CN108036917A - A kind of ram-air turbine wind tunnel test test method - Google Patents

A kind of ram-air turbine wind tunnel test test method Download PDF

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CN108036917A
CN108036917A CN201711348629.5A CN201711348629A CN108036917A CN 108036917 A CN108036917 A CN 108036917A CN 201711348629 A CN201711348629 A CN 201711348629A CN 108036917 A CN108036917 A CN 108036917A
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turbine
speed
face
mrow
wind
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CN108036917B (en
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郭生荣
卢岳良
刘诚
姬芬竹
王岩
寇桂岳
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Beihang University
Jincheng Nanjing Electromechanical Hydraulic Pressure Engineering Research Center Aviation Industry Corp of China
AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems
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AVIC Jincheng Nanjing Engineering Institute of Aircraft Systems
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
    • G01M9/04—Details
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
    • G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/08—Aerodynamic models

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  • General Physics & Mathematics (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The present invention provides a kind of ram-air turbine wind tunnel test test method, and step is as follows：1：Ram-air turbine model is installed in test chamber；2：Determine the in-let dimple face of model in test chamber；3：Determine the control of export face of model in test chamber；4：Determine the streamline bending chain of command of model in test chamber；5：Determine the control volume of model in test chamber；6：Determine test chamber entrance measurement point and exit measurement point；7：Each measurement point is passed through into connecting line and measuring instrument reliable connected respectively；8：Turbine output when testing initial wind speed under difference propeller pitch angle, calculate and obtain turbine efficiency；9：Test turbine output and turbine efficiency under initial propeller pitch angle during different wind speed；10：Turbine output and turbine efficiency under difference propeller pitch angle when testing different wind speed；The present invention realizes outfield flowing internal fieldization processing, improves the ability using wind- tunnel investigation ram-air turbine power performance.

Description

A kind of ram-air turbine wind tunnel test test method
Technical field
The present invention provides a kind of ram-air turbine wind tunnel test test method, and in particular to one kind is based on compressible fluid The ram-air turbine outfield flowing internal fieldization processing wind tunnel test test method of far field open loop system, belongs to ram-air turbine Wind-tunnel technique field.
Background technology
Ram Air Turbine Systems are the emergency power units of modern aircraft, it can lose active force and auxiliary in aircraft The in emergency circumstances offer Emergency power source of power, ensures flight safety.Wherein, turbine rotates and gas under windstream effect Stream punching press can be converted to mechanical energy, be the Energy extraction component of system.Therefore, the output power of ram-air turbine and energy carry Take the core that efficiency is system research, and the key index of turbine pneumatic performance.Ram-air turbine aeroperformance research side Method mainly includes theoretical research, numerical simulation and experimental study etc..At present, experimental study mainly uses wind tunnel test, and seldom Tested as conventional wind machine turbine using live (outfield), main cause is that live (outfield) experiment is needed in natural work Under the conditions of carry out, but the natural operating condition of ram-air turbine can only be on-hook flight, i.e. Flight.Tested however, taking a flight test It is highly difficult big to demonstrate,prove process risk, and the domestic Flight method there has been no maturation at present.Therefore, in order to reduce Flight Risk and technical difficulty, usually first carry out ground wind-tunnel verification experimental verification, then carry out Flight again.
At present, the main process of ram-air turbine ground wind tunnel test methods is：Ram-air turbine is reliably pacified Loaded in test air tunnel；Start wind-tunnel and wind tunnel speed is reached setting；Ram-air turbine acts on backspin in windstream Turn and energy is extracted from tunnel airstream；Ram-air turbine rotating speed and output torque are measured in real time using wind tunnel test system, Turbine output rate is can be calculated, and is ultimately converted to hydraulic energy or electrical energy drive loaded work piece；Monitor gas in wind-tunnel at the same time The signal such as pressure, temperature and fluid velocity.However, the ground wind tunnel test methods are able to validate only ram-air turbine from gas The energy obtained is flowed, turbine efficiency can not be obtained, which refers to energy efficiency, i.e. power coefficient.In order into one Step demonstrate,proves ram-air turbine efficiency, it usually needs wind tunnel test is carried out to turbo blade aeroperformance, to verify vane airfoil profile Power coefficient.
At present, pneumatic equipment bladess wind tunnel test survey is mainly used for reference in the wind tunnel test of ram-air turbine vane airfoil profile aeroperformance Amount method, i.e., the liter resistance coefficient measuring method based on momentum theory (refer to the volume such as Wang Tiecheng《Aerodynamics experimental technique》, state It is anti-industry publishing house, in April, 1986 Section 6.5 of the 6th chapter of the first edition).This method is based on momentum theory, and it is close to measure air respectively Wall hydrostatic pressure above and below degree, speed of incoming flow and wind-tunnel corresponding with model, wall pressure is calculated according to following formula (1)；So Wall pressure is integrated and then tries to achieve the lift coefficient of model leaf according to following formula (2) afterwards；Further, measurement comes respectively Flow flowing stagnation pressure and static pressure that tail at a certain distance from stagnation pressure and static pressure, model trailing edge is flowed in direction wind-tunnel inlet, Ran Houyi The resistance coefficient of model leaf is tried to achieve along path wl integrations according to formula (3).Formula (1)~(3) are described as follows：
In formula, p is the hydrostatic pressure obtained by wind-tunnel wall measurement；ρ is atmospheric density；V∞Carry out flow velocity for wind-tunnel entrance Degree；Cl、CrAnd CpThe respectively lift coefficient of turbo blade, resistance coefficient and surface pressure coefficient；CpuAnd CplRepresent respectively by The surface pressure coefficient that the upper and lower wall measurement parameter of wind-tunnel is tried to achieve；C is the chord length of model leaf；p0、p∞And p01、p1Respectively Wake stagnation pressure, static pressure at a certain distance from expression incoming stagnation pressure, static pressure and airfoil trailing edge；X, y is respectively fluid in wind-tunnel Flow direction and normal direction coordinate；Range of integration x1And x2The respectively x of the upper and lower wall static pressure measuring point of wind-tunnel is to coordinate range；Wl is represented Path of integration along normal direction in flowing tail area.
