CN108760329A - A kind of low-pressure turbine noise fest method and its improved method - Google Patents
A kind of low-pressure turbine noise fest method and its improved method Download PDFInfo
- Publication number
- CN108760329A CN108760329A CN201810487215.9A CN201810487215A CN108760329A CN 108760329 A CN108760329 A CN 108760329A CN 201810487215 A CN201810487215 A CN 201810487215A CN 108760329 A CN108760329 A CN 108760329A
- Authority
- CN
- China
- Prior art keywords
- turbine
- noise
- low
- state
- testing
- 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.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention relates to aero-engine aeroacoustics field, more particularly to a kind of low-pressure turbine noise fest method and its improved method.The low-pressure turbine noise fest method includes S1：Input is tested the structural parameters of turbine test part；S2：Numerical simulation analysis is carried out to each operating mode sound field characteristic of turbine, and testing scheme is formulated according to sound field characteristic, then the testing scheme is optimized；S3：The error range allowed is set, determines whether to meet error requirements；S4：It chooses testing section axial position and noise transducer is installed as measuring point, and start to test；S5：Ensure that turbine test part intake air temperature is kept constant, state point is adjusted, and enroll the noise testing data of turbine；S6：The noise testing data of turbine in S5 are modified.The present invention also provides a kind of low-pressure turbine noise fest improved methods, in the above-mentioned methods, increase the step of handling turbine-exit temperature cooling, choose normal temperature type noise transducer, be effectively reduced experimentation cost.
Description
Technical field
The present invention relates to aero-engine aeroacoustics field, more particularly to a kind of low-pressure turbine noise fest method and its
Improved method.
Background technology
The big dual-use aero-engine of bypass ratio domestic at present develops progress just like a raging fire, in development process
In, the noise level of engine is an important indicator in large-bypass-ratio engine design.
In the past 50 years with the application of big bypass ratio aero-engine and the continuous increasing of civil engine bypass ratio
Greatly, the use of various noise reduction technologies, civil engine noise have been obtained for prodigious reduction so that fan and jet flow are made an uproar
The noise problem of the continuous reduction of sound, other components (such as low-pressure turbine) gradually highlights, therefore low-pressure turbine noise problem
Just become another important research direction that civilian engine noise reduction need to be paid close attention to.
It is domestic at present not yet to carry out the work of low-pressure turbine component noise correlation test, lack effective low-pressure turbine component and makes an uproar
Sound test method.Mainly there are two kinds of overall test method and component test method in foreign countries in development turbine noise experimental study, this
Two methods be respectively under engine overall test state or low-pressure turbine component test state, for low-pressure turbine inside and
External noise carries out experimental test, carries out the test analysis contents such as pipeline glottis neoplasms, far field sound pressure grade and acoustical power, realizes to low
Press quantitative detection and the test assessment of turbine noise characteristic and radiation intensity.First method, that is, overall test method has energy
The advantages of enough directly acquiring measurement data, but there is also each component noises to influence each other simultaneously, the problem of interfering, it is difficult to directly
Obtain to obtain impregnable low-pressure turbine component noise characteristic.Simultaneously because engine low-pressure turbine internal temperature is high, to making an uproar
More stringent requirements are proposed for sound test, and superelevation warm type noise transducer is expensive in addition, substantially increase noise testing at
This, the sensor that primary test generally requires millions of members expends；Second method, that is, component noise test method is in contracting ratio
Or the test of the inside and outside noise of low-pressure turbine is carried out on full-scale low-pressure turbine component, it is low there is no being measured under complete machine state
There is the interference of other component sound source in pressure turbine noise, but still exist and use a large amount of superelevation warm type noise transducer costs
Expensive problem.
Invention content
The object of the present invention is to provide a kind of low-pressure turbine noise fest method and its improved methods, to solve existing skill
At least one problem existing for art.
