CN209459860U - A kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust - Google Patents
A kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust Download PDFInfo
- Publication number
- CN209459860U CN209459860U CN201920576646.2U CN201920576646U CN209459860U CN 209459860 U CN209459860 U CN 209459860U CN 201920576646 U CN201920576646 U CN 201920576646U CN 209459860 U CN209459860 U CN 209459860U
- Authority
- CN
- China
- Prior art keywords
- thrust
- nacelle
- tps
- propulsive thrust
- propulsive
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model discloses a kind of experimental rigs for calibrating TPS propulsive thrust nacelle thrust, including partition, horn mouth, fairing, ventilation strut, support base, air bridges, air inlet steel pipe, reaction balance, measuring system, thrust calibration test measures the thrust that TPS propulsive thrust nacelle generates by reaction balance, carrying out air bridges and labyrinth seal influences after correcting, obtain nacelle actual thrust, theoretical thrust and actual thrust ratio are calculated, the thrust calibration coefficient of corresponding states is obtained；The utility model measures TPS propulsive thrust nacelle thrust by reaction balance, and thrust calibration precision is high；The influence that high pressure airline measures balance is reduced by air bridges, improves the accuracy of balance measurement；It prevents the reversed tail jet of TPS propulsive thrust nacelle from being sucked again by nacelle air inlet by partition, improves the safety and reliability of propulsive thrust calibration test.
Description
Technical field
The present invention relates to wind tunnel test fields, more particularly to a kind of TPS propulsive thrust nacelle calibration test method and its dress
It sets, for the thrust performance in wind tunnel test alignment TPS propulsive thrust nacelle.
Background technique
TPS propulsive thrust experimental technique is the influence that engine reverse thrust device opening is studied in wind-tunnel to aircraft aerodynamic characteristic
A kind of experimental technique.In the test of TPS propulsive thrust, wind-tunnel balance measurement is that model aircraft aerodynamic force and TPS propulsive thrust are short
The sum of the thrust in cabin could obtain propulsive thrust therefore, it is necessary to which the thrust of TPS propulsive thrust nacelle is deducted from balance measured value
To the influence amount of model aircraft aerodynamic characteristic.TPS propulsive thrust nacelle thrust can not be surveyed accurately in TPS propulsive thrust wind tunnel test
Amount, needs to calibrate it using special thrust calibration experimental rig.
Under thrust reverser opening state, the tail jet of TPS propulsive thrust nacelle can be deflected to air inlet direction, be easy quilt
Nacelle air inlet sucks again, and surge occurs so as to cause TPS fan, so that damage fan blade, and existing TPS positive thrust
Nacelle thrust calibration device do not obstruct backward jet device (device need to be separated with reaction balance, avoid influence thrust day
Flat measurement), therefore, it is impossible to carry out thrust school to TPS propulsive thrust nacelle using existing TPS positive thrust nacelle thrust calibration device
It is quasi-.
Summary of the invention
The object of the present invention is to provide a kind of TPS propulsive thrust nacelle calibration test method and device thereof, are used for accurate alignment
TPS propulsive thrust nacelle thrust.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of TPS propulsive thrust nacelle thrust calibration test method, it is characterised in that including following procedure:
The first step installs the calibrating installation in addition to TPS propulsive thrust nacelle, and then carrying out air bridges influences test,
Demarcate the influence of air bridges stiffness by itself, internal high pressure air pressure, temperature and flowing to balance；
TPS propulsive thrust nacelle is mounted on calibrating installation by second step, demarcates effective stress surface of labyrinth gland
Product；
Third step starts to carry out thrust calibration test: starting high pressure air feed system first adjusts gas supply flow to testing shape
State measures the thrust that TPS propulsive thrust nacelle generates by reaction balance, carries out air bridges and labyrinth seal after the system stabilizes
After influencing amendment, nacelle actual thrust is obtained, theoretical thrust and actual thrust ratio is calculated, obtains the thrust calibration of corresponding states
Coefficient；
4th step adjusts gas supply flow to next trystate, repeats third step until off-test；
In above procedure, wind-tunnel is not run, keeps wind-tunnel without incoming flow conditions.
