CN113959729B - Turbine blade surface heat transfer coefficient testing method based on temperature-reduction thermal imaging - Google Patents
Turbine blade surface heat transfer coefficient testing method based on temperature-reduction thermal imaging Download PDFInfo
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- CN113959729B CN113959729B CN202111218268.9A CN202111218268A CN113959729B CN 113959729 B CN113959729 B CN 113959729B CN 202111218268 A CN202111218268 A CN 202111218268A CN 113959729 B CN113959729 B CN 113959729B
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- 238000012546 transfer Methods 0.000 title claims abstract description 73
- 238000012360 testing method Methods 0.000 title claims abstract description 23
- 238000001931 thermography Methods 0.000 title claims abstract description 11
- 239000011248 coating agent Substances 0.000 claims abstract description 43
- 238000000576 coating method Methods 0.000 claims abstract description 43
- 238000012805 post-processing Methods 0.000 claims abstract description 7
- 238000002310 reflectometry Methods 0.000 claims abstract description 6
- 230000007423 decrease Effects 0.000 claims description 18
- 239000000463 material Substances 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 7
- 238000004364 calculation method Methods 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims description 3
- 230000005855 radiation Effects 0.000 abstract description 6
- 238000013461 design Methods 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 abstract description 4
- 238000010438 heat treatment Methods 0.000 abstract description 4
- 230000007246 mechanism Effects 0.000 abstract description 3
- 230000004907 flux Effects 0.000 description 12
- 230000008859 change Effects 0.000 description 7
- 230000009467 reduction Effects 0.000 description 7
- 238000005259 measurement Methods 0.000 description 5
- 238000001816 cooling Methods 0.000 description 2
- 238000012937 correction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000035515 penetration Effects 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 230000009897 systematic effect Effects 0.000 description 2
- 239000013590 bulk material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 230000007704 transition Effects 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
- 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 turbine blade heat transfer coefficient testing method based on temperature drop thermal imaging, which comprises the steps of coating a layer of low-heat-conductivity coating on the outer surface of a turbine rotor blade, covering a layer of high-reflectivity surface coating on the surface of the turbine rotor blade, heating the surface of the coating by using laser pulse light source radiation, heating the outer surface of the coating to a plurality of degrees centigrade, then turning off the laser pulse light source, enabling the temperature of the surface of the coating to drop due to heat transfer mechanisms such as heat conduction, radiation and convection, recording the temperature drop condition of the surface of the coating by using a high-speed infrared camera, finally calculating and evaluating the temperature drop rate of each pixel of a camera picture by using a post-processing algorithm, calculating the heat transfer coefficient at each pixel position one by using a correlation formula between the temperature drop rate and the heat transfer coefficient, accurately measuring the heat transfer coefficient of the surface of the turbine rotor blade, and providing an advanced testing technology for the refinement design of a high-pressure turbine.
Description
Technical Field
The invention belongs to the technical field of fine testing of gas turbine engine impeller machinery, and particularly relates to a turbine blade surface heat transfer coefficient testing method based on temperature-reduction thermal imaging, which is used for accurately measuring the heat transfer characteristics of the turbine blade surface and providing an advanced testing technology for fine design of the impeller machinery.
Background
Modern high performance gas turbine engines have resulted in ever increasing high pressure turbine inlet temperatures. In order to ensure that the high-pressure turbine blade has optimal aerodynamic performance and heat transfer characteristics under various working conditions of the engine, so as to ensure the service life of the high-pressure turbine, it is important to clearly know the heat transfer coefficient of the surface of the turbine blade in the design process.
The heat flux sensor is the main means for measuring the heat transfer coefficient of the blade surface at present. The heat flux sensor is typically composed of one or more thin metal films or foils mounted on the surface of a bulk material with convective flow, and temperature, heat flux and heat transfer coefficient are measured by the temperature sensitive resistance of the sensor. The heat flux sensor is capable of providing high-accuracy measurements of high frequency signals, although the heat flux sensor is high frequency. However its spatial resolution is limited by the size of the thermal flux sensor. In addition, because the turbine rotor blade rotates at a high speed, the heat flux sensor is laid on the surface of the rotor blade, sensor signals are transmitted by means of a slip ring current collector and other complex signal output systems, the test precision of the heat transfer coefficient of the surface of the turbine blade is greatly reduced, the heat transfer coefficient test of the heat flux sensor on the surface of the turbine rotor blade is restricted, and the requirements of the high-pressure turbine on the fine design cannot be met.