The technical scheme is that：
A kind of low-pressure turbine noise fest method, including：
S1：Input is tested the structural parameters of turbine test part；
S2：Numerical simulation analysis is carried out to each operating mode sound field characteristic of turbine, and testing scheme is formulated according to sound field characteristic, so
The testing scheme is optimized afterwards；
S3：The error range allowed is set, determines whether to meet error requirements, if it is not, S2 is repeated, if so, carrying out S4；
S4：Testing section axial direction position is chosen according to each section instrument and meter installation situation of testpieces and testpieces structure feature
It sets and is installed as measuring point, and start to test；
S5：Ensure that turbine test part intake air temperature is kept constant, state point is adjusted, and the noise for enrolling turbine is surveyed
Data are tried, the specific steps are：Change turbine test part by the inflow of the charge flow rate of change turbine, pressure and dynamometer
Expansion ratio and rotating speed, when the trystate of low-pressure turbine reaches state point 1, keep to change the trystate of low-pressure turbine
The state of testpieces starts the noise testing data for enrolling turbine, the state of low-pressure turbine is adjusted to shape after the completion of admission
State point 2, keeps the state of testpieces, then enrolls the noise testing data of turbine, and so on, complete the noise of all state points
Test job determines whether to test all state points and complete, if it is not, the step is repeated, if so, carrying out S6；
S6：The noise testing data of turbine in S5 are modified.
Optionally, in S1, the structural parameters include charge flow rate, intake air temperature, expansion ratio, rotating speed, turn stator leaf
The piece number and distribution, testpieces flow path dimensions.
Optionally, in S2, it includes determining measuring point number and measuring point distribution form to formulate the testing scheme.
Optionally, in S5, the noise testing data of the turbine include aeroperformance and acoustic characteristic.
Optionally, in S6, specially：Consider Aerodynamic conversion and amendment, according to turbo operating state with
The acoustics amendment carried out needed for the difference of practical turbine part working condition.
Optionally, the correcting mode is according to following principle：
A, geometric similarity, i.e. corresponding points pantograph ratio are equal；
B, kinematic similitude, i.e. corresponding points speed triangle are similar；
C, dynamic similarity, i.e., corresponding points Mach number is equal, Strouhal number is equal；
In the areas Reynolds number Dou Zimo when d, testing；
E, the turbine interior noise amplitude for the constant situation of inlet temperature and frequency characteristic amendment.
A kind of low-pressure turbine noise fest improved method, including：
S1：Input is tested the structural parameters of turbine test part；
S2：Numerical simulation analysis is carried out to each operating mode sound field characteristic of turbine, and testing scheme is formulated according to sound field characteristic, so
The testing scheme is optimized afterwards；
S3：The error range allowed is set, determines whether to meet error requirements, if it is not, S2 is repeated, if so, carrying out S4；
S4：Testing section axial direction position is chosen according to each section instrument and meter installation situation of testpieces and testpieces structure feature
It sets and noise transducer is installed as measuring point, and start to test；
S5：Ensure that turbine test part intake air temperature is kept constant, state point is adjusted, turbine-exit temperature is carried out
Whether monitoring, judgement turbine-exit temperature transfinite, if so, carrying out cooling processing to turbine-exit temperature and coming back to S5's
Initial step, if it is not, the noise testing data of turbine are then enrolled, the specific steps are：By the charge flow rate, the pressure that change turbine
The expansion ratio and rotating speed for changing turbine test part with the inflow of dynamometer work as low pressure to change the trystate of low-pressure turbine
When the trystate of turbine reaches state point 1, the state of testpieces is kept, turbine-exit temperature is monitored, judges turbine
Whether outlet temperature transfinites, if so, carrying out cooling processing to turbine-exit temperature and coming back to the step of adjusting trystate
Suddenly, if it is not, then starting the noise testing data of admission turbine, the state of low-pressure turbine is adjusted to state point after the completion of admission
2, the state of testpieces is kept, turbine-exit temperature is monitored, whether judgement turbine-exit temperature transfinites, if so, right
Turbine-exit temperature carries out cooling processing and comes back to the step of adjusting trystate, if it is not, the noise for enrolling turbine again is surveyed
Data are tried, and so on, the noise testing work of all state points is completed, determines whether to test all state points and complete, if
It is no, the step is repeated, if so, carrying out S6；
S6：The noise testing data of turbine in S5 are modified.
