CN203298992U - Aerodynamic performance testing device - Google Patents
Aerodynamic performance testing device Download PDFInfo
- Publication number
- CN203298992U CN203298992U CN201320277799XU CN201320277799U CN203298992U CN 203298992 U CN203298992 U CN 203298992U CN 201320277799X U CN201320277799X U CN 201320277799XU CN 201320277799 U CN201320277799 U CN 201320277799U CN 203298992 U CN203298992 U CN 203298992U
- Authority
- CN
- China
- Prior art keywords
- runner
- primary air
- pressure
- flow
- measuring
- 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 - Lifetime
Links
Images
Abstract
The utility model discloses an aerodynamic performance testing device, which comprises an air inlet passage, a main air flow passage and a purge flow passage. The main air flow passage is provided with a rotating measuring mechanism, a first flow measuring unit, a first flow adjusting unit, and a first suction fan. The purge flow passage is provided with a second flow measuring unit, a second flow adjusting unit, and a second suction fan. The inner wall of the air inlet passage and the inner wall of the purge flow passage are respectively and circumferentially provided with a pressure measuring unit used for measuring the pressure of the air flow. According to the technical scheme of the utility model, the aerodynamic performance testing device provides a quantitative means for evaluating the performances of a particle separator. Therefore, whether the performances of the particle separator are in accordance with the performance indexes of a complete engine or not can be conveniently tested.
Description
Technical field
The utility model relates to the turboshaft engine field, especially, relates to a kind of aeroperformance test unit of the particle separator for turboshaft engine.
Background technology
Inertial Particle Separator is the peculiar admission gear of turboshaft engine, and the runner of particle separator divides primary air and removes stream.The major function of particle separator is the foreign object (such as sand dust, leaf, grass, flying bird etc.) that air inlet and removing enter engine inlets, and the separation principle of particle separator is to set up inertial force field by suitable runner profile or leaf grating to reach the purpose of separating foreign object.
The performance of particle separator directly has influence on the serviceable life of turboshaft engine, and therefore, necessary particle separator to turboshaft engine carries out the test of air inlet runner pitot loss, verifies with examination whether the performance index of particle separator meet design requirement.
The utility model content
The utility model purpose is to provide a kind of test unit of aeroperformance for particle separator, to solve the technical matters of test particle separation vessel aeroperformance.
For achieving the above object, the technical solution adopted in the utility model is as follows:
The utility model provides a kind of aeroperformance test unit, is applicable to the aeroperformance test of particle separator, comprising: air intake duct, primary air runner and removing stream runner;
Primary air runner and removing stream runner all are connected to air intake duct, and the air-flow that enters air intake duct is divided into the two-way outflow through primary air runner and removing stream runner;
The primary air runner is provided with for the wheel measuring mechanism of measuring primary air runner overdraught pressure, be used for measuring the air flow rate of the primary air runner of flowing through the first flow measurement mechanism, be used for regulating primary air runner overdraught flow the first flow regulating device, and be used for generating first of the swabbing action power blower fan of bleeding on the primary air runner;
Remove the stream runner be provided with for measurement flow through the air flow rate of removing the stream runner the second measuring device, be used for regulating the second quantity regulating device of removing stream runner overdraught flow, and be used for generating second of the swabbing action power blower fan of bleeding removing on the stream runner;
The inwall of air intake duct and removing stream runner upwards is being equipped with for the pressure measurement cell of measuring stream pressure in week.
Further, wheel measuring mechanism comprises the rotary test disk on the inwall that is arranged on the primary air runner, rotary test disk week upwards is installed with pressure measurement cell, the rotary test disk is upwards rotatable in the week of primary air runner inner wall, and then drives the pressure measurement cell rotation that is fixedly arranged on the rotary test disk.
Further, pressure measurement cell comprises to be measured mount pad and is arranged on the comb formula pressure measuring tube of measuring on mount pad, and comb formula pressure measuring tube is perpendicular to inwall and radially extension.
