CN108036917B - 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 PDFInfo
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Abstract
The present invention provides a kind of ram-air turbine wind tunnel test test method, and steps are as follows: 1: ram-air turbine model is mounted in test chamber；2: determining the in-let dimple face of model in test chamber；3: determining the control of export face of model in test chamber；4: determining the streamline bending control plane of model in test chamber；5: determining the control volume of model in test chamber；6: determining 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 calculates and obtains turbine efficiency；9: testing the turbine output and turbine efficiency when different wind speed under initial propeller pitch angle；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
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 of far field open loop system handles wind tunnel test test method, belongs to ram-air turbine
Wind-tunnel technique field.
Background technique
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 guarantees flight safety.Wherein, turbine rotates under windstream effect and gas
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 mention
Taking efficiency is the core of 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..Currently, experimental study mainly uses wind tunnel test, and it is seldom
Live (outfield) test is used as conventional wind machine turbine, main cause is that live (outfield) test 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.It is tested however, taking a flight test
It is highly difficult big to demonstrate,prove process risk, and there has been no mature Flight methods for the country 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.
Currently, the ram-air turbine that mainly comprises the processes of of ram-air turbine ground wind tunnel test methods is reliably pacified
Loaded in test air tunnel；Starting wind-tunnel simultaneously makes wind tunnel speed reach specified value；Ram-air turbine acts on backspin in windstream
Turn and extracts energy from tunnel airstream；Using wind tunnel test system real-time measurement ram-air turbine revolving speed and output torque,
It can be calculated turbine output rate, and be ultimately converted to hydraulic energy or electrical energy drive loaded work piece；Gas in wind-tunnel is monitored simultaneously
The signals 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.
Currently, pneumatic equipment bladess wind tunnel test survey is mainly used for reference in ram-air turbine vane airfoil profile aeroperformance wind tunnel test
Amount method, i.e., the liter resistance coefficient measuring method based on momentum theory (are detailed in 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
Lower wall surface hydrostatic pressure on degree, speed of incoming flow and wind-tunnel corresponding with model calculates wall pressure according to following formula (1)；So
Integrate to wall pressure and then acquire the lift coefficient of model leaf according to following formula (2) afterwards；Further, measurement comes respectively
Flow direction wind-tunnel inlet flowing stagnation pressure and static pressure, model rear at a certain distance from tail flowing stagnation pressure and static pressure, then according to
The resistance coefficient of model leaf is acquired along path wl integral 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 CplRespectively indicate by
The surface pressure coefficient that the upper and lower wall measurement parameter of wind-tunnel acquires；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 flow 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 indicated
Path of integration along normal direction in flowing tail area.
However, there is also shortcomings for the test method, it is mainly manifested in the following aspects: (1) the upper and lower wall surface of wind-tunnel
The determination of point position is affected to measurement result, it is necessary to empirically be corrected；(2) it does not account at model rear tail
The tangential component of air velocity.
In view of the above deficiencies, the Jiao Yu Qin etc. of Northwestern Polytechnical University discloses a kind of wind tunnel test side based on momentum theorem
Method (is detailed in Jiao Yuqin, a kind of wind tunnel test methods [P] application number based on momentum theorem of the such as Wang Long, Gao Yongwei
201210251010.3).This method increases by two measurement control planes before and after aerofoil profile model, makes to measure control plane and wind tunnel wall
Complete fixed control volume is constituted, the fluid parameter on two control planes is measured respectively, then according to momentum theory and the moment of momentum
Principle computation model aeroperformance.Increased control volume is fixed control volume in the test method, and the survey pressure on wind tunnel wall
Point is distributed on the center line of test upper wall and test 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 test 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 achieving the measurement of model Moment and carrying out the test of momentum method three dimensional wind tunnel.However, the test method is increased
Control volume beFixed control volume, using the percentage of aerofoil profile model chord length as the foundation for determining the forward and backward control plane of control volume.I
Know, when the variation of wind-tunnel speed of incoming flow, 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, and to reduce disturbing influence, improve measurement accuracy.