Invention effect：
The present invention low-pressure turbine noise fest method and its improved method, provide one kind can contracting than or it is full-scale
The test method of noise fest is carried out on low-pressure turbine testpieces；Its improved method carries out low-pressure turbine noise fest method excellent
Change, high-temperature severe environment during turbine noise experiment is substantially improved under the premise of ensureing measuring accuracy, is passed using normal temperature type
Sensor completes test, greatly reduces cost.
Description of the drawings
Fig. 1 is turbine noise experiment shafting schematic diagram；
Fig. 2 is turbine noise testing section axial position schematic diagram；
Fig. 3 turbine noise testing section circumferential position schematic diagrames；
Fig. 4 turbine noises test process schematic；
Fig. 5 is the low-pressure turbine noise fest method flow diagram of the present invention；
Fig. 6 is the low-pressure turbine noise fest improved method flow chart of the present invention.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
The every other embodiment that member is obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term "center", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, and does not indicate or imply the indicated dress
It sets or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as protecting the present invention
The limitation of range.
1 to 6 pair of of the invention a kind of low-pressure turbine noise fest method and its improved method are done into one below in conjunction with the accompanying drawings
Step is described in detail.
The present invention provides a kind of low-pressure turbine noise fest method and its improved methods.
Specifically, low-pressure turbine noise fest carries out on the basis of being built upon conventional low voltage turbulence stimulation state performance test
, the intake air temperature of low-pressure turbine testpieces and outlet pressure are relatively-stationary at this time, and the state change of testpieces is to pass through
Change the charge flow rate of low-pressure turbine, pressure and adjusts the load (namely dynamometer) of testpieces come what is realized, conventional low voltage
Turbine performance experiment shaft system arrangement as shown in Figure 1, including dynamometer 1, gear-box 2, button axis 3, testpieces 4, exhaust pipe 5 and
Spiral case 6；Dynamometer 1 is connect by coupling spindle 7 with gear-box 2, and gear-box 2 is connected by button axis 3 with testpieces 4, and testpieces 4 connects
Run in tracheae 5；Wherein, dynamometer 1 is wasted work equipment, and gear-box 2 is gear shift device, and torsion axis 3 is power-measuring device.High temperature is high
Body of calming the anger enters low-pressure turbine, and turbine is driven to do work, and high temperature and high pressure gas becomes low-temperature atmosphere-pressure gas and be discharged into disappear after acting
Sound tower, while turbine output is transferred to gear-box 2 and dynamometer 1 by shafting, consuming low-pressure turbine by dynamometer 1 sends out
Power.By the adjusting to charge flow rate, pressure, expansion ratio and rotating speed etc., after control low-pressure turbine runs to trystate,
Noise testing can be completed.
It is illustrated below for low-pressure turbine noise fest test process, simulation state noise fest test is relative to routine
Difference lies in the contents for increasing noise testing for the simulation state experiment of low-pressure turbine, that is, it needs to be determined that noise testing is cut
Face and test mode.
