove is equipped with the sealing copper sheet, described close
Envelope copper sheet is used to be sealed the air-flow for entering the groove；
The pressure measurement rake is in contact with the area of isolation, and pressure measurement rake is set in the isolation cover, and the pressure measurement rake is used
In the total pressure and static pressure that measure multiple spot at the nacelle outlet；
The strut is bored through the nacelle, the isolation cover and the throttling, and the throttling cone is described short for adjusting
Gas flow in cabin；
The top of the strut is set to inside the nacelle, and is in contact with the balance；The top of the balance is equipped with bolt；
The fiaring cone is fixed on the outer rim of the bolt.
2. measuring device according to claim 1, which is characterized in that after the nacelle specifically includes nacelle front, nacelle
Portion, cross frame and the first pin；
The one end at the nacelle rear portion is covered in one end of the nacelle front, and fixes the nacelle front by the first screw
With the nacelle rear portion；
First pin sequentially passes through the nacelle rear portion and the nacelle front, for positioning the nacelle front and described
Nacelle rear portion；
The cross frame is set to the nacelle rear portion, and the cross frame is fixed in the nacelle rear portion by the second screw, and
One end of the cross frame is in contact with the nacelle front.
3. measuring device according to claim 2, which is characterized in that the cross frame is internally provided with the first through hole；
First through hole matches with the strut.
4. measuring device according to claim 3, which is characterized in that the bolt is fastened on by first through hole
On the cross frame, the bolt is used to the nacelle and the cross frame being fixed on the strut.
5. measuring device according to claim 3, which is characterized in that the top of the balance and the first through hole phase
Matching；The outer surface of the balance is equipped with balance protective cover.
6. measuring device according to claim 1, which is characterized in that the outer surface of the isolation cover is equipped with sleeve；
The isolation cover is internally provided with bush support, and the second through hole is equipped in the bush support；The bush support is used
In the support sleeve.
7. measuring device according to claim 6, which is characterized in that the isolation cover further includes：Second pin, third spiral shell
Nail；
Second pin sequentially passes through the sleeve and the bush support, second pin for position the sleeve and
The bush support；
The third screw sequentially passes through the sleeve and the bush support, the third screw for connect the sleeve and
The bush support.
8. measuring device according to claim 1, which is characterized in that the isolation cover is cylinder.
9. measuring device according to claim 1, which is characterized in that the throttling cone specifically includes：Upper throttling cone, lower section
Flow cone and soket head cap screw；
The upper throttling cone is connected with the lower throttling cone by the soket head cap screw.
10. measuring device according to claim 1, which is characterized in that the distance piece is connected using the structure of labyrinth seal
Connect the nacelle and the isolation cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721847300.9U CN207717325U (en) | 2017-12-26 | 2017-12-26 | A kind of measuring device of fanjet nacelle spillage drag |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721847300.9U CN207717325U (en) | 2017-12-26 | 2017-12-26 | A kind of measuring device of fanjet nacelle spillage drag |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207717325U true CN207717325U (en) | 2018-08-10 |
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ID=63049976
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721847300.9U Expired - Fee Related CN207717325U (en) | 2017-12-26 | 2017-12-26 | A kind of measuring device of fanjet nacelle spillage drag |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107860552A (en) * | 2017-12-26 | 2018-03-30 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of measurement apparatus of fanjet nacelle spillage drag |
| CN112985822A (en) * | 2021-04-20 | 2021-06-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet channel test device for simulating coupling effect of air inlet channel and fan |
| CN113252280A (en) * | 2021-04-20 | 2021-08-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle test device capable of simulating air intake and exhaust simultaneously |
-
2017
- 2017-12-26 CN CN201721847300.9U patent/CN207717325U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107860552A (en) * | 2017-12-26 | 2018-03-30 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of measurement apparatus of fanjet nacelle spillage drag |
| CN107860552B (en) * | 2017-12-26 | 2023-10-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Measuring device for overflow resistance of turbofan engine nacelle |
| CN112985822A (en) * | 2021-04-20 | 2021-06-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet channel test device for simulating coupling effect of air inlet channel and fan |
| CN112985822B (en) * | 2021-04-20 | 2021-08-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet channel test device for simulating coupling effect of air inlet channel and fan |
| CN113252280A (en) * | 2021-04-20 | 2021-08-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle test device capable of simulating air intake and exhaust simultaneously |
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Granted publication date: 20180810 Termination date: 20201226 |