Summary 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, 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 calculated result must be modified when turbo blade Airfoil Testing, do not account for mould
The deficiencies of air velocity influences at type rear tail, proposes a kind of 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, establishes for ram-air turbine Dynamic Behavior
Basis is determined.
(2) technical solution
Technical solution and specific implementation process according to the present invention are as follows:
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 control plane, control volume, test procedure and data processing etc. in test chamber.
Model control plane is that gas streamline does not bend in test air tunnel in the test chamber, i.e., without tangential speed
Spend the control plane of component.Control plane is bent including in-let dimple face, control of export face and streamline.It is characterized by: the entrance
Control plane 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 is that turbine rear streamline does not bend, i.e., fluid does not have tangential speed component and perpendicular to turbine rotation center
The critical surface of line；The streamline bending control plane includes preceding to streamline bending control plane and backward streamline bending control plane；Specifically
Ground: each critical control point that streamline does not bend in sub-scale model turbine Plane of rotation along the circumferential direction constitutes Critical Control line, preceding
To streamline bending control plane be on the basis of the Critical Control line intend airflow direction be parallel to turbine rotation centerline be moved to
In-let dimple face is intersected, the cylindricality control plane formed between Critical Control line in gained intersection and turbine Plane of rotation；Backward current
Line bending control plane is the Critical Control that downstream direction does not bend perpendicular to streamline in turbine rotation centerline plane respectively
The control plane that line is constituted, the control plane 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 control plane is constituted, the streamline bending control plane include preceding to streamline bending control plane 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: determining the in-let dimple face of model in test chamber；The in-let dimple face is to be with turbine Plane of rotation
Benchmark, to 1/2 turbine diameter of direction of flow at and perpendicular to the section of turbine rotation centerline；
Step 3: determining 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 control plane, including it is preceding to streamline bending control plane and after
Control plane 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 constitutes Critical Control line in the circumferential direction；Forward direction
Streamline bending control plane is parallel to turbine rotation centerline for airflow direction quasi- on the basis of the Critical Control line and is moved to and enters
Mouth control plane intersects, the cylindricality control plane formed between Critical Control line in gained intersection and turbine Plane of rotation；Backward streamline
Bending control plane is the Critical Control line that downstream direction does not bend perpendicular to streamline in turbine rotation centerline plane respectively
The control plane of composition, the control plane intersect with control of export face；
Step 5: determining 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 control plane composition, the streamline are bent before control plane includes to streamline and are bent control plane and the bending control of backward streamline
Face processed；
Step 6: determining 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 model in the test chamber；The entrance measurement point and
Exit 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 calculates and obtains turbine efficiency, specifically
Measurement process are as follows:
A., the initial wind speed and initial propeller pitch angle of wind-tunnel are set；The initial wind speed of wind-tunnel is determined according to test Reynolds number, if
For V1；It is initial value according to test requirements document adjustment turbine propeller pitch angle
B. starting wind-tunnel reaches the initial wind speed V of test requirements document1；It is tested under the initial wind speed just by measuring instrument
The static pressure, static temperature and fluid velocity of each measurement point when beginning propeller pitch angle, while measuring secondary speed and torque；Wherein, in-let dimple
Radial directional pressure and velocity-stabilization in face, and radial 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, when by following equation to initial wind speed under initial propeller pitch angle each measuring point test number
According to being handled, can be calculated when initial wind speed turbine theory output work and turbine efficiency under initial propeller pitch angle, it is specific calculate it is public
Formula are as follows:
The equivalent stagnation pressure in model control volume in-let dimple face in test chamber are as follows:
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,V1iIt is i-th in in-let dimple face
Measuring point speed, m/s；
The equivalent total temperature in model control volume in-let dimple face in test chamber are as follows:
In formula,For in-let dimple face equivalent total temperature, K；T1For in-let dimple surface current body absolute temperature, K；V1For initial wind
Speed, m/s；cpFor specific heat at constant pressure, J/ (kgK).