The present invention low-pressure turbine noise fest method, by low-pressure turbine exit arrange noise transducer scheme come
Noise fest is carried out, is specifically included：
S1：Input is tested the structural parameters of turbine test part, structural parameters include charge flow rate, intake air temperature, expansion ratio,
Rotating speed turns stator blade number and distribution, testpieces flow path dimensions etc.；
S2：Numerical simulation analysis is carried out to each operating mode sound field characteristic of turbine, and testing scheme is formulated according to sound field characteristic, so
The testing scheme is optimized afterwards, it includes determining measuring point number and measuring point distribution form to formulate testing scheme；
S3：The error range allowed is set, determines whether to meet error requirements, if it is not, S2 is repeated, if so, carrying out S4；
S4：Testing section axial direction position is chosen according to each section instrument and meter installation situation of testpieces and testpieces structure feature
(specific location is as shown in Figure 2,3, wherein 8 be noise testing section, and 9 be noise transducer) is set to pass as measuring point installation noise
Sensor, and start to test；Wherein, when carrying out noise transducer installation, a kind of particular sensor installation form, a side should be used
Face ensures that sensor is not influencing in runner that under gas flow characteristic and acoustic propagation characteristic, accurately and effectively noise number can be obtained
According to, on the other hand also ensure noise transducer will not fall off because of the effect of air pressure or suction passage in；
S5：Ensure that turbine test part intake air temperature keeps constant that (it refers to temperature in a smaller model that temperature, which is kept constant,
Enclose interior floating), state point is adjusted, and enroll the noise testing data of turbine (including aeroperformance and acoustics are special
Property), the specific steps are：Change the swollen of turbine test part by the inflow of the charge flow rate of change turbine, pressure and dynamometer
Swollen ratio and rotating speed, when the trystate of low-pressure turbine reaches state point 1, keep examination to change the trystate of low-pressure turbine
The state for testing part starts the noise testing data for enrolling turbine, the state of low-pressure turbine is adjusted to state after the completion of admission
Point 2, keeps the state of testpieces, then enroll the noise testing data of turbine, and so on, the noise for completing all state points is surveyed
(as shown in Figure 4) is made in trial work, determines whether to test all state points and complete, if it is not, the step is repeated, if so, carrying out S6；
S6：The noise testing data of turbine in S5 are modified, specially：On the one hand it needs to consider Aerodynamic
Conversion and amendment, while more importantly being carried out needed for the difference because of turbo operating state with practical turbine part working condition
Acoustics amendment.It mainly should be according to following similarity criterion：A, geometric similarity, i.e. corresponding points pantograph ratio are equal；B, phase is moved
Seemingly, i.e. corresponding points speed triangle is similar；C, dynamic similarity, i.e., corresponding points Mach number is equal, Strouhal number is equal；D, it tries
In the areas Reynolds number Dou Zimo when testing；E, it is repaiied for the turbine interior noise amplitude and frequency characteristic of the constant situation of inlet temperature
Just.
The development of low-pressure turbine simulation state experiment is built upon on similarity, and low-pressure turbine simulates state noise
Testing experiment carries out on the basis of low-pressure turbine performance test, and the experiment of low-pressure turbine noise mode mimicry is also required to establish phase
" principle of similitude " answered is tested to instruct low-pressure turbine to simulate state noise testing.Simultaneously as simulation state low-pressure turbine testpieces
The temperature change of outlet is larger, substantially changes to several Baidu at tens degree, and noise transducer heatproof degree is higher at present, passes
Sensor cost has also just accordingly increased a large amount of experimentation cost also with regard to double increase, and economy is poor.
In order to reduce experimentation cost, based on the above method, the present invention also provides a kind of examinations of low-pressure turbine noise
Improved method is tested, this method includes：
S1：Input is tested the structural parameters of turbine test part；
S2：Numerical simulation analysis is carried out to each operating mode sound field characteristic of turbine, and testing scheme is formulated according to sound field characteristic, so
The testing scheme is optimized afterwards；
S3：The error range allowed is set, determines whether to meet error requirements, if it is not, S2 is repeated, if so, carrying out S4；
S4：Testing section axial direction position is chosen according to each section instrument and meter installation situation of testpieces and testpieces structure feature
It sets and noise transducer is installed as measuring point, and start to test；
S5：Ensure that turbine test part intake air temperature is kept constant, state point is adjusted, turbine-exit temperature is carried out
Whether monitoring, judgement turbine-exit temperature transfinite, if so, carrying out cooling processing to turbine-exit temperature and coming back to S5's
Initial step, if it is not, the noise testing data of turbine are then enrolled, the specific steps are：By the charge flow rate, the pressure that change turbine
The expansion ratio and rotating speed for changing turbine test part with the inflow of dynamometer work as low pressure to change the trystate of low-pressure turbine
When the trystate of turbine reaches state point 1, the state of testpieces is kept, turbine-exit temperature is monitored, judges turbine
Whether outlet temperature transfinites, if so, carrying out cooling processing to turbine-exit temperature and coming back to the step of adjusting trystate
Suddenly, if it is not, then starting the noise testing data of admission turbine, the state of low-pressure turbine is adjusted to state point after the completion of admission
2, the state of testpieces is kept, turbine-exit temperature is monitored, whether judgement turbine-exit temperature transfinites, if so, right
Turbine-exit temperature carries out cooling processing and comes back to the step of adjusting trystate, if it is not, the noise for enrolling turbine again is surveyed
Data are tried, and so on, the noise testing work of all state points is completed, determines whether to test all state points and complete, if
It is no, the step is repeated, if so, carrying out S6；
S6：The noise testing data of turbine in S5 are modified.
