CN113959728B - Temperature-reduction thermal imaging-based testing method for transition of boundary layer on surface of impeller mechanical blade - Google Patents
Temperature-reduction thermal imaging-based testing method for transition of boundary layer on surface of impeller mechanical blade Download PDFInfo
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- 230000007704 transition Effects 0.000 title claims abstract description 52
- 238000012360 testing method Methods 0.000 title claims abstract description 25
- 238000001931 thermography Methods 0.000 title claims abstract description 15
- 239000011248 coating agent Substances 0.000 claims abstract description 27
- 238000000576 coating method Methods 0.000 claims abstract description 27
- 238000012546 transfer Methods 0.000 claims abstract description 20
- 230000001052 transient effect Effects 0.000 claims abstract description 20
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 238000002310 reflectometry Methods 0.000 claims abstract description 4
- 238000010586 diagram Methods 0.000 claims description 14
- 239000012530 fluid Substances 0.000 claims description 13
- 238000000034 method Methods 0.000 claims description 12
- 238000004364 calculation method Methods 0.000 claims description 6
- 239000007787 solid Substances 0.000 claims description 5
- 230000035515 penetration Effects 0.000 claims description 3
- 208000012322 Raynaud phenomenon Diseases 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 6
- 238000005516 engineering process Methods 0.000 abstract description 5
- 238000012805 post-processing Methods 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 37
- 238000010998 test method Methods 0.000 description 7
- 230000000694 effects Effects 0.000 description 4
- 230000003287 optical effect Effects 0.000 description 4
- 238000005286 illumination Methods 0.000 description 3
- 238000003384 imaging method Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 239000011247 coating layer Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000012212 insulator Substances 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000917 particle-image velocimetry Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000001757 thermogravimetry curve Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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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
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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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
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/20—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity
Abstract
The invention provides a temperature-reduction thermal imaging-based impeller mechanical blade surface boundary layer transition testing method, which comprises the steps of firstly coating a layer of coating with low heat conductivity and high reflectivity on the surface of an impeller mechanical blade, and heating the surface of the blade by transient light pulse (generated by a flash lamp or laser, for example) to heat the outermost layer of the coating. After the light source is turned off, a high-speed infrared camera is used for detecting the temperature drop of each pixel. The temperature drop is evaluated in a post-processing algorithm to obtain a positive ratio with the heat transfer coefficient and the wall shear stress, and the laminar flow, the transition flow and the turbulent flow characteristics of the surface boundary layer of the impeller mechanical blade are accurately captured, so that an advanced test technology is provided for the fine design of the impeller machinery.
Description
Technical Field
The invention relates to the technical field of gas turbine engine impeller machinery refinement test, in particular to a boundary layer transition test method based on temperature-reduction thermal imaging, which is used for accurately capturing boundary layer laminar flow, transition and turbulence characteristics of the surface of an impeller machinery blade and provides an advanced test technology for the impeller machinery refinement design.
Background
Modern gas turbine engines have to be optimally designed for the aerodynamic performance of the impeller machine blades in the design phase in order to achieve as high efficiency as possible. In order to design the optimal aerodynamic layout of the blade, it is important to know the boundary layer laminar flow, transition and turbulent flow states of all positions on the surface of the blade under all working conditions in detail.
In order to detect transition behavior of a blade surface boundary layer, many measurement techniques have been developed in the prior art. The boundary layer transition method based on the surface thermal film test is widely used. The advantage of a thermal film sensor is that the data acquisition frequency is high, so transient behavior in the fluid flow can be detected. However, the disadvantages are also evident, because of the contact test, interference with the boundary layer, and difficulty in conducting boundary layer condition measurements on the surface of the turbomachine rotor blade. In order to minimize interference with boundary layer flow, several non-contact boundary layer optical testing methods with high spatial resolution have also been developed in the prior art. For example, OI et al use particle image velocimetry to detect laminar flow turbulence after laminar flow separation of the blades. Bouchardy and Durand, crawford et al, richter and Schulein utilize infrared thermal imaging to measure the adiabatic temperature distribution of the blade surface and determine boundary layer transition regions. However, the two optical methods have the main defects that the surface of the measured blade is always influenced by the reflection and refraction of surrounding blades, and the viewing angle is highly dependent, so that the influence of surface temperature change caused by boundary layer transition is hidden, larger uncertainty is brought to boundary layer test, laminar flow, transition and turbulent flow characteristics of the surface boundary layer of the impeller mechanical blade cannot be accurately captured, and the fine design of the impeller machinery cannot be met.