Radial directional pressure and speed are unstable in the control of export face, and each measurement point is radially continuously surveyed
Amount, which also includes multimetering；The control of export face hydrostatic pressure average value and speed average are by each measurement
Value is radially integrated and is obtained；Therefore in test chamber model control volume control of export face equivalent stagnation pressure are as follows:
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 control plane；For control of export surface current body speed average,V2iFor
I-th of measuring point speed, m/s in control of export face；
Fluid flows through the equivalent pressure ratio of model control volume in test chamber are as follows:
The adiabatic expansion function that the theoretical output work of model can be flowed through the control volume by fluid in test chamber is calculated,
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 are as follows:
wf=Tn (9)
In formula, wfFor ram-air turbine output work, J；T is the runner torque that measurement obtains, N.m；N measurement obtains
Secondary speed, r/min；
Ram-air turbine efficiency are as follows:
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 variation are adjusted by regulating mechanism
Range 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 measuring secondary speed and torque；It repeats c. data processing section in this step and calculates content, respectively obtain initial
Turbine theory function and turbine efficiency under difference propeller pitch angle when wind speed；
Step 9: testing the turbine output and turbine efficiency when different wind speed under initial propeller pitch angle, specific measurement process
Are as follows:
A. change wind tunnel speed, maintaining turbine propeller pitch angle is the initial value of test requirements documentWind tunnel speed is according to test thunder
Promise number determines that wind tunnel speed variation range is V1~V2；
B. initial propeller pitch angle is maintainedIt is constant, adjust wind tunnel speed；It requires to be arranged between wind tunnel speed according to test Reynolds number
It is Δ V every being worth；Adjusting wind tunnel speed respectively is V1+ΔV、V1+2ΔV、V1+3ΔV…...V2；It is tested respectively by measuring instrument
Under the initial propeller pitch angle when different wind speed each measurement point static pressure, static temperature and fluid velocity, while measuring secondary speed and torque；
C. data processing: each measuring point measurement result when according to different wind speed repeats c. data processing section in step 8 and calculates
Content respectively obtains when different wind speed turbine theory function and turbine efficiency under initial propeller pitch angle；
Step 10: turbine output and turbine efficiency, specific measurement process under difference propeller pitch angle when testing different wind speed are as follows:
A. change wind tunnel speed, require to adjust turbine propeller pitch angle to be a certain according to test Reynolds numberIt is worth and remains unchanged；
It shouldValue is located atBetween；Change wind tunnel speed by wind tunnel speed control device, requires to make wind according to test Reynolds number
Hole wind speed is respectively V1+ΔV、V1+2ΔV、V1+3ΔV…...V2；It is tested respectively by measuring instrument under the turbine propeller pitch angle not
With static pressure, static temperature and the fluid velocity of measurement point each when wind speed, while measuring secondary speed and torque；
B. change turbine propeller pitch angle, require control wind tunnel speed to be a certain air speed value and maintain not according to test Reynolds number
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, static temperature and fluid velocity of each measurement point when elongation, while measuring secondary speed and torque；
C. it data processing: according to each measuring point measurement result, repeats c. data processing section in step 8 and calculates content, respectively
Obtain when different wind speed under same propeller pitch angle, when same wind speed turbine theory function and turbine efficiency under difference propeller pitch angle.
The present invention passes through the static pressure in model in-let dimple face and control of export face, quiet benign fluid in measurement test chamber
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 sought using measurement parameter；Binding model turbine
Torque and tachometric survey result further seek turbine efficiency, improve and utilize wind- tunnel investigation ram-air turbine power
The ability of performance.