However, in place of the test method also Shortcomings, the following aspects is mainly manifested in：(1) the upper and lower wall of wind-tunnel Point position determines to have a great influence to measurement result, it is necessary to is empirically corrected；(2) do not account at model trailing edge tail The tangential component of air velocity.
For above-mentioned deficiency, Jiao Yu Qin of Northwestern Polytechnical University etc. discloses a kind of wind tunnel test side based on momentum theorem Method (refers to a kind of wind tunnel test methods [P] application numbers based on momentum theorem of the such as the Jiao Yu Qin, Wang Long, Gao Yongwei 201210251010.3).This method increases by two measurement chains of command before and after aerofoil profile model, makes measurement chain of command and wind tunnel wall Complete fixed control volume is formed, the fluid parameter on two chains of command is measured respectively, then according to momentum theory and the moment of momentum Principle computation model aeroperformance.Increased control volume is to fix control volume in the test method, and the pressure measurement on wind tunnel wall Point is distributed on experiment upper wall and the center line for testing lower wall, and spacing is between the pressure tap which crosses in aerofoil profile mold segment The 3%~8% of aerofoil profile model chord length, and the center line for testing upper wall and experiment lower wall is crossing aerofoil profile mold segment with the survey of exterior domain Pressure point spacing is the 8%~13% of aerofoil profile model chord length.The test method is mainly characterized by improving wind tunnel test measurement essence Degree, while also achieve the measurement of model Moment and carry out the experiment of momentum method three dimensional wind tunnel.However, the test method is increased Control volume beFixed control volume, the foundation for determining the forward and backward chain of command of control volume is used as using the percentage of aerofoil profile model chord length.I Know, when wind-tunnel speed of incoming flow changes, flowing gas state changes in wind-tunnel, model entrance control in test chamber Face and control of export face processed change therewith, therefore control volume should be also varied from, and to reduce disturbing influence, improve measurement accuracy.
The content of the invention
(1) purpose of the present invention
The object of the present invention is to provide a kind of ram-air turbine wind tunnel test test method, its technical problems to be solved It is to provide a kind of ram-air turbine outfield flowing internal fieldization processing wind tunnel test based on compressible fluid far field open loop system Test method, it can overcome impenetrably face wind tunnel test existing in the prior art obtain ram-air turbine efficiency, Empirically lift coefficient and resistance coefficient result of calculation must be modified during turbo blade Airfoil Testing, not account for mould A kind of the deficiencies of air velocity influences at type trailing edge tail, it is proposed that ram-air based on compressible fluid far field open loop system Turbine wind tunnel test test method, realizes the internal fieldization processing of outer field parameters, is established for ram-air turbine Dynamic Behavior Basis is determined.
(2) technical solution
Technical solution and specific implementation process according to the present invention are：
Technical solution of the present invention is a kind of ram-air turbine wind-tunnel based on compressible fluid far field open loop system Testing method.This method is related to model chain of command, control volume, test procedure and data processing etc. in test chamber.
Model chain of command is that gas streamline does not bend in test air tunnel in the test chamber, i.e., without tangential speed Spend the chain of command of component.Chain of command is bent including in-let dimple face, control of export face and streamline.It is characterized in that：The entrance Chain of command is located at direction of flow and 1/2 turbine diameter of turbine Plane of rotation spacing and perpendicular to turbine rotation centerline；It is described Control of export face does not bend for turbine trailing edge streamline, i.e., fluid does not have tangential speed component and perpendicular to turbine pivot The critical surface of line；The streamline bending chain of command includes preceding to streamline bending chain of command and backward streamline bending chain of command；Specifically Ground：Each critical control point that streamline does not bend in sub-scale model turbine Plane of rotation along the circumferential direction forms Critical Control line, preceding To streamline bending chain of command be on the basis of the Critical Control line intend airflow direction parallel to turbine rotation centerline be moved to In-let dimple face is intersected, the cylindricality chain of command formed in gained intersection and turbine Plane of rotation between Critical Control line；Backward current Line bending chain of command is the downstream direction Critical Control that respectively streamline does not bend in turbine rotation centerline plane The chain of command that line is formed, the chain of command intersect with control of export face.
Model control volume is that the in-let dimple face, the control of export face and the streamline are curved in the test chamber The control volume that bent chain of command is formed, the streamline bending chain of command include preceding to streamline bending chain of command and the bending control of backward streamline Face processed.