Disclosure of Invention
Aiming at the problems existing in the prior art, the invention provides a temperature-reduction thermal imaging-based method for testing the boundary layer transition of the surface of the impeller mechanical blade, which combines the characteristics of a non-contact optical method, aims at the characteristics of laminar flow, transition and turbulence of the boundary layer of the surface of the impeller mechanical blade, and simultaneously considers the large difference of heat transfer coefficients of the laminar flow and the turbulence. And then, after the transient light pulse light source is turned off, the temperature of the surface of the coating is reduced, and a high-speed infrared camera is used for detecting the temperature reduction condition of each pixel. The temperature drop is evaluated in a post-processing algorithm to obtain a positive ratio with the heat transfer coefficient and the wall shear stress, and the laminar flow, the transition flow and the turbulent flow characteristics of the surface boundary layer of the impeller mechanical blade are accurately captured, so that an advanced test technology is provided for the fine design of the impeller machinery.
The invention aims to solve the technical problems, and adopts the following technical scheme:
the method for testing transition of the boundary layer on the surface of the impeller mechanical blade based on temperature drop thermal imaging is characterized by at least comprising the following steps:
SS1, coating a coating with low heat conductivity and high reflectivity on the outer surface of an impeller mechanical blade;
SS2, heating a coating on the outer surface of the impeller mechanical blade by using a transient light pulse light source, and turning off the transient light pulse light source after the temperature of the outer surface of the coating rises by a plurality of degrees centigrade;
SS3, detecting the temperature drop condition of each pixel by using a high-speed infrared camera, and calculating the temperature drop rate Λ of each pixel by using the following calculation formula:
wherein,for the frame rate of the camera, m is the picture index, T' m For the temperature of the current frame picture, T' m+1 The temperature of the next frame of picture;
SS4 calculating the temperature decrease rate Λ value of each pixel by using the calculation in step SS3 (Λ - Λ ref ) A value, wherein Λ ref Represents the rate of temperature drop with no flow of the solid wall surface, plotted (Λ - Λ ref ) The distribution diagram of the value along the wing chord direction of the impeller mechanical blade can obtain the flow transition characteristic of the boundary layer on the surface of the impeller mechanical blade, and the distribution diagram along the wing chord direction (Λ - Λ of the blade ref ) The sudden rise position of the value is the transition position.
Preferably, the turbomachine blade is a gas turbine engine compressor stator blade, a turbine stator blade, a compressor rotor blade, or a turbine rotor blade.
Preferably, in step SS2, the transient light pulse light source may be a flash lamp or a transient laser.
Preferably, in step SS2, the coating outer surface is heated to no more than 10 degrees celsius.
The invention relates to a temperature-reduction thermal imaging-based impeller mechanical blade surface boundary layer transition test method, which adopts an ideal adiabatic simplified model to establish an association equation of wall shear stress and heat transfer coefficient, and specifically comprises the following steps:
temperature rise (T' =t-T) of the coating on the surface of the impeller machinery blade after transient light pulse heating ∞ ) The method comprises the following steps:
wherein q pulse 、c e And ρ e The energy density, specific heat and coating density of the transient light pulse are respectively indicated, while h indicates the penetration depth of the transient light pulse. T' represents the temperature rise, T represents the current temperature, T ∞ Representing the temperature of the incoming flow, i.e. the ambient temperature, T' 0 Representing the initial value of the temperature rise after heating.
Heat flux from heated surface to airflow according to newton's law of coolingGiven by the formula:
where α represents the heat transfer coefficient.