In the above-mentioned technical solutions, by measuring system measure nacelle inside stagnation pressure and temperature, air bridges static pressure and
Temperature, the static pressure of labyrinth gland, reaction balance bear load, using inside nacelle stagnation pressure and measured temperature calculate
The theoretical thrust of nacelle carries out reaction balance measurement load using air bridges static pressure and temperature, labyrinth seal static pressure measurement
Air bridges and labyrinth seal influence amendment.
A kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust, including TPS propulsive thrust nacelle, TPS propulsive thrust nacelle are logical
Cross ventilation strut, support base is fixed on reaction balance, the ventilation strut by the ventilation on support base stay room and air inlet pipe
It is connected, the air inlet of the TPS propulsive thrust nacelle is provided with fairing, and the air inlet and tail of the TPS propulsive thrust nacelle spray
It is provided with partition between mouthful, through-hole is provided on the partition, TPS propulsive thrust nacelle is set on through-hole through being arranged in through-hole
It is equipped with horn mouth, is sealed between horn mouth and TPS propulsive thrust nacelle by contactless labyrinth gland.
In the above-mentioned technical solutions, ventilation, which is stayed, is connected with air bridges between room and air inlet pipe, the air bridges include flexibility
Section and joint steel pipe, air bridges are laid out in " several " font.
In the above-mentioned technical solutions, the flexible joint includes metal bellows and covers outside the flexibility of wavy metal pipe surface
Set, flexible joint have certain freedom degree, can be movable by a small margin.
In the above-mentioned technical solutions, the fairing inner surface is smooth surface, and sectional area is gradually from the inlet to the outlet
Reduce.
In the above-mentioned technical solutions, the partition is fixedly connected on the hole wall of wind-tunnel, and the through-hole on partition is circular hole, if
It sets in the center of partition.
In the above-mentioned technical solutions, the partition includes plate and fixed frame, and the fixed frame connects by the way that connector is fixed
It is connected on wind tunnel wall, plate is fixed on fixed frame, and circular hole is arranged on plate.
In the above-mentioned technical solutions, it is used to seal filled with felt between the partition and hole hole wall.
In the above-mentioned technical solutions, the horn mouth is prominent and perforative horn structure.
In the above-mentioned technical solutions, it is used to seal filled with felt between the horn mouth and partition.
Design principle of the invention is as follows: carrying out precise measurement to TPS propulsive thrust nacelle thrust using reaction balance, utilizes
Air bridges, which reduce pressure-air and measure balance, to be influenced, and prevents the reversed tail jet of nacelle from damaging to TPS fan using partition.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are:
TPS propulsive thrust nacelle thrust is measured by reaction balance, thrust calibration precision is high；High pressure is reduced by air bridges
The influence that air pipe line measures balance improves the accuracy of balance measurement；The reversed tail of TPS propulsive thrust nacelle is prevented by partition
Jet flow is sucked again by nacelle air inlet, improves the safety and reliability of propulsive thrust calibration test.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, in which:
Fig. 1 is a kind of structural schematic diagram of experimental rig for calibrating TPS propulsive thrust nacelle thrust；
Wherein: 1 is wind tunnel wall, and 2 be fairing, and 3 be partition, and 4 be TPS propulsive thrust nacelle, and 5 be ventilation strut, and 6 are
Support base, 7 be air bridges, and 8 be reaction balance, and 9 be air inlet pipe, and 10 be horn mouth.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Any feature disclosed in this specification (including any accessory claim, abstract and attached drawing), except non-specifically chatting
It states, can be replaced by other alternative features that are equivalent or have similar purpose.That is, unless specifically stated, each feature is only
It is an example in a series of equivalent or similar characteristics.
As shown in Fig. 1, the present embodiment include partition, horn mouth, fairing, ventilation strut, support base, air bridges, into
Gas steel pipe, reaction balance, measuring system etc..