A kind of ram-air turbine wind tunnel test test method of the present invention, its step are as follows：
Step 1：Ram-air turbine model is reliably mounted in test chamber；
Step 2：Determine the in-let dimple face of model in test chamber；The in-let dimple face be using turbine Plane of rotation as Benchmark, to 1/2 turbine diameter of direction of flow at and perpendicular to the section of turbine rotation centerline；
Step 3：Determine the control of export face of model in test chamber；Specific method is to utilize seven-hole probe after turbine The Critical Control face that does not bend of edge detection streamline, the Critical Control face is perpendicular to turbine rotation centerline, and fluid is cut It is zero to velocity component；
Step 4：Determine model in test chamber streamline bending chain of command, including it is preceding to streamline bending chain of command and after Chain of command is bent to streamline；Specific method is not bent using streamline in seven-hole probe detection model turbine Plane of rotation, The critical control point of tangential speed component is not present, each critical control point forms Critical Control line in the circumferential direction；Forward direction Streamline bending chain of command is to intend airflow direction on the basis of the Critical Control line to be moved to and enter parallel to turbine rotation centerline Mouth chain of command intersects, the cylindricality chain of command formed in gained intersection and turbine Plane of rotation between Critical Control line；Backward streamline Bending chain of command is the downstream direction Critical Control line that respectively streamline does not bend in turbine rotation centerline plane The chain of command of composition, the chain of command intersect with control of export face；
Step 5：Determine the control volume of model in test chamber；The control volume is respectively by in-let dimple face, control of export Face and streamline bending chain of command composition, streamline bending chain of command bend chain of command and the bending control of backward streamline including preceding to streamline Face processed；
Step 6：Determine test chamber entrance measurement point and exit measurement point；The test chamber entrance measurement point and Exit measurement point is located at the in-let dimple face and control of export face of the wind tunnel test segment model respectively；The entrance measurement point and go out Mouthful measurement point along the circumferential direction equidistantly distributed；
Step 7：Each measurement point is passed through into connecting line and measuring instrument reliable connected respectively；
Step 8：Turbine output when testing initial wind speed under difference propeller pitch angle, calculate and obtain turbine efficiency, specifically Measurement process is：
A., the initial wind speed of wind-tunnel and initial propeller pitch angle are set；The initial wind speed of wind-tunnel is determined according to experiment Reynolds number, if For V1；It is initial value according to test requirements document adjustment turbine propeller pitch angle
B. the initial wind speed V that wind-tunnel reaches test requirements document is started1；Tested by measuring instrument under the initial wind speed just The static pressure of each measurement point, static temperature and fluid velocity during beginning propeller pitch angle, while measure secondary speed and torque；Wherein, in-let dimple Radial direction directional pressure and velocity-stabilization in face, and radial direction directional pressure and speed are unstable in control of export face；In-let dimple face Interior radial direction spot measurement, and radial direction continuously measures in control of export face, which also includes multimetering；
C. data processing：
According to each measuring point measurement result, during by following equation to initial wind speed under initial propeller pitch angle each measuring point test number According to being handled, can be calculated during initial wind speed turbine theory output work and turbine efficiency under initial propeller pitch angle, it is specific calculate it is public Formula is：
The equivalent stagnation pressure in model control volume in-let dimple face is in test chamber：
In formula,For in-let dimple face equivalent stagnation pressure, Pa；For in-let dimple face hydrostatic pressure average value,n1For measure-point amount in in-let dimple face；p1iFor i-th of measuring point static pressure, Pa in in-let dimple face；ρ is stream Volume density, kg/m3；For in-let dimple surface current body speed average,V1iFor i-th in in-let dimple face Measuring point speed, m/s；
The equivalent total temperature in model control volume in-let dimple face is in test chamber：
In formula,For in-let dimple face equivalent total temperature, K；T1For in-let dimple surface current body absolute temperature, K；V1For entrance control Face fluid velocity processed, m/s；cpFor specific heat at constant pressure, J/ (kgK).
Radial direction directional pressure and speed are unstable in the control of export face, and each measurement point is radially continuously surveyed Amount, the continuous measurement also include multimetering；The control of export face hydrostatic pressure average value and speed average are by each measurement Value is radially integrated and obtained；Therefore the equivalent stagnation pressure in model control volume control of export face is in test chamber：
In formula,For control of export face equivalent stagnation pressure, Pa；For control of export face hydrostatic pressure average value,n2For measure-point amount in control of export face；r2It is control of export face diameter to radius, m；p2iFor outlet I-th of measuring point static pressure, Pa in chain of command；For control of export surface current body speed average,V2iFor I-th of measuring point speed, m/s in control of export face；
The equivalent pressure ratio that fluid flows through model control volume in test chamber is：
The theoretical output work of model can be flowed through the adiabatic expansion work(of the control volume by fluid and is calculated in test chamber, That is,
In formula, wtsFor turbine insulation expansion work, J；cpFor fluid specific heat at constant pressure, J/ (kgK)；Work as in-let dimple face Measure total temperature, K；The equivalent pressure ratio of model control volume in test chamber is flowed through for fluid；γ is adiabatic exponent.