Thus, the differential equation for an ideal adiabatic reduction model can be written as:
the solution can be obtained:
wherein T' (T) represents the temperature rise over time.
In the case of ideal insulation, the heat of the incoming fluid can be expressed as:
α＝c e ρ e hΛ (5)
where Λ is the rate of temperature decrease.
After thermal excitation, the temperature drop rate Λ is constant and can be determined by the following equation:
wherein,for the frame rate of the camera, m is the picture index, T' m For the temperature of the current frame picture, T' m+1 The temperature for the next frame picture is approximated by expanding its number of steps.
For Plantt number P r Subsonic flow of approximately 1, reynolds analog factor s is approximately constant:
wherein S is t For the Stanton number, c f Indicating the coefficient of friction of the fluid, coefficient of friction c f The calculation formula of (2) is as follows:
τ w ρ is the density of the fluid, U, as wall shear stress ∞ Is the free flow velocity of the fluid.
Heat transfer coefficient alpha and stentNumber of trails S t The relation of (2) is that
c p Is the isobaric specific heat capacity of the fluid.
Equations (5), (7), (8) and (9) may be combined into the following expression:
this indicates that if the coating approximates an ideal insulator, the wall shear stress τ w The heat transfer coefficient alpha and the temperature drop rate lambda are in direct proportion.
Using the measured Λ value, a (Λ - Λ ref ) And (3) drawing a distribution diagram along the chord direction, and obtaining the transition characteristic of the flow. Because of the temperature drop rate Λ and the wall shear stress tau w In direct proportion (equation (10)), the wall shear stress is one of the usual parameters for determining transition characteristics, and therefore (Λ - Λ) ref ) The distribution of the values can be directly used for judging the transition characteristics. Wherein Λ ref Representing the rate of temperature drop at which the solid wall surface is free of flow (i.e., heat transfer coefficient α=0), based on this, interference effects such as variations in thermal coating thickness and uneven illumination can be reduced while maintaining a linear relationship between the rate of temperature drop and heat transfer coefficient. When (Λ - Λ ref ) And when the value rises suddenly, the position is represented as a transition position of the boundary layer.
Compared with the prior art, the temperature-reduction thermal imaging-based impeller mechanical blade surface boundary layer transition testing method has the following characteristics:
1) The scheme is simple and easy to realize: by adopting the temperature drop method, only transient light pulses (generated by a flash lamp or laser for example) are used for heating the coating on the surface of the impeller mechanical blade, so that the temperature of the outer surface of the coating is raised by a plurality of degrees centigrade, and continuous heating is not required.
2) The universality is good: the boundary layer transition test technology is suitable for the transition test of the compressor and the turbine stator blade and is also suitable for the transition prediction of the rotor blade.
3) The test precision is high: the heat transfer coefficient is directly related to the shearing stress of the wall surface, so that the effect of the non-uniformity of the heat pulse is weakened, the reflection influence of surrounding blades is greatly reduced, and the testing precision is greatly improved.
Drawings
Fig. 1 is a schematic diagram illustrating an application of the surface boundary layer transition testing method of the present invention to an airfoil of an impeller mechanical blade.
Fig. 2 is a schematic diagram of boundary layer transition characteristics obtained based on the temperature-reduced thermal imaging method according to the present invention at different reynolds numbers.
Fig. 3 is a schematic diagram of boundary layer transition characteristics obtained based on the temperature drop imaging method of the present invention under different attack angles.
Fig. 4 is a comparison diagram of measurement transition precision of the present invention and other existing boundary layer transition test methods.