Disclosure of Invention
Aiming at the defects and shortcomings in the prior art, the invention provides a turbine blade heat transfer coefficient testing method based on temperature reduction thermal imaging for testing the heat transfer coefficient of the surface of a turbine rotor blade through impeller machinery.
The invention aims to solve the technical problems, and adopts the following technical scheme:
the turbine blade surface heat transfer coefficient testing method based on temperature drop thermal imaging is characterized by at least comprising the following steps:
SS1, coating a coating with low thermal conductivity on the outer surface of a turbine rotor blade, and further covering the outer surface of the coating with a high-reflectivity surface coating;
SS2, utilizing a laser pulse light source to radiate and heat a coating on the outer surface of the turbine rotor blade, and turning off the laser pulse light source after the outer surface of the coating is heated to a temperature of a plurality of degrees centigrade;
SS3, adopting a high-speed infrared camera to record the temperature drop condition of the outer surface of the coating;
and SS4, calculating and evaluating the temperature drop rate of each pixel of the camera picture by using a post-processing algorithm, wherein the temperature drop rate calculation method of each pixel is as follows:
wherein,for the frame rate of the camera, m is the picture index, T' m For the temperature of each pixel of the current frame picture, T' m+1 The temperature of each pixel of the next frame of picture;
SS5, calculating the heat transfer coefficient at each pixel position one by utilizing an association relation between the temperature decrease rate Λ and the heat transfer coefficient alpha, and then obtaining the heat transfer coefficient at each part of the surface of the turbine rotor blade, wherein the association relation between the temperature decrease rate Λ and the heat transfer coefficient alpha is as follows:
α＝C′(Λ-Λ ref )+α n
wherein, lambda ref The reference value is the temperature drop rate, which is the temperature drop rate when no fluid flows across the surface. Alpha n Is the heat transfer coefficient of natural convection. C 'is a material characteristic parameter and a thermal conductivity coefficient including a reference value, and in the measurement, C' is measured by first passing through a temperature decrease rate (Λ - Λ ref ) And the linear relation of the heat transfer coefficient calculated by the Noval relation is calibrated. The method for calculating the heat transfer coefficient by the knoop-seel relation is as follows:
for laminar flow:
for turbulent flow:
the invention relates to a turbine blade surface heat transfer coefficient testing method based on temperature drop thermal imaging, which comprises the following working principles:
according to the first law of thermodynamics, for a flat plate object in an inflow environment, the temperature rise delta T of the surface of the flat plate 0 ＝T-T ∞ And the pulse energy q of the light source pulse Proportional, i.e.:
where T is the current temperature, T ∞ For ambient temperature, c=cρh is a proportionality constant comprising the specific heat and the density of the slab, C is the specific heat of the slab, ρ is the density of the slab, and h is the penetration depth of the laser pulse energy wave within the coating.
After the plate has been heated by the laser pulse source for a short period of time (typically after 50 milliseconds), a thermal quasi-plateau condition occurs at the plate surface, where the plate surface temperature is nearly constant. Using newton's law of cooling, the resulting differential equation can be written as:
wherein,for the rate of temperature change, ΔT is the current temperature change relative to the environment, +.>Heat flux of heat conduction part of flat plate material, alpha is flatPlate surface convective heat transfer coefficient:
the term represents the rate of temperature decrease of the surface of the plate, and +.>Is extracted from the measured temperature change. Let α be a constant, only when +.>In linear relation to Δt, Λ can be considered as a constant. This assumption applies in the case of small temperature variations present across the blade surface.
By setting α to zero, i.e. no incoming flow, no forced convection is used as a reference value, which is subtracted from the measurement of the incoming flow. The temperature drop in this case is controlled by natural convection and is transferred to the substrate by heat conduction:
the quantity related to the reference value is indexed by "ref", Λ ref For no incoming flow conditions the reference temperature drop rate,for reference of heat conduction heat flux, deltaT ref For reference temperature variation value alpha n Is the heat transfer coefficient of natural convection. The reference values are mainly used as corrections for reflections, uneven heating and different coating thicknesses of surrounding adjacent blades, reducing systematic errors due to conduction losses.