Advantageously, in the improved test method, temperature (the namely noise transducer of low-pressure turbine exit is controlled
Use environment temperature), while choosing normal temperature type noise transducer, experimentation cost can be effectively reduced.
In low-pressure turbine component noise tests improved method, it can pacify in order to enable outlet temperature is maintained at noise transducer
It within the temperature range of entirely using, needs during turbine test, adjusts the temperature and flow of turbine inlet air-flow repeatedly, thus
Cause, in carrying out experimental test data handling procedure, on the one hand needs the conversion and amendment that consider Aerodynamic, simultaneously
Should include more importantly the sound because being carried out needed for the difference of turbine out temperature and practical turbine part out temperature
It learns and corrects.
It is illustrated by taking certain type low-pressure turbine noise fest demonstration process as an example, which exists
Change in 100 DEG C~150 DEG C, if the noise transducer that selection temperature resistant range is larger, every sensor need about 50,000,
If by Control experiment process, ensure that turbine-exit temperature is maintained at 80 DEG C hereinafter, can so select the noise of normal temperature type
Sensor, for every sensor cost at 10,000 yuan, the demand according to routine test part noise testing sensor is 75 calculating,
Only sensor one can about 3,000,000 yuan of reduction of expenditure, economy is good.
Experiment process is described with the normal temperature type noise transducer that resistance to temperature value is -30 DEG C~80 DEG C.Turbine test generally uses
The compressed air that air compressor machine generates is as incoming air source, and incoming-flow pressure is generally less than 1MPa, and temperature is generally at 130 DEG C~150 DEG C
Interior variation can be changed using temperature after cooling measure in 30 DEG C~150 DEG C.
Before testpieces starts air inlet, temperature of incoming flow is adjusted to 50 DEG C, testpieces starts air inlet at this time, and testpieces turns at this time
Speed and expansion ratio are smaller, and the temperature difference of testpieces inlet and outlet is little, is consistent substantially, at this time the fortune of monitoring test part and equipment
Row state improves the air inflow of testpieces, the trystate point of testpieces if the operating parameter of testpieces and equipment is normal
The envelope of dynamometer is initially entered, at this time since the state of testpieces improves, the outlet temperature of testpieces can decline, will try
It tests state point to improve to state point 1, at 30 DEG C, noise transducer can work turbine test part outlet temperature, at this time may be used at this time
To enroll the noise data of state point 1, after the data recording of completion status point 1, if continuing raising state to state point 2, meeting
Cause testpieces outlet temperature too low, formed moisture condensation frosting, influence the accuracy of test result, at this time adjust turbine test part into
Mouth temperature, is promoted to 90 DEG C, and testpieces is kept to stablize in state point 1, and testpieces outlet temperature can be increased to 70 at this time
DEG C or so, it is not above the limits value of sensor, after completing inlet temperature adjustment, testpieces state is promoted to state point 2, is tried
It tests part outlet temperature and maintains 30 DEG C or so, enroll the noise testing data of testpieces state point 2, and so on, it completes to shape
The noise testing of state point 3 works.After the completion of the test job of all state points, testpieces needs the path promoted according to state
It is reversed to reduce testpieces state, ensure that noise transducer does not damage.