Wherein, described in step 3,4 " seven-hole probe " 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 outer 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, described in step 7,8 " measuring instrument " 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, advantage and effect are:
The present invention increases by two measurement control planes in test chamber before and after model and the streamline of radial direction is bent control
The streamline bending control plane of face processed, this two measurement control planes and radial direction constitutes measurement control volume；It is controlled using the measurement
Body can be that the internal field that gas does work through turbine expansion is flowed the outfield flow-transfer of ram-air turbine, realize ram-air
Flow internal fieldization processing in turbine outfield；As long as measuring static pressure, static temperature and the fluid velocity of former and later two measurement control planes, 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；In conjunction with
The torque and tachometric survey of sub-scale model turbine are as a result, further seek turbine efficiency in test air tunnel；Its significance show as by
Wind tunnel test measurement result seeks ram-air turbine theory acting ability, while the survey of ram-air turbine efficiency may be implemented
Amount.
Model control volume determines method in test chamber of the present invention, is directed not only to using probe detection streamline not
Preceding control plane, rear control plane and the streamline bending control surface technology to bend, also relates to utilize particle image velocimetry
(particle image velximetry, PIV) technology determines model control volume in test chamber；The particle picture is surveyed
Fast technology stream field is noiseless.
Detailed description of the invention
Fig. 1 is the test flow chart of the method for the invention.
Fig. 2 is wind tunnel test test schematic diagram of the invention.
Each label meaning in above-mentioned figure is as follows:
1- in-let dimple face；The control of export face 2-；Control plane is bent to streamline before 3-；Control plane is bent to streamline after 4-；
5- sub-scale model turbine；DratRam-air turbine diameter；D1In-let dimple face diameter；S1In-let dimple face area；D2Outlet control
Face diameter processed；S2Control of export face area.
Specific embodiment
The present invention will be further described with reference to the accompanying drawings and detailed description.
As shown in Fig. 2, being wind tunnel test test schematic diagram of the invention.Wherein, U is wind-tunnel upper wall surface, L is 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 control plane, 4 be
Backward streamline is bent control plane, 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, the specific steps are that:
Step 1: ram-air turbine model is reliably mounted on wind-tunnel by model in wind tunnel installation method routinely
In test section, and it is made to meet airflow direction arrangement；
Step 2: determining 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 quasi-, at 1/2 turbine diameter of direction of flow, and in-let dimple face 1 is perpendicular to turbine rotation centerline；
Step 3: determining test chamber control of export face 2；The control of export face 2 is located at sub-scale model turbine rear, specific side
Method is the critical surface not bent using seven-hole probe detection model turbine rear streamline, which rotates perpendicular to turbine
Center line；
Step 4: determining that test chamber streamline is bent control plane, it includes that preceding be bent to streamline is controlled which, which is bent control plane,
Face 3 processed and backward streamline are bent control plane 4；Specific method be using streamline in seven-hole probe detection model turbine Plane of rotation not
The critical control point to bend, each critical control point constitutes Critical Control line in the circumferential direction；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
It hands over, the cylindricality control plane formed between Critical Control line in gained intersection and turbine Plane of rotation；Backward streamline is bent control plane 4
The control constituted for downstream direction perpendicular to each Critical Control line that streamline in turbine rotation centerline plane does not bend
Face, the control plane intersect with control of export face；
Step 5: determining 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 control plane composition, it includes preceding being bent control plane 3 and the bending control of backward streamline to streamline which, which is bent control plane,
Face 4 processed；
Step 6: determining test chamber entrance measurement point and exit measurement point；The test chamber entrance measurement point and
Exit measurement point is located at model in-let dimple face 1 and control of export face 2 in the test chamber, the entrance measurement point and
Exit measurement point along the circumferential direction equidistantly distributed；
Step 7: each measuring point being passed through into connecting line respectively and is connected to measuring instrument；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 starting wind-tunnel, reaches the initial wind speed of test requirements document and stable operation, respectively surveyed when testing different propeller pitch angles by measuring instrument
Static pressure, static temperature and the fluid velocity of point, while measuring secondary speed and torque；Obtain when initial wind speed turbine under difference propeller pitch angle
Theoretical output work and turbine efficiency；Detailed process are as follows:
A. the setting initial wind speed V of wind-tunnel is required according to test Reynolds number1；
B. initial propeller pitch angle is set according to test requirements documentThe initial propeller pitch angle is adjusted by regulating mechanism；
C. starting wind-tunnel reaches the initial wind speed V of test requirements document1；At the beginning of when testing the initial wind speed by measuring instrument
The static pressure, static temperature and fluid velocity of each measurement point under beginning propeller pitch angle, while measuring 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 variation are adjusted by regulating mechanism
Range 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 measuring 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 initial wind tunnel speed V is respectively obtained1Turbine theory function under Shi Butong turbine propeller pitch angle
And turbine efficiency；Specific formula for calculation are as follows:
The equivalent stagnation pressure in model control volume in-let dimple face in test chamber are as follows:
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；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 in test chamber are as follows:
In formula,For in-let dimple face equivalent total temperature, K；T1For in-let dimple surface current body absolute temperature, K；V1For initial wind
Speed, m/s；cpFor specific heat at constant pressure, J/ (kgK).