α＝C(Λ-Λ ref )+α n +f cond (α) (5)
Wherein the method comprises the steps off cond And (α) represents the heat conduction effect contained in the heat transfer coefficient. For small alpha values, the simulated predictions show +.>In a linear behavior, i.e. f cond (α) ≡α. By using the linear relation, the heat transfer coefficient can be converted by the temperature drop rate:
α＝C′(Λ-Λ ref )+α n (6)
wherein C 'is a material characteristic parameter and a thermal conductivity coefficient including a reference value, and C' is measured by first passing a temperature decrease rate (Λ - Λ ref ) And the linear relation of the heat transfer coefficient calculated by the Noval relation is calibrated. The method for calculating the heat transfer coefficient by the knoop-seel relation is as follows:
for laminar flow:
for turbulent flow:
by utilizing the principle, the coating with low heat conductivity is coated on the outer surface of the turbine rotor blade, and the coating with high reflectivity is coated on the outer surface of the turbine rotor blade, the coating on the surface of the turbine rotor blade is heated by the radiation of the laser pulse light source, so that the temperature of the outer surface of the coating rises by a plurality of degrees centigrade, then the laser pulse light source is turned off, the temperature of the surface of the coating is reduced due to heat transfer mechanisms such as heat conduction, radiation, convection and the like, then the temperature reduction condition is recorded by using a high-speed infrared camera, finally, the temperature reduction rate of each pixel of a camera picture is calculated and evaluated by using a post-processing algorithm, the heat transfer coefficient at each pixel position is calculated one by using the association relation between the temperature reduction rate and the heat transfer coefficient, and the heat transfer coefficient on the surface of the turbine rotor blade can be accurately measured, and an advanced test technology is provided for the refinement design of the high-pressure turbine.
Compared with the prior art, the turbine blade surface heat transfer coefficient testing method based on temperature-reducing thermal imaging has the following characteristics:
1) The scheme is simple and easy to realize: the surface of the blade is heated by transient light pulse, so that the outermost layer of the coating is heated by a plurality of degrees centigrade, pulse laser is turned off, and the temperature drop condition is recorded by using a high-speed infrared camera. The use of post-processing algorithms to achieve temperature decline rate and heat transfer coefficient correlation reduces instrument effort and provides high spatial resolution, short response time, and high temperature sensitivity.
2) The universality is good: the heat transfer coefficient testing method is not only suitable for heat transfer testing of the stator blade of the turbine, but also suitable for transition prediction of the rotor blade.
3) The test precision is high: the method effectively reduces the interference reflection and the change of the surface coating characteristics by evaluating the relative temperature difference and subtracting the reference measured value under the condition of no forced convection, and greatly improves the test precision.
Drawings
FIG. 1 is a schematic diagram showing the temperature relationship with time for different heat transfer coefficients.
FIG. 2 is a graph showing a calculated temperature decrease rate Λ for the same heat transfer coefficient, where Λ ref Is the rate of temperature decrease without forced convection (α=0).
FIG. 3 is a graph of temperature drop Λ - Λ extracted from the 80ms quasi-constant time range of FIG. 1 ref A quasi-linear relation diagram between the temperature drop rate and the heat transfer coefficient is accurately predicted.
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 some, but not all, embodiments of the invention and are intended to be illustrative of the invention and are not to be construed as limiting the invention. 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.
The invention relates to a turbine blade surface heat transfer coefficient testing method based on temperature-reduction thermal imaging, which mainly comprises the following steps:
firstly, coating a coating with low thermal conductivity on the outer surface of a turbine rotor blade, and further covering the outer surface of the coating with high reflectivity;
then, the laser pulse light source is utilized to radiate and heat the coating on the outer surface of the turbine rotor blade, and the laser pulse light source is turned off after the outer surface of the coating is heated to a plurality of degrees centigrade;
then, using a high-speed infrared camera to record the temperature drop of the outer surface of the coating;
thirdly, calculating and evaluating the temperature drop rate of each pixel of the camera picture by using a post-processing algorithm, wherein the temperature drop rate calculation method of each pixel is as follows:
wherein,for the frame rate of the camera, m is the picture index, T' m For the temperature of each pixel of the current frame picture, T' m+1 The temperature of each pixel of the next frame of picture;
finally, calculating the heat transfer coefficient at each pixel position one by utilizing an association relation between the temperature decrease rate Λ and the heat transfer coefficient alpha, and then obtaining the heat transfer coefficient at each part of the surface of the turbine rotor blade, wherein the association relation between the temperature decrease rate Λ and the heat transfer coefficient alpha is as follows:
α＝C’(Λ-Λ ref )+α n
wherein, lambda ref Reference for the rate of temperature decreaseThe value is the rate of temperature decrease when no fluid is flowing across the surface. Alpha n Is the heat transfer coefficient of natural convection. C 'is a material characteristic parameter and a thermal conductivity coefficient including a reference value, and in the measurement, C' is measured by first passing through a temperature decrease rate (Λ - Λ ref ) And the linear relation of the heat transfer coefficient calculated by the Noval relation is calibrated. The method for calculating the heat transfer coefficient by the knoop-seel relation is as follows:
for laminar flow:
for turbulent flow:
the invention relates to a turbine blade surface heat transfer coefficient testing method based on temperature drop thermal imaging, which comprises the following working principles:
according to the first law of thermodynamics, for a flat plate object in an inflow environment, the temperature rise delta T of the surface of the flat plate 0 ＝T-T ∞ And the pulse energy q of the light source pulse Proportional, i.e.:
where T is the current temperature, T ∞ For ambient temperature, c=cρh is a proportionality constant comprising the specific heat and the density of the slab, C is the specific heat of the slab, ρ is the density of the slab, and h is the penetration depth of the laser pulse energy wave within the coating.