In conclusion the low-pressure turbine noise fest method and its improved method of the present invention, pneumatic in low-pressure turbine component
On the basis of performance test, for the uniqueness of noise fest, and the demand that considers economy and usability is proposed, is
Can contracting ratio or full-scale low-pressure turbine testpieces on progress noise fest test method；Based on low-pressure turbine aeroperformance
Simulation state test method optimize low-pressure turbine noise fest in conjunction with the Acoustic Similarity principle of turbomachine aerodynamic noise
Method and flow, in addition, the low-pressure turbine noise fest improved method substantially improves turbine under the premise of ensureing measuring accuracy
High-temperature severe environment during noise fest is completed to test, greatly reduces cost using normal temperature type sensor.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all answer by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of the claims
It is accurate.
Claims (7)
1. a kind of low-pressure turbine noise fest method, which is characterized in that including：
S1：Input is tested the structural parameters of turbine test part；
S2：Numerical simulation analysis is carried out to each operating mode sound field characteristic of turbine, and testing scheme is formulated according to sound field characteristic, it is then right
The testing scheme optimizes；
S3：The error range allowed is set, determines whether to meet error requirements, if it is not, S2 is repeated, if so, carrying out S4；
S4：Testing section axial position is chosen according to each section instrument and meter installation situation of testpieces and testpieces structure feature to make
Noise transducer is installed for measuring point, and starts to test；
S5：Ensure that turbine test part intake air temperature is kept constant, state point is adjusted, and enroll the noise testing number of turbine
According to, the specific steps are：Change the expansion of turbine test part by the inflow of the charge flow rate of change turbine, pressure and dynamometer
Than and rotating speed, to change the trystate of low-pressure turbine, when the trystate of low-pressure turbine reaches state point 1, keep experiment
The state of part starts the noise testing data for enrolling turbine, the state of low-pressure turbine is adjusted to state point after the completion of admission
2, the state of testpieces is kept, then enroll the noise testing data of turbine, and so on, complete the noise testing of all state points
Work determines whether to test all state points and complete, if it is not, the step is repeated, if so, carrying out S6；
S6：The noise testing data of turbine in S5 are modified.
2. low-pressure turbine noise fest method according to claim 1, which is characterized in that in S1, the structural parameters
Including charge flow rate, intake air temperature, expansion ratio, rotating speed, turn stator blade number and distribution, testpieces flow path dimensions.
3. low-pressure turbine noise fest method according to claim 1, which is characterized in that in S2, formulate the test
Scheme includes determining measuring point number and measuring point distribution form.
4. low-pressure turbine noise fest method according to claim 1, which is characterized in that in S5, the turbine is made an uproar
Sound test data include aeroperformance and acoustic characteristic.
5. low-pressure turbine noise fest method according to claim 4, which is characterized in that in S6, specially：Consider gas
The conversion and amendment of dynamic performance parameter, according to what is carried out needed for the difference of turbo operating state and practical turbine part working condition
Acoustics amendment.
6. low-pressure turbine noise fest method according to claim 5, which is characterized in that the correcting mode is according to following
Principle：
A, geometric similarity, i.e. corresponding points pantograph ratio are equal；
B, kinematic similitude, i.e. corresponding points speed triangle are similar；
C, dynamic similarity, i.e., corresponding points Mach number is equal, Strouhal number is equal；
In the areas Reynolds number Dou Zimo when d, testing；
E, the turbine interior noise amplitude for the constant situation of inlet temperature and frequency characteristic amendment.