Ram-air turbine output work is：
wf=Tn (9)
In formula, wfFor ram-air turbine output work, J；T is to measure obtained runner torque, N.m；N measurements obtain Secondary speed, r/min；
Ram-air turbine efficiency is：
In formula, η is turbine efficiency, i.e. turbine power extraction efficiency；
D. the initial wind speed V of wind-tunnel is maintained1It is constant, turbine propeller pitch angle, turbine propeller pitch angle change are adjusted by adjusting mechanism Scope isThe static pressure of each measurement point, quiet gentle stream under difference propeller pitch angle when testing the initial wind speed by measuring instrument Body speed, while measure secondary speed and torque；Repeat c. data processing sections in this step and calculate content, respectively obtain initial Turbine theory work(and turbine efficiency under difference propeller pitch angle during wind speed；
Step 9：Test turbine output and turbine efficiency under initial propeller pitch angle, specific measurement process during different wind speed For：
A. change wind tunnel speed, maintain the initial value that turbine propeller pitch angle is test requirements documentWind tunnel speed is according to experiment thunder Promise number determines that wind tunnel speed excursion is V1~V2；
B. initial propeller pitch angle is maintainedIt is constant, adjust wind tunnel speed；According between experiment Reynolds number requirement setting wind tunnel speed It is Δ V every being worth；It is V to adjust wind tunnel speed respectively1+ΔV、V1+2ΔV、V1+3ΔV……V2；Tested respectively by measuring instrument Under the initial propeller pitch angle during different wind speed each measurement point static pressure, static temperature and fluid velocity, while measure secondary speed and torque；
C. data processing：Each measuring point measurement result during according to different wind speed, c. data processing sections calculate in repeat step 7 Content, respectively obtains during different wind speed turbine theory work(and turbine efficiency under initial propeller pitch angle；
Step 10：Turbine output and turbine efficiency, specific measurement process are under difference propeller pitch angle when testing different wind speed：
A. wind tunnel speed is changed, it is a certain to require to adjust turbine propeller pitch angle according to experiment Reynolds numberIt is worth and remains unchanged； ShouldValue is located atBetween；Wind tunnel speed is changed by wind tunnel speed control device, makes wind according to experiment Reynolds number requirement Hole wind speed is respectively V1+ΔV、V1+2ΔV、V1+3ΔV……V2；Tested respectively by measuring instrument under the turbine propeller pitch angle not With the static pressure of each measurement point, static temperature and fluid velocity during wind speed, while measure secondary speed and torque；
B. change turbine propeller pitch angle, control wind tunnel speed as a certain air speed value according to experiment Reynolds number requirement and maintain not Become；The air speed value is located at V1~V2Between；By regulating device adjust turbine propeller pitch angle namely toTest different vane wheel oars under the wind tunnel speed respectively by measuring instrument The static pressure of each measurement point, static temperature and fluid velocity during elongation, while measure secondary speed and torque；
B. data processing：According to each measuring point measurement result, c. data processing sections calculate content in repeat step 7, respectively Obtain during different wind speed under same propeller pitch angle, same wind speed when difference propeller pitch angle under turbine theory work(and turbine efficiency.
The present invention is by measuring the static pressure in model in-let dimple face and control of export face in test chamber, quiet benign fluid Speed, it is real by wind tunnel test methods expanded application in the ram-air turbine wind tunnel test methods based on far field compressible fluid Outfield flowing internal fieldization processing is showed, the theoretical output work of sub-scale model turbine can be asked for using measurement parameter；Binding model turbine Torque and tachometric survey result further ask for turbine efficiency, improve and utilize wind- tunnel investigation ram-air turbine power The ability of performance.
Wherein, " seven-hole probe " described in step 3,4 refer to a kind of size that can obtain flowing velocity, direction, The air measuring device of stagnation pressure and static pressure, is inlaid in the stainless steel tube of a slightly larger outside diameter, head by 7 stainless steel capillaries In cone, it is widely used in the flow measurement that low-speed wind tunnel tests various wide-angles.
Wherein, " measuring instrument " described in step 7,8 refers to pressure-measuring instrument, speed measuring Instrument and temperature Measuring instrument.
(3) advantage and effect
A kind of ram-air turbine wind tunnel test test method proposed by the present invention, i.e., it is a kind of to be based on compressible fluid far field The wind tunnel test test method of the ram-air turbine outfield flowing internal fieldization processing of open loop system, its advantage and effect are：
The present invention increases the streamline bending control of two measurement chains of command and radial direction in test chamber before and after model The streamline bending chain of command of face processed, this two measurement chains of command and radial direction forms measurement control volume；Controlled using the measurement Body can flow the outfield flow-transfer of ram-air turbine for the internal field that gas does work through turbine expansion, realize ram-air Turbine outfield flowing internal fieldization processing；As long as measure static pressure, static temperature and the fluid velocity of former and later two measurement chains of command, so that it may The theoretical output work of turbine model in test air tunnel is calculated with the internal field flowing formula to do work according to gas through turbine expansion；With reference to Torque and the tachometric survey of sub-scale model turbine are as a result, further ask for turbine efficiency in test air tunnel；Its significance show as by Wind tunnel test measurement result asks for ram-air turbine theory acting ability, while can realize the survey of ram-air turbine efficiency Amount.
Test chamber model cootrol body of the present invention determines method, is directed not only to not send out using probe detection streamline Raw curved preceding chain of command, rear chain of command and streamline bending control surface technology, also relate to utilize particle image velocimetry (particle image velximetry, PIV) technology determines test chamber model cootrol body；The particle image velocimetry Technology stream field is noiseless.
Brief description of the drawings
Fig. 1 is the test flow chart of the method for the invention.
Fig. 2 is the wind tunnel test test schematic diagram of the present invention.
Each mark meaning in above-mentioned figure is as follows：
1- in-let dimples face；2- control of export faces；Before 3- chain of command is bent to streamline；After 4- chain of command is bent to streamline； 5- sub-scale model turbines；Drat- ram-air turbine diameter；D1- in-let dimple face diameter；S1- in-let dimple face area；D2- outlet control Face diameter processed；S2- control of export face area.
Embodiment
The present invention will be further described with reference to the accompanying drawings and detailed description.