Radial directional pressure and speed are unstable in the control of export face, and each measurement point is radially continuously surveyed
Amount, which also includes multimetering；The control of export face hydrostatic pressure average value and speed average are by each measurement
Value is radially integrated and is obtained；Therefore in test chamber model control volume control of export face equivalent stagnation pressure are as follows:
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 control plane；For control of export surface current body speed average,V2iFor
I-th of measuring point speed, m/s in control of export face；
Fluid flows through the equivalent pressure ratio of model control volume in test chamber are as follows:
The adiabatic expansion function that the theoretical output work of model can be flowed through the control volume by fluid in test chamber is calculated,
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 are as follows:
wf=Tn (9)
In formula, wfFor ram-air turbine output work, J；T is the runner torque that measurement obtains, N.m；N measurement obtains
Secondary speed, r/min；
Ram-air turbine efficiency are as follows:
In formula, η is turbine efficiency, i.e. turbine power extraction efficiency；
Step 9: testing the turbine output and turbine efficiency when different wind speed under initial propeller pitch angle, specific measurement process
Are as follows:
A. change wind tunnel speed, maintaining turbine propeller pitch angle is the initial value of test requirements documentWind tunnel speed is according to test thunder
Promise number determines that wind tunnel speed variation range 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；Adjusting wind tunnel speed respectively is V1+ΔV、V1+2ΔV、V1+3ΔV…...V2；Measure the initial paddle respectively by measuring instrument
Under elongation when different wind speed each measurement point static pressure, static temperature and fluid velocity, while measuring secondary speed and torque；
C. data processing: according to measuring point measurement result each under different wind speed, e. data processing in the present embodiment step 8 is repeated
Part calculates content, turbine theory function and turbine efficiency when respectively obtaining different wind speed under initial propeller pitch angle；
Step 10: turbine output and turbine efficiency, specific measurement process under difference propeller pitch angle when testing different wind speed are as follows:
A. change wind tunnel speed, be a certain according to test requirements document adjustment turbine propeller pitch angleIt is worth and remains unchanged；It shouldValue
It is located atBetween；Wind tunnel speed is controlled by wind tunnel speed control device, requires to make wind tunnel speed according to test Reynolds number
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 measuring secondary speed and torque；
B. change turbine propeller pitch angle, require control wind tunnel speed to be a certain air speed value and maintain not according to test Reynolds number
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, static temperature and fluid velocity of each measurement point when elongation, while measuring secondary speed and torque；
C. it data processing: according to each measuring point measurement result, repeats in the present embodiment step 8 in the calculating of e. data processing section
Hold, respectively obtains when different wind speed under same propeller pitch angle, when same wind speed turbine theory function and turbine efficiency under difference propeller pitch angle.
In the present embodiment, when ram-air turbine wind tunnel test, in test chamber turbine model in-let dimple face and go out
Distribution measuring head on mouth control plane, does not need to open up measured hole on sub-scale model turbine 5, not only reduces test preparation amount,
And facilitate the batch testing for carrying out ram-air turbine.