TPS propulsive thrust nacelle is fixed on reaction balance by ventilation strut, support base, and ventilation strut passes through on support base
Ventilation stay room be connected with air bridges, air bridges are connected with air inlet pipe.Pressure-air is ventilated through air inlet pipe, air bridges, support base
Enter TPS propulsive thrust nacelle, driving TPS turbine rotation in room, ventilation strut, to drive fan rotation, generate thrust, thrust
Balance measures the actual thrust that TPS propulsive thrust nacelle generates.
Ventilation strut is used to support TPS propulsive thrust nacelle, and ventilation strut is hollow bar, and inside is high air pressure passages,
For providing high drive air to TPS propulsive thrust nacelle；It is connected firmly between ventilation strut and TPS propulsive thrust nacelle by screw,
Therebetween it is sealed by O-shaped rubber seal.
Support base is connected firmly on reaction balance by screw, has ventilation to stay room, ventilation one end in room and ventilation on support base
Strut is connected, and the other end is connected with air bridges, and ventilation is stayed between room and ventilation strut, air bridges and connected firmly by screw, by O-shaped
Rubber seal is sealed.
Air inlet pipe is mainly used for connecting air bridges and high pressure air feed system, solid by screw between air inlet steel pipe and air bridges
Connection, is sealed using O-shaped rubber seal.
To reduce the influence that high pressure airline measures balance, air bridges are installed on pipeline, air bridges are " several " word
Shape structure, is made of flexible joint and joint steel pipe；Flexible joint is made of metal bellows and flexible jacket, and inside is wavy metal
Pipe, outside is flexible jacket, therefore flexible joint can be movable by a small margin；Flexible joint totally three, both direction is consistent, another with
It is vertical, when pressure-air from air bridges by when, three flexible joints mutually absorb each other because of the displacement generated by compression swelling,
Reduce the influence measured balance；Static pressure and temperature measuring point are disposed in air bridges, it is empty for measuring air bridges internal high pressure
The pressure and temperature of gas.
Fairing is installed in TPS propulsive thrust nacelle import, and fairing inner surface is smooth surface, is cut from the inlet to the outlet
Area gradually reduces.The effect of fairing is rectified to the air-flow for entering TPS propulsive thrust nacelle, prevents air-flow uneven
Cause the TPS fan inside nacelle that surge occurs, damages fan blade；Fairing exit end face by screw with TPS is counter pushes away
Power nacelle connects firmly, and is sealed by O-shaped rubber seal therebetween.
The reversed tail jet of TPS propulsive thrust nacelle is sucked again by nacelle air inlet in order to prevent, and TPS fan is caused to occur
Surge damages fan blade, one piece of partition is arranged between TPS propulsive thrust nacelle air inlet and nozzle, for preventing TPS anti-
The reversed tail jet of thrust nacelle is sprayed to import direction.Partition is plank+steel framework structure, and steel framework structure passes through spiral shell
Nail is fixed on wind tunnel wall, and plank is fixed on steel framework, and felt seal is used between partition and wind tunnel wall；In partition
The heart has a circular hole, and TPS propulsive thrust nacelle is passed through from this circular hole, and horn mouth is installed on circular hole, and horn mouth is prominent and perforative
Horn structure uses felt seal between horn mouth and partition, by contactless between horn mouth and TPS propulsive thrust nacelle
Labyrinth gland sealing, has the function that sealing and not power transmission, labyrinth seal two sides are disposed with static pressure measurement point, for measuring
Labyrinth seal two sides pressure, to calculate labyrinth seal pressure action power.