Reference numerals illustrate:
1-transient light pulse light source, 2-high-speed infrared camera and 3-impeller mechanical blade airfoil.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention become more apparent, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. The described embodiments are intended to be illustrative of the invention and should not be construed as limiting the invention in any way. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Fig. 1 is a schematic diagram illustrating an application of the surface boundary layer transition test method of the present invention to an airfoil of an impeller mechanical blade. The invention relates to a temperature-reduction thermal imaging-based impeller mechanical blade surface boundary layer transition test method, which at least comprises the following steps:
first, the outer surface of the impeller mechanical blade 3 is coated with a coating layer having low thermal conductivity and high reflectivity; then, a transient light pulse light source 1 (for example, generated by a flash lamp or laser) is adopted to heat the coating on the outer surface of the impeller mechanical blade 3, and the transient light pulse light source 1 is turned off after the temperature of the outer surface of the coating rises by a plurality of degrees centigrade; thereafter, the temperature drop condition of each pixel in the coating layer is detected using the high-speed infrared camera 2, and the temperature drop rate Λ of each pixel is calculated using the following calculation formula:
wherein,for the frame rate of the camera, m is the picture index, T' m For the temperature of the current frame picture, T' m+1 Is the temperature of the next frame picture.
Using the measured Λ value, a (Λ - Λ ref ) And (3) drawing a distribution diagram along the chord direction, and obtaining the transition characteristic of the flow. Because of the temperature drop rate Λ and the wall shear stress tau w In direct proportion (equation (10)), the wall shear stress is one of the usual parameters for determining transition characteristics, and therefore (Λ - Λ) ref ) The distribution of the values can be directly used for judging the transition characteristics. Wherein Λ ref Representing the rate of temperature drop at which the solid wall surface is free of flow (i.e., heat transfer coefficient α=0), based on this, interference effects such as variations in thermal coating thickness and uneven illumination can be reduced while maintaining a linear relationship between the rate of temperature drop and heat transfer coefficient. When (Λ - Λ ref ) And when the value rises suddenly, the position is represented as a transition position of the boundary layer.
The invention relates to a temperature drop thermal imaging-based impeller mechanical blade surface boundary layer transition test method, which adopts an ideal adiabatic simplified model to establish an association equation of wall shear stress and heat transfer coefficient.
Specifically:
the coating on the outer surface of the impeller machinery blade is heated by laser pulse and then is heated up (T' =t-T ∞ ) The method comprises the following steps:
wherein q pulse 、c e And ρ e The energy density, specific heat and coating density of the transient light pulse are respectively indicated, while h indicates the penetration depth of the transient light pulse. T' represents the temperature rise, T represents the current temperature, T ∞ Representing the temperature of the incoming flow, i.e. the ambient temperature, T' 0 Representing the initial value of the temperature rise after heating.
According to newton's law of cooling, the heat flux from the heated surface to the air flow is given by:
where α represents the heat transfer coefficient.
Thus, the differential equation for an ideal adiabatic reduction model can be written as:
the solution can be obtained:
wherein T' (T) represents the temperature rise over time.
In the case of ideal insulation, the heat of the incoming fluid can be expressed as:
α＝c e ρ e hΛ (5)
where Λ is the rate of temperature decrease.
After thermal excitation, Λ is a constant, which can be determined by:
wherein,is the frame rate of the camera, m is the picture index, T' m For the temperature of the current frame picture, T' m+1 The temperature for the next frame picture is approximated by expanding its number of steps.
For Plantt number P r Subsonic flow of approximately 1, reynolds analog factor s is approximately constant:
wherein S is t Is the Stangton number, c f Indicating the coefficient of friction of the fluid, coefficient of friction c f Is calculated as
τ w ρ is the density of the fluid, U, as wall shear stress ∞ As the free flow velocity of the fluid.
Heat transfer coefficient alpha and ston number S t The relation of (2) is that
c p Is the isobaric specific heat capacity of the fluid.
Equations (5), (7), (8) and (9) can be combined into the following expression
This indicates that if the coating approximates an ideal insulator, the wall shear stress τ w The heat transfer coefficient alpha and the temperature drop rate lambda are in direct proportion. Equation (6) is used to calculate each pixel of the continuous thermogram and to relate it to α and τ w And (5) directly associating. Λ and absolute temperature water, by definitionAnd is irrelevant. The non-uniformity of the initial heat pulse is therefore not important and the reflection of surrounding blades can be greatly reduced by using the proposed analysis method, thereby greatly improving the test accuracy.