Claims (3)
1. a kind of ram-air turbine wind tunnel test test method, it is characterised in that: its step are as follows:
Step 1: ram-air turbine model is mounted in test chamber；
Step 2: determining 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: determining the control of export face of model in test chamber；Specific method is to be visited using seven-hole probe in turbine rear
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
Spending component is zero；
Step 4: determining the streamline bending control plane of model in test chamber, including preceding to streamline bending control plane and backward current
Line is bent control plane；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 points of tangential speed component, and each critical control point constitutes Critical Control line in the circumferential direction；Forward direction streamline
Bending control plane is parallel to turbine rotation centerline for airflow direction quasi- on the basis of the Critical Control line and is moved to and entrance control
Face processed is intersected, the cylindricality control plane formed between Critical Control line in gained intersection and turbine Plane of rotation；Backward streamline bending
Control plane is that downstream direction is respectively constituted perpendicular to the Critical Control line that streamline in turbine rotation centerline plane does not bend
Control plane, which intersects with control of export face；
Step 5: determining the control volume of model in test chamber；The control volume respectively by in-let dimple face, control of export face and
Streamline is bent control plane composition；It includes preceding to streamline bending control plane and the bending control of backward streamline that the streamline, which is bent control plane,
Face；
Step 6: determining 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 model in the test chamber；The entrance measurement point and outlet
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 calculates and obtains turbine efficiency, specific to measure
Process are as follows:
A., the initial wind speed and initial propeller pitch angle of wind-tunnel are set；The initial wind speed that wind-tunnel is determined according to test Reynolds number, is set as V1；
It is initial value according to test requirements document adjustment turbine propeller pitch angle
B. starting wind-tunnel reaches the initial wind speed V of test requirements document1；Initial paddle under the initial wind speed is tested by measuring instrument
The static pressure, static temperature and fluid velocity of each measurement point when elongation, while measuring secondary speed and torque；Wherein, in in-let dimple face
Radial direction pressure and velocity-stabilization, and radial 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, when by following equation to initial wind speed under initial propeller pitch angle each measuring point test data into
Row processing, calculating can obtain when initial wind speed turbine theory output work and turbine efficiency, specific formula for calculation under initial propeller pitch angle are as follows:
The equivalent stagnation pressure in model control volume in-let dimple face in test chamber are as follows:
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 in test chamber are as follows:
In formula,For in-let dimple face equivalent total temperature, K；T1For in-let dimple surface current body absolute temperature, K；V1For initial wind speed, m/
s；cpFor specific heat at constant pressure, J/ (kgK)；
Radial 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 in test chamber model control volume control of export face equivalent stagnation pressure are as follows:
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 control plane；For control of export surface current body speed average,V2i
For i-th of measuring point speed, m/s in control of export face；
Fluid flows through the equivalent pressure ratio of model control volume in test chamber are as follows:
The theoretical output work of model is calculated by the adiabatic expansion function that fluid flows through the control volume in test chamber, that is,
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 are as follows:
wf=Tn (9)
In formula, wfFor ram-air turbine output work, J；T is the runner torque that measurement obtains, N.m；N is the turbine that measurement obtains
Revolving speed, r/min；
Ram-air turbine efficiency are as follows:
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 regulating mechanism, which isWhen testing the initial wind speed by measuring instrument under difference propeller pitch angle each measurement point static pressure, static temperature and fluid velocity,
Secondary speed and torque are measured simultaneously；It repeats c. data processing section in this step and calculates content, when respectively obtaining initial wind speed
Turbine theory function and turbine efficiency under different propeller pitch angles；