After the plate has been heated by the laser pulse source for a short period of time (typically after 50 milliseconds), a thermal quasi-plateau condition occurs at the plate surface, where the plate surface temperature is nearly constant. Using newton's law of cooling, the resulting differential equation can be written as:
wherein,for the rate of temperature change, ΔT is the current temperature change relative to the environment, +.>Heat flux of the heat conduction part of the flat plate material, and alpha is the convective heat transfer coefficient of the flat plate surface:
the term represents the rate of temperature decrease of the surface of the plate, and +.>Is extracted from the measured temperature change. Let α be a constant, only when +.>In linear relation to Δt, Λ can be considered as a constant. This assumption applies in the case of small temperature variations present across the blade surface.
By setting α to zero, i.e. no incoming flow, no forced convection is used as a reference value, which is subtracted from the measurement of the incoming flow. The temperature drop in this case is controlled by natural convection and is transferred to the substrate by heat conduction:
the quantity related to the reference value is indexed by "ref", Λ ref For no incoming flow conditions the reference temperature drop rate,for reference of heat conduction heat flux, deltaT ref For reference temperature variation value alpha n Is the heat transfer coefficient of natural convection. The reference values are mainly used as corrections for reflections, uneven heating and different coating thicknesses of surrounding adjacent blades, reducing systematic errors due to conduction losses.
α＝C(Λ-Λ ref )+α n +f cond (α) (5)
Wherein the method comprises the steps off cond And (α) represents the heat conduction effect contained in the heat transfer coefficient. For small alpha values, the simulated predictions show +.>In a linear behavior, i.e. f cond (α) ≡α. By using the linear relation, the heat transfer coefficient can be converted by the temperature drop rate:
α＝C′(Λ-Λ ref )+α n (6)
wherein C 'is a material characteristic parameter and a thermal conductivity coefficient including a reference value, and C' is measured by first passing a temperature decrease rate (Λ - Λ ref ) And the linear relation of the heat transfer coefficient calculated by the Noval relation is calibrated.
By utilizing the principle, the coating with low heat conductivity is coated on the outer surface of the turbine rotor blade, and the coating with high reflectivity is coated on the outer surface of the turbine rotor blade, the coating is heated by the radiation of the laser pulse light source, so that the temperature of the outer surface of the coating rises by a plurality of degrees centigrade, then the laser pulse light source is turned off, the temperature of the surface of the coating is reduced due to heat transfer mechanisms such as heat conduction, radiation, convection and the like, then the temperature reduction condition is recorded by using a high-speed infrared camera, finally the temperature reduction rate of each pixel of the camera is calculated and evaluated by using a post-processing algorithm, the heat transfer coefficient at each pixel position is calculated one by using the association relation between the temperature reduction rate and the heat transfer coefficient, and the heat transfer coefficient of the turbine rotor blade surface can be accurately measured, so that an advanced test technology is provided for the refinement design of the high-pressure turbine.
FIG. 1 shows the temperature versus time for different heat transfer coefficients; FIG. 2 shows a calculated temperature decrease rate Λ, Λ for the same heat transfer coefficient ref A temperature drop rate of no forced convection (α=0); FIG. 3 is a graph of temperature drop Λ - Λ extracted from the 80ms quasi-constant time range of FIG. 1 ref A quasi-linear relationship between the temperature drop rate and the heat transfer coefficient is accurately predicted.