Carrying out the test of TPS propulsive thrust nacelle thrust calibration using the device of the invention, specific step is as follows:
The first step installs the calibrating installation in addition to TPS propulsive thrust nacelle, and then carrying out air bridges influences test,
The influence of air bridges stiffness by itself, internal high pressure air pressure, temperature and flowing to balance is demarcated, to test in thrust calibration
When on balance measurement data carry out air bridges influence amendment；
TPS propulsive thrust nacelle is mounted on calibrating installation by second step, demarcates effective stress of aforementioned labyrinth gland
Area corrects its influence to balance measurement to calculate labyrinth seal pressure action power when thrust calibration is tested；
Step 3: starting to carry out thrust calibration test: starting high pressure air feed system first adjusts gas supply flow to testing shape
State measures the stagnation pressure and temperature, the static pressure of air bridges and temperature, labyrinth inside nacelle by measuring system after the system stabilizes
The load that static pressure, the reaction balance of sealing device are born；Utilize the reason of stagnation pressure and measured temperature calculating nacelle inside nacelle
By thrust, using air bridges static pressure and temperature, labyrinth seal static pressure measurement to reaction balance measurement load carry out air bridges and
Labyrinth seal influences amendment, obtains the actual thrust of TPS propulsive thrust nacelle generation；Finally calculate theoretical thrust and actual thrust ratio
Value, obtains the thrust calibration coefficient of corresponding states；
Step 4: adjusting gas supply flow to next trystate, third step is repeated.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (9)
1. it is a kind of calibrate TPS propulsive thrust nacelle thrust experimental rig, it is characterised in that including partition, horn mouth, fairing,
Ventilate strut, support base, air bridges, air inlet steel pipe, reaction balance, measuring system, TPS propulsive thrust nacelle by ventilation strut,
Support base is fixed on reaction balance, and the ventilation strut stays room by the ventilation on support base and is connected with air inlet pipe, the TPS
The air inlet of propulsive thrust nacelle is provided with fairing, is provided between the air inlet and nozzle of the TPS propulsive thrust nacelle
Partition, through-hole is provided on the partition, and TPS propulsive thrust nacelle is provided with horn mouth, loudspeaker through being arranged in through-hole on through-hole
It is sealed between mouth and TPS propulsive thrust nacelle by contactless labyrinth gland.
2. a kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust according to claim 1, it is characterised in that ventilation is stayed
Air bridges are connected between room and air inlet pipe, the air bridges include flexible joint and joint steel pipe, and air bridges are in " several " font cloth
Office.
3. a kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust according to claim 2, it is characterised in that described soft
Property section include metal bellows and cover the flexible jacket in wavy metal pipe surface, between flexible joint can mutually activity, be used for
Absorb respective expansion displacement.
4. a kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust according to claim 1, it is characterised in that described whole
Stream device inner surface is smooth surface, and sectional area gradually reduces from the inlet to the outlet.
5. it is according to claim 1 it is a kind of calibrate TPS propulsive thrust nacelle thrust experimental rig, it is characterised in that it is described every
Plate is fixedly connected on the hole wall of wind-tunnel, and the through-hole on partition is circular hole, and the center of partition is arranged in.
6. it is according to claim 5 it is a kind of calibrate TPS propulsive thrust nacelle thrust experimental rig, it is characterised in that it is described every
Plate includes plate and fixed frame, and the fixed frame is fixedly attached on wind tunnel wall by connector, and plate is fixed on fixed frame
On, circular hole is arranged on plate.
7. it is according to claim 6 it is a kind of calibrate TPS propulsive thrust nacelle thrust experimental rig, it is characterised in that it is described every
Filled with felt for sealing between plate and hole hole wall.
8. a kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust according to claim 1, it is characterised in that the loudspeaker
Mouth is prominent and perforative horn structure.