Step 9: testing the turbine output and turbine efficiency when different wind speed under initial propeller pitch angle, specific measurement process are as follows:
A. change wind tunnel speed, maintaining turbine propeller pitch angle is the initial value of test requirements documentWind tunnel speed is according to test Reynolds number
It determines, wind tunnel speed variation range is V1~V2；
B. initial propeller pitch angle is maintainedIt is constant, adjust wind tunnel speed；Setting wind tunnel speed spacing value is required according to test Reynolds number
For Δ V；Adjusting wind tunnel speed respectively is V1+ΔV、V1+2ΔV、V1+3ΔV…...V2；It is first to test this respectively by measuring instrument
Under beginning propeller pitch angle when different wind speed each measurement point static pressure, static temperature and fluid velocity, while measuring secondary speed and torque；
C. data processing: each measuring point measurement result when according to different wind speed repeats in step 8 in the calculating of c. data processing section
Hold, respectively obtains when different wind speed turbine theory function and turbine efficiency under initial propeller pitch angle；
Step 10: turbine output and turbine efficiency, specific measurement process under difference propeller pitch angle when testing different wind speed are as follows:
A. change wind tunnel speed, require to adjust turbine propeller pitch angle to be a certain according to test Reynolds numberIt is worth and remains unchanged；It should
Value is located atBetween；Change wind tunnel speed by wind tunnel speed control device, requires to make wind-tunnel wind according to test Reynolds number
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, static temperature and fluid velocity of each measurement point when fast, while measuring secondary speed and torque；
B. change turbine propeller pitch angle, require control wind tunnel speed to be an air speed value and remain unchanged according to test Reynolds number；The wind
Speed value is located at V1~V2Between；By regulating device adjust turbine propeller pitch angle namely to It is tested respectively by measuring instrument each when different turbine propeller pitch angles under the wind tunnel speed
Static pressure, static temperature and the fluid velocity of measurement point, while measuring secondary speed and torque；
C. it data processing: according to each measuring point measurement result, repeats c. data processing section in step 8 and calculates content, respectively obtain
Turbine theory function and turbine efficiency under difference propeller pitch angle under same propeller pitch angle, when same wind speed when different wind speed；
By the static pressure in model in-let dimple face and control of export face, static temperature and fluid velocity in measurement test chamber, by wind
Hole test method expanded application realizes outer field flow in the ram-air turbine wind tunnel test methods based on far field compressible fluid
Dynamic internal fieldization processing, the theoretical output work of sub-scale model turbine can be sought using measurement parameter；The torque of binding model turbine and turn
Fast measurement result further seeks turbine efficiency, improves the energy using wind- tunnel investigation ram-air turbine power performance
Power.
2. a kind of ram-air turbine wind tunnel test test method according to claim 1, it is characterised in that:
Described in step 3,4 " seven-hole probe " refers to a kind of size, direction, stagnation pressure and static pressure that can obtain flowing velocity
Air measuring device, be inlaid in the stainless steel tube of a slightly larger outer diameter by 7 stainless steel capillaries, head in cone,
It is widely used in the flow measurement that low-speed wind tunnel tests various wide-angles.
3. a kind of ram-air turbine wind tunnel test test method according to claim 1, it is characterised in that:
Described in step 7,8 " measuring instrument " refers to pressure-measuring instrument, speed measuring Instrument and thermometric instruments.
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| CN111271179B (en) * | 2018-12-04 | 2022-07-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Power performance test method for ram air turbine |
| CN109737016B (en) * | 2019-01-30 | 2020-04-07 | 沈阳航空航天大学 | Mechanical efficiency measuring method of wind turbine aerodynamic performance experimental device |
| CN110686858B (en) * | 2019-11-07 | 2021-02-26 | 中国空气动力研究与发展中心 | Sound explosion measurement wind tunnel test data processing method |
| CN111122100A (en) * | 2019-12-10 | 2020-05-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Low-temperature testing method and system for emergency energy system |
| CN113432826B (en) * | 2020-03-23 | 2024-05-31 | 核工业理化工程研究院 | Method for measuring influence degree of bent pipe in different characteristic flow fields |
| CN112729853B (en) * | 2020-12-24 | 2023-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Resistance correction method for main engine air inlet of propeller aircraft |
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