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 (1)
1. The turbine blade surface heat transfer coefficient testing method based on temperature drop thermal imaging is characterized by at least comprising the following steps:
SS1, coating a coating with low thermal conductivity on the outer surface of a turbine rotor blade, and further covering the outer surface of the coating with a high-reflectivity surface coating;
SS2, utilizing a laser pulse light source to radiate and heat a coating on the outer surface of the turbine rotor blade, and turning off the laser pulse light source after the outer surface of the coating is heated to a temperature of a plurality of degrees centigrade;
SS3, adopting a high-speed infrared camera to record the temperature drop condition of the outer surface of the coating;
and SS4, calculating and evaluating the temperature drop rate of each pixel of the camera picture by using a post-processing algorithm, wherein the temperature drop rate calculation method of each pixel is as follows:
wherein,for the frame rate of the camera, m is the picture index, T' m For the temperature of each pixel of the current frame picture, T' m+1 The temperature of each pixel of the next frame of picture;
SS5, calculating the heat transfer coefficient at each pixel position one by utilizing an association relation between the temperature decrease rate Λ and the heat transfer coefficient alpha, and then obtaining the heat transfer coefficient at each part of the surface of the turbine rotor blade, wherein the association relation between the temperature decrease rate Λ and the heat transfer coefficient alpha is as follows:
α＝C′(Λ-Λ ref )+α n
wherein, lambda ref Is the reference value of the temperature drop rate, is the temperature drop rate when no fluid flows through the surface, alpha n Is the heat transfer coefficient of natural convection, C 'is the material characteristic parameter and the heat transfer coefficient including the reference value, and C' is measured by first passing the temperature decrease rate (Λ - Λ ref ) The method for calculating the heat transfer coefficient by the Noval relation is obtained by calibrating the linear relation of the heat transfer coefficient calculated by the Noval relation, and comprises the following steps:
for laminar flow:
for turbulent flow:
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998005949A1 (en) * | 1996-07-31 | 1998-02-12 | Siemens Aktiengesellschaft | Method and device for testing substrate coatings for delamination, in particular vacuum plasma sprayed coatings on gas turbine blades |
| US7040805B1 (en) * | 2004-05-24 | 2006-05-09 | The United States Of America As Represented By The Secretary Of The Air Force | Method of infrared thermography |
| CN105972441A (en) * | 2016-07-04 | 2016-09-28 | 新疆电力建设调试所 | Method for detecting leakage from heat distribution pipeline with heat preservation structure |
| CN110954575A (en) * | 2019-12-07 | 2020-04-03 | 北京航空航天大学 | Test system for convective heat transfer coefficient of rotating disc |
| CN111207903A (en) * | 2020-03-02 | 2020-05-29 | 北京空天技术研究所 | Transition measuring method suitable for sub-transonic wind tunnel |
| CN112162005A (en) * | 2020-08-27 | 2021-01-01 | 湘潭大学 | Method and device for detecting thermal insulation effect of thermal barrier coating of turbine blade |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6585408B2 (en) * | 2001-07-30 | 2003-07-01 | General Electric Company | Method and apparatus for measuring local heat transfer distribution on a surface |
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998005949A1 (en) * | 1996-07-31 | 1998-02-12 | Siemens Aktiengesellschaft | Method and device for testing substrate coatings for delamination, in particular vacuum plasma sprayed coatings on gas turbine blades |
| US7040805B1 (en) * | 2004-05-24 | 2006-05-09 | The United States Of America As Represented By The Secretary Of The Air Force | Method of infrared thermography |
| CN105972441A (en) * | 2016-07-04 | 2016-09-28 | 新疆电力建设调试所 | Method for detecting leakage from heat distribution pipeline with heat preservation structure |
| CN110954575A (en) * | 2019-12-07 | 2020-04-03 | 北京航空航天大学 | Test system for convective heat transfer coefficient of rotating disc |
| CN111207903A (en) * | 2020-03-02 | 2020-05-29 | 北京空天技术研究所 | Transition measuring method suitable for sub-transonic wind tunnel |
| CN112162005A (en) * | 2020-08-27 | 2021-01-01 | 湘潭大学 | Method and device for detecting thermal insulation effect of thermal barrier coating of turbine blade |
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