Further, the inwall of air intake duct and removing stream runner upwards has been evenly arranged a plurality of pressure measurement cells in week, and be intervally distributed with a plurality of pressure survey probes on the comb formula pressure measuring tube on each pressure measurement cell, a plurality of pressure survey probes on comb formula pressure measuring tube are at air intake duct or remove on the whole circumferencial direction of stream runner inner wall that the anchor ring such as to be spaced apart.
Further, wheel measuring mechanism be included in the primary air runner inner wall week upwards along the vertically disposed a plurality of static boles of primary air flow direction in the primary air runner.
The utlity model has following beneficial effect:
The utility model aeroperformance test unit, by air intake duct, primary air runner being set and removing the stream runner and simulate the generation primary air and remove stream, and the inwall at air intake duct and removing stream runner upwards is being equipped with for the pressure measurement cell of measuring stream pressure in week, the primary air runner is provided with for the wheel measuring mechanism of measuring primary air runner overdraught pressure, has realized the import cross section stagnation pressure value P to air intake duct
t1, the outlet stagnation pressure value P in the primary air runner
t2Isoparametric measurement, for follow-up aeroperformance test provides reliable research technique, and test unit is simple in structure, easy to operate.
Except purpose described above, feature and advantage, the utility model also has other purpose, feature and advantage.Below with reference to figure, the utility model is described in further detail.
Description of drawings
The accompanying drawing that forms the application's a part is used to provide further understanding of the present utility model, and illustrative examples of the present utility model and explanation thereof are used for explaining the utility model, do not form improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the principle schematic of the utility model preferred embodiment aeroperformance test unit;
Fig. 2 is the structural representation of the utility model preferred embodiment aeroperformance test unit; And
Fig. 3 is the structural representation of the utility model preferred embodiment wheel measuring mechanism.
Description of reference numerals:
1, air intake duct; 2, primary air runner; 3, first flow measurement mechanism; 4, first flow regulating device;
5, first blower fan of bleeding; 6, remove the stream runner; 7, second measuring device; 8, second quantity regulating device;
9, second blower fan of bleeding; 10, wheel measuring mechanism; 110, rotary test disk; 111, comb formula pressure measuring tube;
111a, measuring probe; 130, static bole; 11, radome fairing; 20, cone; 21, inlet cone; 23, tail cone.
Embodiment
Below in conjunction with accompanying drawing, embodiment of the present utility model is elaborated, but the multitude of different ways that the utility model can be defined by the claims and cover is implemented.
Referring to figs. 1 through Fig. 2, the utility model provides a kind of aeroperformance test unit, is applicable to the aeroperformance test of particle separator, and this aeroperformance test unit comprises: air intake duct 1, primary air runner 2 and removing stream runner 6; Primary air runner 2 and removing stream runner 6 all are connected to air intake duct 1, and the air-flow that enters air intake duct 1 along direction shown in arrow in Fig. 1, Fig. 2 is divided into the two-way outflow through primary air runner 2 and removing stream runner 6.In the present embodiment, with reference to Fig. 2, the radome fairing 11 of boring section within it is provided with cone 20, cone 20 axially parallel with the axis of radome fairing 11, and the middle part of cone 20 is large, and both ends are respectively inlet cone 21 and the tail cone 23 that is cone tip shape; The close outside diameter of the endpiece of radome fairing 11 has annular bypass and exports to form removing stream runner 6, and the entrance point of radome fairing 11 coordinates the air intake duct 1 that forms annular with inlet cone 21, and the endpiece of radome fairing 11 coordinates the annular primary air runner 2 of formation with tail cone 23.With reference to Fig. 1, primary air runner 2 is provided with for the wheel measuring mechanism 10 of measuring primary air runner 2 overdraught pressure, be used for measuring the air flow rate of the primary air runner 2 of flowing through first flow measurement mechanism 3, be used for regulating primary air runner 2 overdraught flows first flow regulating device 4, and be used for generating