As shown in Fig. 2, it is the wind tunnel test test schematic diagram of the present invention.Wherein, U be wind-tunnel upper wall surface, L be wind-tunnel lower wall Face, 1 be test chamber in-let dimple face, 2 be test chamber control of export face, 3 be before to streamline bending chain of command, 4 be Backward streamline bending chain of command, DratFor ram-air turbine diameter, D1And S1Respectively test chamber in-let dimple face diameter With area, D2And S2Respectively test chamber control of export face diameter and area.
A kind of ram-air turbine wind tunnel test test method of the present invention, as shown in Figure 1, it is concretely comprised the following steps：
Step 1：Model in wind tunnel installation method routinely, wind-tunnel is reliably mounted on by ram-air turbine model In test section, and it is set to meet airflow direction arrangement；
Step 2：Determine test chamber in-let dimple face 1；The in-let dimple face 1 is located at using turbine Plane of rotation as base It is accurate, at 1/2 turbine diameter of direction of flow, and in-let dimple face 1 is perpendicular to turbine rotation centerline；
Step 3：Determine test chamber control of export face 2；The control of export face 2 is located at sub-scale model turbine trailing edge, specific side Method is the critical surface not bent using seven-hole probe detection model turbine trailing edge streamline, which rotates perpendicular to turbine Center line；
Step 4：Determine that test chamber streamline bends chain of command, streamline bending chain of command includes preceding bent to streamline and controls Face 3 processed and backward streamline bending chain of command 4；Specific method be using streamline in seven-hole probe detection model turbine Plane of rotation not The critical control point to bend, in the circumferential direction each critical control point form Critical Control line；The bending control of forward direction streamline Face 3 be intended on the basis of the Critical Control line airflow direction and turbine rotation centerline move in parallel to in-let dimple face phase Hand over, the cylindricality chain of command formed in gained intersection and turbine Plane of rotation between Critical Control line；Backward streamline bending chain of command 4 The control that each Critical Control line that streamline does not bend in turbine rotation centerline plane for downstream direction is formed Face, the chain of command intersect with control of export face；
Step 5：Determine model control volume in test chamber；The control volume is respectively by in-let dimple face 1, control of export face 2 and streamline bending chain of command composition, streamline bending chain of command includes preceding bending chain of command 3 and the bending control of backward streamline to streamline Face 4 processed；
Step 6：Determine test chamber entrance measurement point and exit measurement point；The test chamber entrance measurement point and Exit measurement point is located at the wind tunnel test segment model in-let dimple face 1 and control of export face 2 respectively, the entrance measurement point and goes out Mouthful measurement point along the circumferential direction equidistantly distributed；
Step 7：Each measuring point is connected by connecting line with measuring instrument respectively；It is required that from each measured hole to measuring instrument The connection of device is reliable, sealing is air tight, fully on；
Step 8：Turbine output and turbine efficiency when testing initial wind speed under difference propeller pitch angle；The test process It is to start wind-tunnel, reaches initial wind speed and the stable operation of test requirements document, respectively surveyed when testing different propeller pitch angles by measuring instrument Static pressure, static temperature and the fluid velocity of point, while measure secondary speed and torque；Obtain during initial wind speed turbine under difference propeller pitch angle Theoretical output work and turbine efficiency；Detailed process is：
A. require to set the initial wind speed V of wind-tunnel according to experiment Reynolds number1；
B. initial propeller pitch angle is set according to test requirements documentThe initial propeller pitch angle is adjusted by adjusting mechanism；
C. the initial wind speed V that wind-tunnel reaches test requirements document is started1；At the beginning of when testing the initial wind speed by measuring instrument The static pressure of each measurement point, static temperature and fluid velocity under beginning propeller pitch angle, while measure secondary speed and torque；
D. the initial wind speed V of wind-tunnel is maintained1It is constant, turbine propeller pitch angle, turbine propeller pitch angle change are adjusted by adjusting mechanism Scope isThe static pressure of each measurement point, quiet gentle stream under difference propeller pitch angle when testing the initial wind speed by measuring instrument Body speed, while measure secondary speed and torque；
E. data processing：By following equation to measurement obtain initial wind speed when difference propeller pitch angle under each measuring point it is quiet Pressure, static temperature and fluid velocity are handled, and respectively obtain initial wind tunnel speed V1Turbine theory work(under Shi Butong turbine propeller pitch angles And turbine efficiency；Specific formula for calculation is：
The equivalent stagnation pressure in model control volume in-let dimple face is in test chamber：
In formula,For in-let dimple face equivalent stagnation pressure, Pa；For in-let dimple face hydrostatic pressure average value,n1For measure-point amount in in-let dimple face；p1iFor i-th of measuring point static pressure, Pa in in-let dimple face；To enter Mouth chain of command fluid velocity average value,V1iFor i-th of measuring point speed, m/s in in-let dimple face；
The equivalent total temperature in model control volume in-let dimple face is in test chamber：
In formula,For in-let dimple face equivalent total temperature, K；T1For in-let dimple surface current body absolute temperature, K；V1For entrance control Face fluid velocity processed, m/s；cpFor specific heat at constant pressure, J/ (kgK).