Using the measured Λ value, a (Λ - Λ ref ) And drawing a chord-wise distribution diagram of the temperature drop value, so that the flow transition characteristic can be obtained. Because of the temperature drop rate Λ and the wall shear stress tau w In direct proportion (equation (10)), the wall shear stress is one of the usual parameters for determining transition characteristics, and therefore (Λ - Λ) ref ) The distribution of the values can be directly used for judging the transition characteristics. Wherein Λ ref Representing the rate of temperature drop at which the solid wall surface is free of flow (i.e., heat transfer coefficient α=0), based on this, interference effects such as variations in thermal coating thickness and uneven illumination can be reduced while maintaining a linear relationship between the rate of temperature drop and heat transfer coefficient. When (Λ - Λ ref ) And when the value rises suddenly, the position is represented as a transition position of the boundary layer.
FIGS. 2 and 3 are graphs showing the temperature drop imaging (Λ - Λ) based on the present invention at different Reynolds numbers and different angles of attack ref ) And (5) obtaining transition characteristics of the boundary layer. Fig. 4 compares the different boundary layer transition test technologies, and currently, it is generally considered that the thermal film test boundary layer is the most accurate. And thus is based thereon. It can be seen that the boundary layer optical test method (I-I 1 ) The invention provides a temperature drop imaging (lambda-lambda based ref ) The obtained boundary layer transition is more accurate.
The object of the present invention is fully effectively achieved by the above-described embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, those illustrated in the drawings and described in the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the scope of the appended claims.
Claims (3)
1. The method for testing transition of the boundary layer on the surface of the impeller mechanical blade based on temperature drop thermal imaging is characterized by at least comprising the following steps:
SS1, coating a coating with low heat conductivity and high reflectivity on the outer surface of an impeller mechanical blade;
SS2, heating a coating on the outer surface of the impeller mechanical blade by using a transient light pulse light source, and turning off the transient light pulse light source after the temperature of the outer surface of the coating rises by a plurality of degrees centigrade but the temperature rise range is not more than 10 degrees centigrade;
SS3, detecting the temperature drop condition of each pixel by using a high-speed infrared camera, and calculating the temperature drop rate Λ of each pixel by using the following calculation formula:
wherein,for the frame rate of the camera, m is the picture index, T ′ m T is the temperature of the current frame picture ′ m+1 The temperature of the next frame of picture;
SS4 calculating the temperature decrease rate Λ value of each pixel by using the calculation in step SS3 (Λ - Λ ref ) A value, wherein Λ ref Represents the rate of temperature drop at which the solid wall surface is free of flow and the heat transfer coefficient α is 0, plotted (Λ - Λ ref ) Distribution diagram of values along the airfoil chord direction of the impeller mechanical blade based on wall shear stress tau w Is a judging parameter of transition characteristics, and the temperature drop rate lambda and the wall shear stress tau w The ratio of the two formulas satisfies the proportional relation:
wherein, c e And ρ e Respectively representing specific heat and density of the coating, alpha represents the heat transfer coefficient of the fluid, h represents the penetration depth of transient light pulses, s represents the Raynaud analog factor, U ∞ Indicating the free flow velocity of the fluid,
utilizing (Λ - Λ) ref ) Obtaining a flow transition characteristic of a boundary layer of a surface of an impeller mechanical blade from a distribution diagram of values along an airfoil chord direction of the impeller mechanical blade, wherein the distribution diagram is a distribution diagram along the airfoil chord direction (Λ - Λ ref ) The abrupt position of the value is the transition position.
2. The temperature-dropping thermal imaging-based method for transition testing of boundary layer on surface of impeller mechanical blade according to claim 1, wherein the impeller mechanical blade is a gas turbine engine compressor stator blade, a turbine stator blade, a compressor rotor blade or a turbine rotor blade.
3. The method for transition testing of the boundary layer of the surface of the impeller mechanical blade based on temperature-reducing thermal imaging as set forth in claim 1, wherein in step SS2, the transient light pulse light source is a flash lamp or a transient laser.
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