first of the swabbing action power blower fan 5 of bleeding on primary air runner 2; Remove stream runner 6 be provided with for measurement flow through the air flow rate of removing stream runner 6 second measuring device 7, be used for regulating the second quantity regulating device 8 of removing stream runner 6 overdraught flows, and be used for generating second of the swabbing action power blower fan 9 of bleeding removing on stream runner 6; The inwall of air intake duct 1 and removing stream runner 6 upwards is being equipped with for the pressure measurement cell of measuring stream pressure in week.The pressure measurement cell that is distributed on air intake duct 1 is arranged on the I-I cross section of Fig. 2, is used for the import cross section stagnation pressure value P of the air intake duct of measurement particle separator
t1Be distributed in the pressure measurement cell of removing on stream runner 6 and be arranged on Fig. 2 III-III cross section, be used for measuring removing flow export stagnation pressure P
t3The wheel measuring mechanism 10 that is distributed on primary air runner 2 is arranged in Fig. 2 II-II cross section, is used for measuring the outlet stagnation pressure value P in the primary air runner
t2The simulation of the utility model aeroperformance test unit generates air intake duct 1, primary air runner 2 and removes stream runner 6, and can be to the import cross section stagnation pressure value P of air intake duct
t1, the outlet stagnation pressure value P in the primary air runner
t2Isoparametric measurement, for follow-up aeroperformance test provides reliable test figure, and test unit is simple in structure, easy to operate.
In the present embodiment, with reference to Fig. 3, wheel measuring mechanism 10 comprises the rotary test disk 110 on the inwall that is arranged on primary air runner 2,110 weeks of rotary test disk upwards are installed with pressure measurement cell, rotary test disk 110 is upwards rotatable in the week of primary air runner 2 inwalls, and then drives the pressure measurement cell rotation that is fixedly arranged on rotary test disk 110.In the present embodiment, upwards evenly be intervally distributed with 3 pressure measurement cells (laying respectively at 0 ° of position of wheel measuring disk 110,120 ° of positions and 240 ° of positions) week of rotary test disk 110, each pressure measurement cell comprises to be measured mount pad and is arranged on the comb formula pressure measuring tube 111 of measuring on mount pad, and comb formula pressure measuring tube 111 is perpendicular to inwall and radially extension.Be distributed with 5 measuring probe 111a on each comb formula pressure measuring tube 111.When carrying out pressure survey, at first the rotary test disk 110 of wheel measuring mechanism 10 is positioned at 0 ° of position, measure one time flow field, then in the direction of the clock (along the airintake direction shown in arrow in Fig. 1 and Fig. 2, favorable current is seen) rotate 11 times,, at interval of exit flow field force value of 10 ° of measurements, stablized 30 seconds at every turn.While carrying out next status adjustment, first test plate is adjusted back to 0 ° of position.Preferably, upwards along the interior primary air flow direction of primary air runner 2, a plurality of static boles 130 are set vertically in the week of primary air runner 2 inwalls.In the present embodiment, the week of primary air runner 2 inwalls upwards is evenly distributed with 3 static boles 130, and with reference to Fig. 3, static bole 130 lays respectively at 60 ° of positions of wheel measuring disk 110,180 ° of positions and 300 ° of positions, and the aperture of static bole 130 is
Static bole 130 is vertical with air flow direction, is used for measuring the average static pressure in primary air outlet
in the present embodiment, the inwall of air intake duct 1 and removing stream runner 6 upwards has been evenly arranged a plurality of pressure measurement cells in week, this pressure measurement cell is the same with the pressure measurement cell structure on being arranged on rotary test disk 110, include and measure mount pad and be arranged on the comb formula pressure measuring tube 111 of measuring on mount pad, and be intervally distributed with a plurality of pressure survey probe 111a on the comb formula pressure measuring tube 111 on each pressure measurement cell, the anchor ring interval difference such as a plurality of pressure survey probe 111a on comb formula pressure measuring tube 111 press on the whole circumferencial direction of air intake duct 1 or removing stream runner 6 inwalls.In specific embodiment, the quantity of measuring unit can need to be carried out relative set according to test.
The utility model also provides a kind of aeroperformance test method, is applicable to the aeroperformance test of particle separator, comprises the following steps:
At the primary air runner of particle separator and remove simulation in the stream runner and generate primary air and remove stream;
Measure the import cross section stagnation pressure value P of the air intake duct of particle separator
t1
Regulate respectively the size of primary air rate of discharge Q1 and the removing flow export flow Q2 of particle separator, make to remove to meet preset value than SCR, wherein remove and compare SCR=Q2/Q1;
Measure the interior outlet stagnation pressure value P of primary air runner of particle separator
t2
Computing formula according to air inlet pitot loss value Δ P: Δ P=(P
t1-P
t2)/P
t1, calculate the air inlet pitot loss value Δ P of particle separator, wherein, P
t1For the import cross section stagnation pressure value of air intake duct, P
t2Outlet stagnation pressure value for the primary air runner.
Preferably, primary air rate of discharge Q1 and the removing flow export flow Q2 size of the utility model aeroperformance test method by regulating particle separator,, at different primary air rate of discharge Q1 and under removing than the state of SCR, measure the air inlet pitot loss value Δ P of particle separator.Wherein, primary air rate of discharge Q1 can regulate by first flow regulating device 4, removing flow export flow Q2 can regulate by second quantity regulating device 8, primary air rate of discharge Q1 can be by first flow measurement mechanism 3 measuring flow sizes, removing flow export flow Q2 can be by second measuring device 7 measuring flow size, by regulating and measure primary air rate of discharge Q1 and removing stream flow Q2, under can and removing than the state of SCR at different primary air rate of discharge Q1, measure the air inlet pitot loss value Δ P of particle separator.
Preferably, the utility model aeroperformance test method also is included in different primary air rate of discharge Q1 and removes than under the state of SCR, measure the step of the primary air top hole pressure distortion index DC60 of particle separator, the measuring process of primary air top hole pressure distortion index DC60 comprises:
Measure the average static pressure in primary air outlet of particle separator
And the average stagnation pressure in primary air outlet
According to formula
Calculate the average dynamic pressure q in primary air outlet of particle separator;
Computing formula according to primary air top hole pressure distortion index DC60:
Calculate the primary air top hole pressure distortion index DC60 of particle separator, wherein, P
60min, for the given 60 ° of fan-shaped minimum average B configuration stagnation pressures in the outlet of primary air runner, can measure and calculate by wheel measuring mechanism 10.Pressure when wherein, stagnation pressure refers to that air-flow constant entropy ground stagnation is zero to speed; Static pressure refers to fluid produces when flowing the pressure perpendicular to the fluid motion direction.
In order better to show the relation between each parameter, the utility model aeroperformance test method also comprises the relation curve of drawing air inlet pitot loss value Δ P, primary air top hole pressure distortion index DC60 and primary air rate of discharge Q1 and removing flow export flow Q2.
In the present embodiment, the primary air rate of discharge is 2kg/s～15kg/s; Removing is 10%, 12%, 14%, 16%, 18%, 20% or 22% than SCR.In the present embodiment test method, aeroperformance trystate table is as follows:
Wherein, " √ " expression has been carried out the fluid field pressure test to this state, and "-" expression is not carried out the fluid field pressure test to this state.
The utility model aeroperformance test method, generate primary air and remove stream by simulation, and measure respectively the import cross section stagnation pressure value P of air intake duct
t1And the outlet stagnation pressure value P in the primary air runner
t2Thereby, can calculate the air inlet pitot loss value Δ P for the important performance of weighing particle separator, for the performance of assessing particle separator provides the quantification means, whether the performance of being convenient to the test particle separation vessel meets engine overall performance index.The utility model is primary air rate of discharge Q1 and the removing flow export flow Q2 size by regulating particle separator further,, at different primary air rate of discharge Q1 and under removing than the state of SCR, measure the air inlet pitot loss value Δ P of particle separator and the primary air top hole pressure distortion index DC60 of particle separator; Further, also can draw according to corresponding data the relation curve of air inlet pitot loss value Δ P, primary air top hole pressure distortion index DC60 and primary air rate of discharge Q1 and removing flow export flow Q2, thereby for the performance test of particle separator provides detailed parameter to reach relation curve intuitively, be convenient to comprehensively verify the performance of particle separator, so that the engine overall performance is up to standard.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (5)
1. an aeroperformance test unit, be applicable to the aeroperformance test of particle separator, it is characterized in that, comprising: air intake duct (1), primary air runner (2) and removing stream runner (6);
Described primary air runner (2) and described removing stream runner (6) all are connected to described air intake duct (1), and the air-flow that enters described air intake duct (1) is divided into the two-way outflow through described primary air runner (2) and described removing stream runner (6);
Described primary air runner (2) is provided be used to the wheel measuring mechanism (10) of measuring described primary air runner (2) overdraught pressure, be used for to measure the first flow measurement mechanism (3) of the air flow rate of the described primary air runner (2) of flowing through, be used for regulating described primary air runner (2) overdraught flow first flow regulating device (4), and be used at upper first of the swabbing action power blower fan (5) of bleeding that generates of described primary air runner (2);
Described removing stream runner (6) be provided with for measurement flow through described removing stream runner (6) air flow rate second measuring device (7), be used for regulating described removing stream runner (6) overdraught flow second quantity regulating device (8), and be used at upper second of the swabbing action power blower fan (9) of bleeding that generates of described removing stream runner (6);
The inwall of described air intake duct (1) and described removing stream runner (6) upwards is being equipped with for the pressure measurement cell of measuring stream pressure in week.
2. aeroperformance test unit according to claim 1, is characterized in that,
Described wheel measuring mechanism (10) comprises the rotary test disk (110) on the inwall that is arranged on described primary air runner (2), described rotary test disk (110) week upwards is installed with pressure measurement cell, described rotary test disk (110) is upwards rotatable in the week of described primary air runner (2) inwall, and then drives the described pressure measurement cell rotation that is fixedly arranged on described rotary test disk (110).
3. aeroperformance test unit according to claim 2, is characterized in that,
Described pressure measurement cell comprises to be measured mount pad and is arranged on comb formula pressure measuring tube (111) on described measurement mount pad, and described comb formula pressure measuring tube (111) is perpendicular to described inwall and radially extend.
4. aeroperformance test unit according to claim 3, is characterized in that,
The inwall of described air intake duct (1) and described removing stream runner (6) upwards is being evenly arranged a plurality of described pressure measurement cells week, and be intervally distributed with a plurality of pressure survey probes (111a) on the described comb formula pressure measuring tube (111) on each described pressure measurement cell, a plurality of described pressure survey probe (111a) on described comb formula pressure measuring tube (111) such as is at the anchor ring on the whole circumferencial direction of described air intake duct (1) or described removing stream runner (6) inwall spaced apart.
5. aeroperformance test unit according to claim 4, is characterized in that,
Described wheel measuring mechanism (10) is included in the week of described primary air runner (2) inwall upwards along described primary air runner (2) the vertically disposed a plurality of static boles of interior primary air flow direction (130).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320277799XU CN203298992U (en) | 2013-05-20 | 2013-05-20 | Aerodynamic performance testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320277799XU CN203298992U (en) | 2013-05-20 | 2013-05-20 | Aerodynamic performance testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203298992U true CN203298992U (en) | 2013-11-20 |
Family
ID=49574997
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320277799XU Expired - Lifetime CN203298992U (en) | 2013-05-20 | 2013-05-20 | Aerodynamic performance testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203298992U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103234730A (en) * | 2013-05-20 | 2013-08-07 | 中国航空动力机械研究所 | Pneumatic performance testing method as well as pneumatic performance testing device |
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
| CN111044296A (en) * | 2019-12-13 | 2020-04-21 | 湖南汉能科技有限公司 | Comprehensive test bed and test method for aero-engine parts |
| CN111103146A (en) * | 2019-12-13 | 2020-05-05 | 湖南汉能科技有限公司 | Rotary measuring device of aero-engine test bed |
-
2013
- 2013-05-20 CN CN201320277799XU patent/CN203298992U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103234730A (en) * | 2013-05-20 | 2013-08-07 | 中国航空动力机械研究所 | Pneumatic performance testing method as well as pneumatic performance testing device |
| CN111024402A (en) * | 2019-12-13 | 2020-04-17 | 湖南汉能科技有限公司 | Aeroengine test bench installing system |
| CN111044296A (en) * | 2019-12-13 | 2020-04-21 | 湖南汉能科技有限公司 | Comprehensive test bed and test method for aero-engine parts |
| CN111103146A (en) * | 2019-12-13 | 2020-05-05 | 湖南汉能科技有限公司 | Rotary measuring device of aero-engine test bed |
| CN111044296B (en) * | 2019-12-13 | 2021-03-23 | 湖南汉能科技有限公司 | Comprehensive test bed and test method for aero-engine parts |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103234730B (en) | Pneumatic performance testing method as well as pneumatic performance testing device | |
| CN101813554B (en) | Air inlet experimental facility capable of carrying out measurement on the same model and operating method thereof | |
| Ganz et al. | Boeing 18-inch fan rig broadband noise test | |
| CN203298992U (en) | Aerodynamic performance testing device | |
| CN109506744B (en) | Air flow calibration method for venturi nozzle of aircraft engine complete machine test | |
| CN204346744U (en) | Air cleaner particle counting classification efficiency test board | |
| CN104391135A (en) | Calibration device and calibration method for micro wind speed based on laser doppler | |
| CN106248139A (en) | Atmosphere parameter measurement is popped one's head in | |
| CN106837840B (en) | It is a kind of to be used for the fan-shaped cascade experiment system that stator blade aeroperformance is studied in Non-uniform Currents | |
| CN108536922A (en) | The internal and external flow field integration method for numerical simulation of aircraft and engine | |
| CN109441878A (en) | A kind of optimization method of the aeroperformance of dust catcher centrifugal blower | |
| CN104034377B (en) | Air compressor flow measurement device and calibration system and method thereof | |
| Ma et al. | Effects of probe support on the flow field of a low-speed axial compressor | |
| CN106949957A (en) | It is a kind of to have the measurement apparatus for flowing silencer element acoustic characteristic and flow behavior under environment | |
| CN105572422B (en) | High-performance wind speed measurement system | |
| CN103353435A (en) | Air filter test board | |
| CN106126858B (en) | A kind of method of fan type selecting in power battery air cooling system | |
| CN102607658A (en) | Method for measuring gas flow in complicated structure channel based on concentration method | |
| CN106525159A (en) | Air flow measurement device | |
| CN204493246U (en) | A kind of lift fan system for air cushion ship model performance curve gauging means | |
| CN109737089A (en) | High subsonics plane cascade suction unit | |
| Wartzek et al. | Realistic inlet distortion patterns interacting with a transonic compressor stage | |
| CN109612699A (en) | A kind of PM2.5The evaluating apparatus of turbulent flow reunion device efficiency | |
| Yu et al. | Effect of the rotor cage chassis on inner flow field of a turbo air classifier | |
| CN205593570U (en) | Air flow meter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20131120 |