Radial direction directional pressure and speed are unstable in the control of export face, and each measurement point is radially continuously surveyed Amount, the continuous measurement also include multimetering；The control of export face hydrostatic pressure average value and speed average are by each measurement Value is radially integrated and obtained；Therefore the equivalent stagnation pressure in model control volume control of export face is in test chamber：
In formula,For control of export face equivalent stagnation pressure, Pa；For control of export face hydrostatic pressure average value,n2For measure-point amount in control of export face；r2It is control of export face diameter to radius, m；p2iFor outlet I-th of measuring point static pressure, Pa in chain of command；For control of export surface current body speed average,V2iFor I-th of measuring point speed, m/s in control of export face；
The equivalent pressure ratio that fluid flows through model control volume in test chamber is：
The theoretical output work of model can be flowed through the adiabatic expansion work(of the control volume by fluid and is calculated in test chamber, That is,
In formula, wtsFor turbine insulation expansion work, J；cpFor fluid specific heat at constant pressure, J/ (kgK)；Work as in-let dimple face Measure total temperature, K；The equivalent pressure ratio of model control volume in test chamber is flowed through for fluid；γ is adiabatic exponent；
Ram-air turbine output work is：
wf=Tn (9)
In formula, wfFor ram-air turbine output work, J；T is to measure obtained runner torque, N.m；N measurements obtain Secondary speed, r/min；
Ram-air turbine efficiency is：
In formula, η is turbine efficiency, i.e. turbine power extraction efficiency；
Step 9：Test turbine output and turbine efficiency under initial propeller pitch angle, specific measurement process during different wind speed For：
A. change wind tunnel speed, maintain the initial value that turbine propeller pitch angle is test requirements documentWind tunnel speed is according to experiment thunder Promise number determines that wind tunnel speed excursion is V1~V2；
B. initial propeller pitch angle is maintainedIt is constant, adjust wind tunnel speed；According to test requirements document, wind tunnel speed spacing value Δ is set V；It is V to adjust wind tunnel speed respectively1+ΔV、V1+2ΔV、V1+3ΔV……V2；Measure the initial paddle respectively by measuring instrument Under elongation during different wind speed each measurement point static pressure, static temperature and fluid velocity, while measure secondary speed and torque；
C. data processing：According to each measuring point measurement result under different wind speed, e. data processings in the present embodiment step 8 are repeated Part calculates content, turbine theory work(and turbine efficiency when respectively obtaining different wind speed under initial propeller pitch angle；
Step 10：Turbine output and turbine efficiency, specific measurement process are under difference propeller pitch angle when testing different wind speed：
A. change wind tunnel speed, be a certain according to test requirements document adjustment turbine propeller pitch angleIt is worth and remains unchanged；ShouldValue It is located atBetween；Wind tunnel speed is controlled by wind tunnel speed control device, makes wind tunnel speed according to experiment Reynolds number requirement Respectively V1+ΔV、V1+2ΔV、V1+3ΔV……V2；Test different wind speed under the turbine propeller pitch angle respectively by measuring instrument When each measurement point static pressure, static temperature and fluid velocity, while measure secondary speed and torque；
B. change turbine propeller pitch angle, control wind tunnel speed as a certain air speed value according to experiment Reynolds number requirement and maintain not Become；The air speed value is located at V1~V2Between；By regulating device change turbine propeller pitch angle namely toTest different vane wheel oars under the wind tunnel speed respectively by measuring instrument The static pressure of each measurement point, static temperature and fluid velocity during elongation, while measure secondary speed and torque；
B. data processing：According to each measuring point measurement result, repeat in the present embodiment step 8 in the calculating of e. data processing sections Hold, respectively obtain during different wind speed under same propeller pitch angle, same wind speed when difference propeller pitch angle under turbine theory work(and turbine efficiency.
In the present embodiment, during ram-air turbine wind tunnel test, in test chamber turbine model in-let dimple face and go out Distribution measuring head on mouth chain of command, it is not necessary to measured hole is opened up on sub-scale model turbine 5, not only reduces experiment preparation amount, And the convenient batch testing for carrying out ram-air turbine.

Claims (3)

  1. A kind of 1. ram-air turbine wind tunnel test test method, it is characterised in that：Its step is as follows：
    Step 1：Ram-air turbine model is installed in test chamber；
    Step 2：Determine the in-let dimple face of model in test chamber；The in-let dimple face is using turbine Plane of rotation as base Standard, to 1/2 turbine diameter of direction of flow at and perpendicular to the section of turbine rotation centerline；
    Step 3：Determine the control of export face of model in test chamber；Specific method is to be visited using seven-hole probe in turbine trailing edge The Critical Control face that flow measurement line does not bend, the Critical Control face is perpendicular to turbine rotation centerline, and the tangential speed of fluid It is zero to spend component；
    Step 4：Determine the streamline bending chain of command of model in test chamber, including it is preceding to streamline bending chain of command and backward current Line bends chain of command；Specific method is not bent using streamline in seven-hole probe detection model turbine Plane of rotation, i.e., not There are the critical control point of tangential speed component, each critical control point forms Critical Control line in the circumferential direction；Forward direction streamline Bending chain of command is to intend airflow direction on the basis of the Critical Control line to be moved to and entrance control parallel to turbine rotation centerline Face processed is intersected, the cylindricality chain of command formed in gained intersection and turbine Plane of rotation between Critical Control line；Backward streamline bending Chain of command is formed for the downstream direction Critical Control line that respectively streamline does not bend in turbine rotation centerline plane Chain of command, which intersects with control of export face；