9. a kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust according to claim 1, it is characterised in that the loudspeaker
Between mouth and partition filled with felt for sealing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920576646.2U CN209459860U (en) | 2019-04-25 | 2019-04-25 | A kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920576646.2U CN209459860U (en) | 2019-04-25 | 2019-04-25 | A kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209459860U true CN209459860U (en) | 2019-10-01 |
Family
ID=68048285
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920576646.2U Expired - Fee Related CN209459860U (en) | 2019-04-25 | 2019-04-25 | A kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209459860U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111735602A (en) * | 2020-08-10 | 2020-10-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-speed wind tunnel test model abdominal bracing system |
| CN110806302B (en) * | 2019-11-21 | 2021-01-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Pressure compensation device capable of decoupling six-component acting force |
| CN115615654A (en) * | 2022-11-15 | 2023-01-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Test device and method for calibrating flow influence of backflow type air bridge |
| CN117606741A (en) * | 2024-01-18 | 2024-02-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Non-contact air-tight sealing device applied to wind tunnel balance calibration and application method |
-
2019
- 2019-04-25 CN CN201920576646.2U patent/CN209459860U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110806302B (en) * | 2019-11-21 | 2021-01-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Pressure compensation device capable of decoupling six-component acting force |
| CN111735602A (en) * | 2020-08-10 | 2020-10-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-speed wind tunnel test model abdominal bracing system |
| CN111735602B (en) * | 2020-08-10 | 2020-11-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-speed wind tunnel test model abdominal bracing system |
| CN115615654A (en) * | 2022-11-15 | 2023-01-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Test device and method for calibrating flow influence of backflow type air bridge |
| CN115615654B (en) * | 2022-11-15 | 2023-03-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Test device and method for calibrating flow influence of backflow type air bridge |
| CN117606741A (en) * | 2024-01-18 | 2024-02-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Non-contact air-tight sealing device applied to wind tunnel balance calibration and application method |
| CN117606741B (en) * | 2024-01-18 | 2024-04-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Non-contact air-tight sealing device applied to wind tunnel balance calibration and application method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110031181A (en) | A kind of TPS propulsive thrust nacelle thrust calibration test method | |
| CN209459860U (en) | A kind of experimental rig for calibrating TPS propulsive thrust nacelle thrust | |
| US7565269B2 (en) | Thrust correction | |
| Sondergaard et al. | Control of low-pressure turbine separation using vortex-generator jets | |
| CN112945443B (en) | Jet pipe thrust measurement platform | |
| Lee et al. | Wind-tunnel studies of F/A-18 tail buffet | |
| GB2452026A (en) | Aerofoil or instrumentation rake with integrally formed instrumentation elements | |
| CN110595729A (en) | Multi-jet flow interference test device for hypersonic wind tunnel surface symmetry model | |
| CN104848904A (en) | Air duct flow measuring system | |
| CN112945306B (en) | Test platform for simultaneously measuring thrust and flow of double-duct spray pipe | |
| Sutliff et al. | Low-speed fan noise reduction with trailing edge blowing | |
| CN102607799A (en) | Device for changing Mach number in supersonic velocity wind tunnel model experiment and working method | |
| CN113479343A (en) | Integrated test method for air inlet channel and force measurement | |
| CN113946904B (en) | Design method of large-size low-noise spray pipe | |
| CN209400562U (en) | A kind of pitot | |
| CN208534819U (en) | Device for the test of fan aeroperformance | |
| CN102564726A (en) | Air bridge for dynamic simulation experiment of high-speed wind tunnel | |
| Anabtawi et al. | An experimental study of vortex generators in boundary layer ingesting diffusers with a centerline offset | |
| CN212003680U (en) | Fixing device for wind measuring sensor of driving face | |
| CN113432828A (en) | Air bridge device based on annular balance | |
| Hathaway et al. | NASA low-speed centrifugal compressor for three-dimensional viscous code assessment and fundamental flow physics research | |
| Compton III et al. | Jet effects on the boattail axial force of conical afterbodies at subsonic and transonic speeds | |
| CN117309310A (en) | High-pressure jet flow force measuring device for wind tunnel test | |
| CN115493802B (en) | Internal and external flow aerodynamic decoupling structure of body propulsion integrated model and working installation method | |
| Hathaway et al. | NASA low-speed centrifugal compressor for 3-D viscous code assessment and fundamental flow physics research |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191001 Termination date: 20210425 |