7. a kind of low-pressure turbine noise fest improved method, which is characterized in that including：
S1：Input is tested the structural parameters of turbine test part；
S2：Numerical simulation analysis is carried out to each operating mode sound field characteristic of turbine, and testing scheme is formulated according to sound field characteristic, it is then right
The testing scheme optimizes；
S3：The error range allowed is set, determines whether to meet error requirements, if it is not, S2 is repeated, if so, carrying out S4；
S4：Testing section axial position is chosen according to each section instrument and meter installation situation of testpieces and testpieces structure feature to make
Noise transducer is installed for measuring point, and starts to test；
S5：Ensure that turbine test part intake air temperature is kept constant, state point is adjusted, turbine-exit temperature is supervised
Whether control, judgement turbine-exit temperature transfinite, if so, carrying out cooling processing to turbine-exit temperature and coming back to the first of S5
Beginning step, if it is not, the noise testing data of turbine are then enrolled, the specific steps are：By change the charge flow rate of turbine, pressure and
The inflow of dynamometer changes the expansion ratio and rotating speed of turbine test part, to change the trystate of low-pressure turbine, when low pressure whirlpool
When the trystate of wheel reaches state point 1, the state of testpieces is kept, turbine-exit temperature is monitored, judgement turbine goes out
Whether mouth temperature transfinites, if so, cooling processing is carried out to turbine-exit temperature and comes back to the step of adjusting trystate,
If it is not, then starting the noise testing data of admission turbine, the state of low-pressure turbine is adjusted to state point 2 after the completion of admission,
The state for keeping testpieces, is monitored turbine-exit temperature, and whether judgement turbine-exit temperature transfinites, if so, to whirlpool
Wheel outlet temperature carries out cooling processing and comes back to the step of adjusting trystate, if it is not, enrolling the noise testing of turbine again
Data, and so on, the noise testing work of all state points is completed, determines whether to test all state points and complete, if it is not,
The step is repeated, if so, carrying out S6；
S6：The noise testing data of turbine in S5 are modified.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810487215.9A CN108760329B (en) | 2018-05-21 | 2018-05-21 | Low-pressure turbine noise test method and improvement method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810487215.9A CN108760329B (en) | 2018-05-21 | 2018-05-21 | Low-pressure turbine noise test method and improvement method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108760329A true CN108760329A (en) | 2018-11-06 |
| CN108760329B CN108760329B (en) | 2020-02-07 |
Family
ID=64008558
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810487215.9A Active CN108760329B (en) | 2018-05-21 | 2018-05-21 | Low-pressure turbine noise test method and improvement method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108760329B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112857815A (en) * | 2019-11-28 | 2021-05-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for testing internal noise of aircraft engine compressor |
| CN112924180A (en) * | 2021-01-15 | 2021-06-08 | 南京航空航天大学 | Jet flow noise active control test platform based on engine spray pipe scaling model |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2924509Y (en) * | 2006-05-26 | 2007-07-18 | 广西玉柴机器股份有限公司 | Engine test bench for anechoic chamber |
| KR20090041146A (en) * | 2007-10-23 | 2009-04-28 | 현대자동차주식회사 | Turbo charger tester |
| CN102937478A (en) * | 2012-11-13 | 2013-02-20 | 奥凯嘉集团有限公司 | System for measuring booster noise |
| CN103148927A (en) * | 2013-02-21 | 2013-06-12 | 奇瑞汽车股份有限公司 | Noise measuring system for engine accessory system in hemi-anechoic room |
| CN103392122A (en) * | 2011-02-24 | 2013-11-13 | Avl里斯脱有限公司 | Method for functionally testing turbomachines, and test device therefor |
| CN105277370A (en) * | 2015-11-25 | 2016-01-27 | 山东大学 | Engine exhaust noise off-line simulation test table and test method |
| CN107796630A (en) * | 2016-09-05 | 2018-03-13 | 赛峰航空助推器股份有限公司 | Turbine testboard with Active noise control |