    Step 5：Determine the control volume of model in test chamber；The control volume respectively by in-let dimple face, control of export face and Streamline bending chain of command composition；Streamline bending chain of command includes preceding to streamline bending chain of command and the bending control of backward streamline Face；
    Step 6：Determine test chamber entrance measurement point and exit measurement point；The test chamber entrance measurement point and outlet Measurement point is located at the in-let dimple face and control of export face of the wind tunnel test segment model respectively；The entrance measurement point and outlet are surveyed Measure point along the circumferential direction equidistantly distributed；
    Step 7：Each measurement point is passed through into connecting line and measuring instrument reliable connected respectively；
    Step 8：Turbine output when testing initial wind speed under difference propeller pitch angle, calculate and obtain turbine efficiency, specific measurement Process is：
    A., the initial wind speed of wind-tunnel and initial propeller pitch angle are set；The initial wind speed of wind-tunnel is determined according to experiment Reynolds number, is set to V1； It is initial value according to test requirements document adjustment turbine propeller pitch angle
    B. the initial wind speed V that wind-tunnel reaches test requirements document is started1；Initial paddle under the initial wind speed is tested by measuring instrument The static pressure of each measurement point, static temperature and fluid velocity during elongation, while measure secondary speed and torque；Wherein, in in-let dimple face Radial direction pressure and velocity-stabilization, and radial direction directional pressure and speed are unstable in control of export face；In-let dimple face internal diameter To direction spot measurement, and radial direction continuously measures in control of export face, which also includes multimetering；
    C. data processing：
    According to each measuring point measurement result, during by following equation to initial wind speed under initial propeller pitch angle each measuring point test data into Row processing, calculating can obtain during initial wind speed that turbine theory output work and turbine efficiency, specific formula for calculation are under initial propeller pitch angle：
    The equivalent stagnation pressure in model control volume in-let dimple face is in test chamber：
    <mrow> <msubsup> <mi>p</mi> <mn>1</mn> <mo>*</mo> </msubsup> <mo>=</mo> <msub> <mover> <mi>p</mi> <mo>&amp;OverBar;</mo> </mover> <mn>1</mn> </msub> <mo>+</mo> <mfrac> <mn>1</mn> <mn>2</mn> </mfrac> <mi>&amp;rho;</mi> <msubsup> <mover> <mi>V</mi> <mo>&amp;OverBar;</mo> </mover> <mn>1</mn> <mn>2</mn> </msubsup> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>4</mn> <mo>)</mo> </mrow> </mrow>
    In formula,For in-let dimple face equivalent stagnation pressure, Pa；For in-let dimple face hydrostatic pressure average value, n1For measure-point amount in in-let dimple face；p1iFor i-th of measuring point static pressure, Pa in in-let dimple face；ρ is fluid density, kg/m3； For in-let dimple surface current body speed average,V1iFor i-th of measuring point speed, m/s in in-let dimple face；
    The equivalent total temperature in model control volume in-let dimple face is in test chamber：
    <mrow> <msubsup> <mi>T</mi> <mn>1</mn> <mo>*</mo> </msubsup> <mo>=</mo> <msub> <mi>T</mi> <mn>1</mn> </msub> <mo>+</mo> <mfrac> <msubsup> <mi>V</mi> <mn>1</mn> <mn>2</mn> </msubsup> <mrow> <mn>2</mn> <msub> <mi>c</mi> <mi>p</mi> </msub> </mrow> </mfrac> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>5</mn> <mo>)</mo> </mrow> </mrow>
    In formula,For in-let dimple face equivalent total temperature, K；T1For in-let dimple surface current body absolute temperature, K；V1For in-let dimple face Fluid velocity, m/s；cpFor specific heat at constant pressure, J/ (kgK)；
    Radial direction directional pressure and speed are unstable in the control of export face, and each measurement point radially continuously measures, The continuous measurement also includes multimetering；The control of export face hydrostatic pressure average value and speed average are by each measured value edge Radial Integrals obtain；Therefore the equivalent stagnation pressure in model control volume control of export face is in test chamber：
    <mrow> <msubsup> <mi>p</mi> <mn>2</mn> <mo>*</mo> </msubsup> <mo>=</mo> <msub> <mover> <mi>p</mi> <mo>&amp;OverBar;</mo> </mover> <mn>2</mn> </msub> <mo>+</mo> <mfrac> <mn>1</mn> <mn>2</mn> </mfrac> <mi>&amp;rho;</mi> <msubsup> <mover> <mi>V</mi> <mo>&amp;OverBar;</mo> </mover> <mn>2</mn> <mn>2</mn> </msubsup> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>6</mn> <mo>)</mo> </mrow> </mrow>
    In formula,For control of export face equivalent stagnation pressure, Pa；For control of export face hydrostatic pressure average value,n2For measure-point amount in control of export face；r2It is control of export face diameter to radius, m；p2iFor outlet I-th of measuring point static pressure, Pa in chain of command；For control of export surface current body speed average,V2iFor I-th of measuring point speed, m/s in control of export face；
    The equivalent pressure ratio that fluid flows through model control volume in test chamber is：
    <mrow> <msubsup> <mi>&amp;pi;</mi> <mi>t</mi> <mo>*</mo> </msubsup> <mo>=</mo> <mfrac> <msubsup> <mi>p</mi> <mn>1</mn> <mo>*</mo> </msubsup> <msubsup> <mi>p</mi> <mn>2</mn> <mo>*</mo> </msubsup> </mfrac> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>7</mn> <mo>)</mo> </mrow> </mrow>
    The theoretical output work of model is flowed through the adiabatic expansion work(of the control volume by fluid and is calculated in test chamber, i.e.
    <mrow> <msub> <mi>w</mi> <mrow> <mi>t</mi> <mi>s</mi> </mrow> </msub> <mo>=</mo> <msub> <mi>c</mi> <mi>p</mi> </msub> <msubsup> <mi>T</mi> <mn>1</mn> <mo>*</mo> </msubsup> <mo>&amp;lsqb;</mo> <mn>1</mn> <mo>-</mo> <mfrac> <mn>1</mn> <msup> <mrow> <mo>(</mo> <msubsup> <mi>&amp;pi;</mi> <mi>t</mi> <mo>*</mo> </msubsup> <mo>)</mo> </mrow> <mfrac> <mrow> <mi>&amp;gamma;</mi> <mo>-</mo> <mn>1</mn> </mrow> <mi>&amp;gamma;</mi> </mfrac> </msup> </mfrac> <mo>&amp;rsqb;</mo> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>8</mn> <mo>)</mo> </mrow> </mrow>
    In formula, wtsFor turbine insulation expansion work, J；cpFor fluid specific heat at constant pressure, J/ (kgK)；It is total for in-let dimple face equivalent Temperature, K；The equivalent pressure ratio of model control volume in test chamber is flowed through for fluid；γ is adiabatic exponent；
    Ram-air turbine output work is：
    wf=Tn (9)
    In formula, wfFor ram-air turbine output work, J；T is to measure obtained runner torque, N.m；N is the turbine that measurement obtains Rotating speed, r/min；
    Ram-air turbine efficiency is：
    <mrow> <mi>&amp;eta;</mi> <mo>=</mo> <mfrac> <msub> <mi>w</mi> <mi>f</mi> </msub> <msub> <mi>w</mi> <mrow> <mi>t</mi> <mi>s</mi> </mrow> </msub> </mfrac> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>10</mn> <mo>)</mo> </mrow> </mrow>
    In formula, η is turbine efficiency, i.e. turbine power extraction efficiency；
    D. the initial wind speed V of wind-tunnel is maintained1It is constant, turbine propeller pitch angle is adjusted by adjusting mechanism, which isThe static pressure of each measurement point, static temperature and fluid velocity under difference propeller pitch angle when testing the initial wind speed by measuring instrument, Measure secondary speed and torque at the same time；Repeat c. data processing sections in this step and calculate content, when respectively obtaining initial wind speed Turbine theory work(and turbine efficiency under different propeller pitch angles；
    Step 9：Testing turbine output and turbine efficiency under initial propeller pitch angle, specific measurement process during different wind speed is：
    A. change wind tunnel speed, maintain the initial value that turbine propeller pitch angle is test requirements documentWind tunnel speed is according to experiment Reynolds number Determine, wind tunnel speed excursion is V1~V2；
    B. initial propeller pitch angle is maintainedIt is constant, adjust wind tunnel speed；Require to set wind tunnel speed spacing value according to experiment Reynolds number For Δ V；It is V to adjust wind tunnel speed respectively1+ΔV、V1+2ΔV、V1+3ΔV……V2；It is first to test this respectively by measuring instrument Under beginning propeller pitch angle during different wind speed each measurement point static pressure, static temperature and fluid velocity, while measure secondary speed and torque；
    C. data processing：Each measuring point measurement result during according to different wind speed, in c. data processing sections calculate in repeat step 7 Hold, respectively obtain during different wind speed turbine theory work(and turbine efficiency under initial propeller pitch angle；
    Step 10：Turbine output and turbine efficiency, specific measurement process are under difference propeller pitch angle when testing different wind speed：
    A. wind tunnel speed is changed, it is a certain to require to adjust turbine propeller pitch angle according to experiment Reynolds numberIt is worth and remains unchanged；Should Value is located atBetween；Wind tunnel speed is changed by wind tunnel speed control device, makes wind-tunnel wind according to experiment Reynolds number requirement Speed is respectively V1+ΔV、V1+2ΔV、V1+3ΔV……V2；Test different wind under the turbine propeller pitch angle respectively by measuring instrument The static pressure of each measurement point, static temperature and fluid velocity when fast, while measure secondary speed and torque；
    B. change turbine propeller pitch angle, control wind tunnel speed as an air speed value according to experiment Reynolds number requirement and remain unchanged；The wind Speed value is located at V1~V2Between；By regulating device adjust turbine propeller pitch angle namely to Tested respectively by measuring instrument each during different turbine propeller pitch angles under the wind tunnel speed Static pressure, static temperature and the fluid velocity of measurement point, while measure secondary speed and torque；
    B. data processing：According to each measuring point measurement result, c. data processing sections calculate content in repeat step 7, respectively obtain During different wind speed under same propeller pitch angle, same wind speed when difference propeller pitch angle under turbine theory work(and turbine efficiency；
    The present invention is by measuring the static pressure in model in-let dimple face and control of export face in test chamber, quiet benign fluid speed Degree, by wind tunnel test methods expanded application in the ram-air turbine wind tunnel test methods based on far field compressible fluid, is realized Outfield flowing internal fieldization processing, can ask for using measurement parameter the theoretical output work of sub-scale model turbine；Binding model turbine Torque and tachometric survey result further ask for turbine efficiency, improve and utilize wind- tunnel investigation ram-air turbine dynamic property The ability of energy.
  2. A kind of 2. ram-air turbine wind tunnel test test method according to claim 1, it is characterised in that：
    " seven-hole probe " described in step 3,4 refers to a kind of size that can obtain flowing velocity, direction, stagnation pressure and static pressure Air measuring device, be inlaid in by 7 stainless steel capillaries in the stainless steel tube of a slightly larger outside diameter, head in cone, It is widely used in the flow measurement that low-speed wind tunnel tests various wide-angles.
  3. A kind of 3. ram-air turbine wind tunnel test test method according to claim 1, it is characterised in that：
    " measuring instrument " described in step 7,8 refers to pressure-measuring instrument, speed measuring Instrument and thermometric instruments.
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