-
2018
- 2018-05-21 CN CN201810487215.9A patent/CN108760329B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2924509Y (en) * | 2006-05-26 | 2007-07-18 | 广西玉柴机器股份有限公司 | Engine test bench for anechoic chamber |
| KR20090041146A (en) * | 2007-10-23 | 2009-04-28 | 현대자동차주식회사 | Turbo charger tester |
| CN103392122A (en) * | 2011-02-24 | 2013-11-13 | Avl里斯脱有限公司 | Method for functionally testing turbomachines, and test device therefor |
| CN102937478A (en) * | 2012-11-13 | 2013-02-20 | 奥凯嘉集团有限公司 | System for measuring booster noise |
| CN103148927A (en) * | 2013-02-21 | 2013-06-12 | 奇瑞汽车股份有限公司 | Noise measuring system for engine accessory system in hemi-anechoic room |
| CN105277370A (en) * | 2015-11-25 | 2016-01-27 | 山东大学 | Engine exhaust noise off-line simulation test table and test method |
| CN107796630A (en) * | 2016-09-05 | 2018-03-13 | 赛峰航空助推器股份有限公司 | Turbine testboard with Active noise control |
Non-Patent Citations (1)
| Title |
|---|
| 周禹彬等: "某型高压涡轮级性能试验研究", 《燃气涡轮试验与研究》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112857815A (en) * | 2019-11-28 | 2021-05-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for testing internal noise of aircraft engine compressor |
| CN112857815B (en) * | 2019-11-28 | 2022-09-02 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for testing internal noise of aircraft engine compressor |
| CN112924180A (en) * | 2021-01-15 | 2021-06-08 | 南京航空航天大学 | Jet flow noise active control test platform based on engine spray pipe scaling model |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108760329B (en) | 2020-02-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111044252B (en) | High-precision air inlet channel flow measuring method | |
| Bozza et al. | 1D simulation and experimental analysis of a turbocharger compressor for automotive engines under unsteady flow conditions | |
| CN102829976B (en) | Simulator stand for exhaust characteristics of vehicle engine | |
| CN112067304B (en) | Method for measuring inlet flow of compressor in engine whole machine test | |
| Marelli et al. | Effect of pulsating flow characteristics on performance and surge limit of automotive turbocharger compressors | |
| Capobianco et al. | Experimental analysis of unsteady flow performance in an automotive turbocharger turbine fitted with a waste-gate valve | |
| AU7828101A (en) | System and method for direct non-intrusive measurement of corrected airflow | |
| CN110671219B (en) | Method and system for controlling air-fuel ratio of gas engine | |
| CN107977526B (en) | Big bypass ratio Civil Aviation Engine performance diagnogtics method and system | |
| CN105424105B (en) | Dust pelletizing system is responsible for air volume detecting method and on-line measuring device | |
| CN108760329A (en) | A kind of low-pressure turbine noise fest method and its improved method | |
| Came | The development, application and experimental evaluation of a design procedure for centrifugal compressors | |
| CN109186972A (en) | One kind is for the exploitation of air inlet system and exhaust system acoustical behavior and verifying testboard bay | |
| CN106499651A (en) | A kind of centrifugal compressor Non-steady characteristics platform and test method | |
| Tiikoja et al. | Investigations of automotive turbocharger acoustics | |
| CN103742277A (en) | Engine friction torque computing method and device | |
| Liu et al. | Parametric modelling of vibration response for high-speed gear transmission system | |
| CN106092538A (en) | A kind of for axial rotation hole discharge coefficient measure device and do not rotate method | |
| CN113361040A (en) | Method for evaluating outlet temperature of combustion chamber under engine complete machine condition | |
| CN116104791A (en) | Test bed and test method for influence of axial flow compressor blade tip clearance flow on stall | |
| CN203743033U (en) | Nuclear reactor top draught fan performance testing device | |
| CN114383850B (en) | Open test bed thrust correction method under natural wind condition | |
| CN104596757B (en) | Variable geometry turbine supercharger nozzle ring flow calibration method and experimental rig | |
| Bright et al. | Closed Loop Active Flow Seperation Detection and Control in a Multistage Compressor | |
| Vrettakos | Impact of compressor surge on performance and emissions of a marine diesel engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |