CN113586166B - Turbine blade with kerosene cooling micro-channel - Google Patents

Abstract

The invention relates to a turbine blade with kerosene cooling micro-channel, comprising: the cooling micro-channel structure comprises a turbine blade body and a cooling micro-channel arranged in the turbine blade body, wherein the turbine blade body comprises a blade top, a blade root and a blade body positioned between the blade top and the blade root, the blade body is formed by enclosing a blade pressure surface and a blade suction surface, and a blade leading edge and a blade trailing edge are respectively formed at the joint of the blade pressure surface and the blade suction surface; the inlet and the outlet of the cooling micro-channel are both arranged on the blade top, wherein the inlet is close to the leading edge of the blade, and the outlet is close to the trailing edge of the blade; the cooling microchannel comprises an inlet flow dividing section, a first flow dividing branch, a second flow dividing branch, a first transition section, a second transition section, a first confluence branch, a second confluence branch and an outlet confluence section. Compared with a channel with a larger diameter, the cooling micro-channel arranged on the turbine blade has the advantages of stronger convection heat exchange process, more obvious heat exchange effect and better cooling effect on the turbine blade.

Description

A turbine blade with kerosene cooling microchannels

technical field

The invention belongs to the field of turbine-based combined cycle engines, in particular to a turbine blade with kerosene cooling microchannels.

Background technique

With the continuous development of aerospace technology and the needs of national defense, higher and higher requirements are put forward for the performance of aerospace engines, and blades are an important part of the engine. According to the analysis of the Carnot cycle, the increase of the thrust of the gas turbine engine largely depends on the increase of the total temperature before the turbine. According to the calculation, when the temperature of the front end of the turbine increases by 55°C, the engine thrust can be increased by about 55°C under the condition of the same engine size 10%. In order to meet the increasingly high temperature working environment in front of the turbine, the cooling structure design of the blades is also more complicated. Higher requirements are placed on the cooling structure design of turbine blades.

In order to obtain higher thrust-to-weight ratio and thermal efficiency, modern aviation gas turbine engines continuously increase the turbine inlet temperature. At present, the turbine inlet temperature has far exceeded the melting point temperature of the blade material, and complex cooling technology must be adopted to maintain the normal operation of the turbine blades. Considering the cooling effect and the efficiency of the engine, the cooling of the turbine blades of the engine mainly has the following requirements: (1) Minimize the amount of cooling medium; (2) Improve the cooling efficiency; (3) Make the temperature of the cooling blades as uniform as possible.

Common blade cooling methods include internal convection cooling and external film cooling. For the internal convection cooling method, cooling microchannels of conventional size are mostly used, and cooling gas or liquid is introduced into the cooling microchannels to achieve cooling of the blades. The cooling microchannels of regular size have very limited cooling effect on the leading edge of the blade, and the cooling is not uniform.

SUMMARY OF THE INVENTION

In order to solve the above problems in the prior art, the present invention provides a turbine blade with kerosene cooling microchannels. The technical problem to be solved by the present invention is realized by the following technical solutions:

The present invention provides a turbine blade with kerosene cooling microchannels, comprising: a turbine blade body and a cooling microchannel disposed inside the turbine blade, wherein,

The turbine blade body includes a blade tip, a blade root, and a blade body located between the blade tip and the blade root. The blade body is surrounded by a blade pressure surface and a blade suction surface. The connection between the pressure surface and the suction surface of the blade respectively forms the leading edge of the blade and the trailing edge of the blade;

Both the inlet and the outlet of the cooling microchannel are arranged on the blade tip, wherein the inlet is close to the leading edge of the blade, and the outlet is close to the trailing edge of the blade;

The cooling microchannel includes an inlet branching section, a first branching branch, a second branching branch, a first transition section, a second transition section, a first converging branch, a second converging branch and an outlet converging section, wherein,

The first branching branch, the first converging branch and the first transition section are all set according to the curvature of the suction surface of the blade; the second branching branch, the second converging branch and all the The second transition section is set according to the curvature of the blade pressure surface;

The first end of the inlet splitting section is connected to the inlet, the second end is respectively connected to the first splitting branch and the second splitting branch; the first end of the outlet confluence section is connected to the outlet, The second ends are respectively connected with the first confluence branch and the second confluence branch;

The first branch branch and the first confluence branch are respectively connected to the first transition section through a plurality of fluid microchannels; the second branch branch and the second confluence branch pass through a plurality of the A fluidic microchannel is connected to the second transition section.

In an embodiment of the present invention, the first branch branch, the second branch branch, the first converging branch and the second converging branch are all located at positions close to the blade tip,

Both the first transition section and the second transition section are located near the blade root.

In an embodiment of the present invention, both the inlet split section and the outlet confluence section are in the shape of a truncated cone, the diameter of the top surface of the truncated truncated cone is 1.5-2 mm, the diameter of the bottom surface is 4-4.5 mm, and the diameter of the circular truncated cone is larger. One end is connected with the inlet or the outlet as the first end.

In an embodiment of the present invention, a plurality of the fluid microchannels are vertically arranged along the blade height direction of the turbine blade body, and the fluid microchannels have a diameter of 0.8mm-1.2mm and a height of 20-25mm .

In an embodiment of the present invention, the spacing of several of the fluid microchannels connected to the first transition section is 2.5-3 times the diameter of the fluid microchannels.

In an embodiment of the present invention, the spacing of several of the fluid microchannels connected to the second transition section is 2.5-4 times the diameter of the fluid microchannels.

In an embodiment of the present invention, the first branch branch, the second branch branch, the first transition section, the second transition section, the first confluence branch, and the first flow branch The diameter of the two confluence branches is 1.5-3 times the diameter of the fluid microchannel.

In one embodiment of the present invention, the distance between the fluid microchannel near the leading edge of the blade and the leading edge of the blade is 3-6 times the diameter of the fluid microchannel.

Compared with the prior art, the beneficial effects of the present invention are:

1. The turbine blade with kerosene cooling microchannel of the present invention, the cooling microchannel provided is close to the leading edge of the blade and is evenly distributed along the blade pressure surface and the blade suction surface, and the heat transfer coefficient of the microchannel increases significantly as the diameter decreases. Compared with the larger diameter channel, the boundary layer of the microchannel is thinner, the convective heat transfer process is stronger, the heat transfer effect is more obvious, and the cooling effect on the turbine blades is better.

2. In the turbine blade with kerosene cooling microchannels of the present invention, the surface heat transfer coefficient of the cooling microchannels provided is significantly higher than that of the conventional single cooling channel, and the increase of heat transfer increases with the increase of kerosene flow rate. Continuously increasing, can significantly increase the heat transfer, thereby reducing the thermal load on the blade surface.

3. The turbine blade with kerosene cooling micro-channels of the present invention can effectively reduce the blade surface temperature by using the cooling micro-channel cooling, ensure the normal operation of the aerospace engine, and improve the efficiency and thrust-weight ratio of the turbine engine.

The above description is only an overview of the technical solutions of the present invention, in order to be able to understand the technical means of the present invention more clearly, it can be implemented according to the content of the description, and in order to make the above and other purposes, features and advantages of the present invention more obvious and easy to understand , the following specific preferred embodiments, and in conjunction with the accompanying drawings, are described in detail as follows.

Description of drawings

1 is a perspective perspective view of a turbine blade with kerosene cooling microchannels provided by an embodiment of the present invention;

2 is a schematic structural diagram of a turbine blade body provided by an embodiment of the present invention;

3 is a three-view diagram of a turbine blade with kerosene cooling microchannels provided by an embodiment of the present invention;

4 is a schematic structural diagram of a cooling microchannel provided by an embodiment of the present invention;

5 is a temperature distribution diagram of a blade pressure surface and a blade suction surface provided by an embodiment of the present invention;

6 is a schematic structural diagram of a single cooling channel of a conventional size provided by an embodiment of the present invention;

7 is a temperature distribution diagram at the middle diameter of a blade of a single cooling channel and a cooling microchannel of a conventional size provided by an embodiment of the present invention;

FIG. 8 is a streamline diagram of a fluid in a cooling microchannel provided by an embodiment of the present invention;

9 is a graph of the average surface heat transfer coefficient of a single cooling channel and a cooling microchannel of a conventional size provided by an embodiment of the present invention;

10 is a schematic diagram of a turbine blade cooling experimental device provided by an embodiment of the present invention;

11 is a simulation and experimental error diagram of the dimensionless value of the temperature rise of kerosene at the inlet and outlet of the cooling microchannel provided by the embodiment of the present invention;

FIG. 12 is a relationship diagram of kerosene temperature rise, heat exchange and kerosene flow rate in cooling microchannels provided by an embodiment of the present invention.

Detailed ways

In order to further illustrate the technical means and effects adopted by the present invention to achieve the predetermined purpose of the invention, a turbine blade with kerosene cooling micro-channels proposed according to the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

The foregoing and other technical contents, features and effects of the present invention can be clearly presented in the following detailed description of the specific implementation with the accompanying drawings. Through the description of the specific embodiments, the technical means and effects adopted by the present invention to achieve the predetermined purpose can be more deeply and specifically understood. However, the accompanying drawings are only for reference and description, and are not used for the technical description of the present invention. program is restricted.

Example 1

Please refer to FIG. 1 and FIG. 2 in conjunction. FIG. 1 is a perspective perspective view of a turbine blade with kerosene cooling microchannels provided by an embodiment of the present invention; FIG. 2 is a schematic structural diagram of a turbine blade body provided by an embodiment of the present invention. . As shown in the figure, the turbine blade with kerosene cooling microchannels of this embodiment includes a turbine blade body 10 and a cooling microchannel 20 disposed inside the turbine blade body 10 .

As shown in FIG. 2 , the turbine blade body 10 includes a blade tip 101 , a blade root 102 and a blade body located between the blade tip 101 and the blade root 102 , and the blade body is surrounded by a blade pressure surface 103 and a blade suction surface 104 , the blade leading edge 105 and the blade trailing edge 106 are respectively formed at the connection between the blade pressure surface 103 and the blade suction surface 104 .

In this embodiment, the height of the turbine blade body 10 is 30 mm and the width is 27.9 mm.

Further, both the inlet 21 and the outlet 22 of the cooling microchannel 20 are disposed on the blade tip 101 , wherein the inlet 21 is close to the leading edge 105 of the blade, and the outlet 22 is close to the trailing edge 106 of the blade. Since the leading edge 105 of the blade is directly impacted by the high temperature mainstream gas, the thermal load is the largest. Therefore, arranging the inlet 21 of the cooling microchannel 20 near the leading edge 105 of the blade can effectively reduce the thermal load of the leading edge 105 of the blade. .

In this embodiment, the turbine blade body 10 and the cooling microchannel 20 are both axisymmetric structures.

Further, please refer to FIG. 3 and FIG. 4 in combination. FIG. 3 is three views of a turbine blade with kerosene cooling microchannels provided by an embodiment of the present invention, wherein (a) is a front view, and (b) is a front view. Right view, (c) is a top view; FIG. 4 is a schematic structural diagram of a cooling microchannel provided by an embodiment of the present invention, wherein (a) is a perspective view, and (b) is a top view. As shown in the figure, the cooling microchannel 20 includes an inlet branching section 201, a first branching branch 202, a second branching branch 203, a first transition section 204, a second transition section 205, a first converging branch 206, a second branch Convergence branch 207 and outlet confluence section 208 .

Specifically, the first branch branch 202 , the first confluence branch 206 and the first transition section 204 are all set according to the curvature of the suction surface 104 of the blade; the second branch branch 203 , the second confluence branch 207 and the second transition section 205 are set according to the curvature of the blade pressure surface 103 . It is used to ensure that the cooling microchannels can be evenly distributed from the blade surface to prevent excessive thermal stress caused by large differences in blade temperature distribution.

Further, the first end of the inlet diversion section 201 is connected to the inlet 21, the second end is connected to the first diversion branch 202 and the second diversion branch 203 respectively; the first end of the outlet confluence section 208 is connected to the outlet 22, and the second end is connected to the outlet 22. They are respectively connected to the first confluence branch 206 and the second confluence branch 207 . The first branch branch 202 and the first confluence branch 206 are connected to the first transition section 204 through several fluid microchannels 209 respectively; the second branch branch 203 and the second confluence branch 207 are connected to the first transition section 204 through several fluid microchannels 209 The two transition sections 205 are connected.

In this embodiment, the first branching branch 202 , the second branching branch 203 , the first converging branch 206 and the second converging branch 207 are all located near the blade tip 101 . Both the first transition section 204 and the second transition section 205 are located near the blade root 102 . Several fluid microchannels 209 are vertically arranged along the blade height direction of the turbine blade body 10 .

It should be noted that, in this embodiment, the cross-section of each branch of the cooling microchannel 20 is circular. The first branch branch 202 is connected to the first transition section 204 through four groups of fluid microchannels 209, the second branch branch 203 is connected to the second transition section 205 through five groups of fluid microchannels 209, and the first confluence branch 206 passes through four The group of fluid microchannels 209 is connected to the first transition section 204 , and the second confluence branch 207 is connected to the second transition section 205 through five groups of fluid microchannels 209 .

Further, both the inlet splitting section 201 and the outlet converging section 208 are in the shape of a truncated cone. Optionally, the diameter of the top surface of the truncated truncated cone is 1.5-2mm, the diameter of the bottom surface is 4-4.5mm, and the larger diameter of the truncated cone is used as the first end. Connect to inlet 21 or outlet 22. The inlet splitting section 201 and the outlet converging section 208 are designed to be truncated cones, which can ensure that the cooling kerosene can be more evenly distributed into each branch inside the cooling microchannel 20 .

In this embodiment, the diameter of the top surface of the circular frustum is 1.8 mm, and the diameter of the bottom surface is 4 mm.

It should be noted that, in this embodiment, the fluid passage formed by the first branch branch 202 , several fluid microchannels 209 , the first transition section 204 and the first confluence branch 206 realizes cooling of the blade suction surface 104 . The fluid passage formed by the second branch branch 203 , several fluid microchannels 209 , the second transition section 205 and the second confluence branch 207 realizes cooling of the blade leading edge 105 , the blade pressure surface 103 and the blade trailing edge 106 .

Further, optionally, the diameter of the fluid microchannel 209 is 0.8mm-1.2mm, and the height is 20-25mm.

In this embodiment, the fluid microchannel 209 has a diameter of 0.8 mm and a height of 25 mm.

Further, the spacing of several fluid microchannels 209 connected to the first transition section 204 is 2.5-3 times the diameter of the fluid microchannels 209 . The spacing of several fluid microchannels 209 connected to the second transition section 205 is 2.5-4 times the diameter of the fluidic microchannels 209 .

Further, the diameters of the first branch branch 202 , the second branch branch 203 , the first transition section 204 , the second transition section 205 , the first confluence branch 206 and the second confluence branch 207 are equal to the diameter of the fluid microchannel 209 . 1.5-3 times the diameter.

In this embodiment, the diameters of the first branch branch 202 , the second branch branch 203 , the first transition section 204 , the second transition section 205 , the first confluence branch 206 and the second confluence branch 207 are fluid micrometers. 1.8 times the diameter of the channel 209.

Further, the distance between the fluid microchannel 209 near the blade leading edge 105 and the blade leading edge 105 is 3-6 times the diameter of the fluid microchannel 209 .

In this embodiment, the distance between the fluid microchannel 209 near the blade leading edge 105 and the blade leading edge 105 is 5 times the diameter of the fluid microchannel 209 .

The working process of the turbine blade with kerosene cooling microchannels in this embodiment is as follows: the cooling fluid flows in from the inlet 21, and the fluid is divided into the first branch branch 202 and the second branch branch 203 through the inlet branch section 201, and the first branch The fluid in the branch 202 flows into the first transition section 204 through the fluid microchannel 209, the fluid in the second branch branch 203 flows into the second transition section 205 through the fluid microchannel 209, and the fluid in the first transition section 204 passes through the microchannel. The channel 209 flows into the first confluence branch 206, the fluid in the second transition section 205 flows into the second confluence branch 208 through the microchannel 209, and finally the fluid in the first confluence branch 206 and the second confluence branch 207 flows into the outlet The confluence section 208 flows out through the outlet 22 .

In this embodiment, the cooling fluid is kerosene, and several microchannels 209 can be regarded as several parallel U-shaped channels.

In the turbine blade with kerosene cooling microchannels in this embodiment, the cooling microchannels are arranged close to the leading edge of the blade and are evenly distributed along the blade pressure surface and the blade suction surface, and the heat transfer coefficient of the microchannel increases significantly as the diameter decreases , Compared with the larger diameter channel, the boundary layer of the microchannel is thinner, the convective heat transfer process is stronger, the heat transfer effect is more obvious, and the cooling effect on the turbine blades is better. Moreover, under the same average flow rate, the smaller the pipe diameter, the greater the fluid velocity gradient on the solid wall, the greater the temperature gradient, and the greater the heat transfer. In addition, the surface heat transfer coefficient of the cooling microchannel set in this embodiment is significantly higher than that of the conventional single cooling channel, and the increase of heat transfer increases with the increase of kerosene flow rate, which can significantly increase the heat transfer coefficient. heat, thereby reducing the thermal load on the blade surface.

For the turbine blade with kerosene cooling microchannels in this embodiment, the cooling microchannel cooling can effectively reduce the blade surface temperature, ensure the normal operation of the aerospace engine, and improve the efficiency and thrust-to-weight ratio of the turbine engine.

Embodiment 2

In this embodiment, the cooling effect of the turbine blade with the kerosene cooling microchannel of the first embodiment is verified by a simulation experiment.

Specifically, the mainstream gas temperature is 1000K, the mainstream gas flow rate is 100g/s, the cooling kerosene inlet temperature is 300K, and the flow rate is 5.7g/s. The simulation results are shown in Figure 5. Figure 5 is the temperature distribution diagram of the blade pressure surface and the blade suction surface provided by the embodiment of the present invention. It can be seen from the figure that the overall cooling effect of the blade is better, and the highest temperature occurs at the leading edge of the blade. The temperature at the leading edge of the blade is about 800K, which is 150-200K lower than the mainstream high-temperature gas temperature. The cooling microchannel has a large heat exchange area and a wide coverage area, and the distributed flow path arrangement can cover a wider area.

In this embodiment, the diameter of the fluid micro-channel is 0.8mm, which can be closer to the leading edge of the blade, and is evenly arranged on the pressure surface of the blade and the suction surface of the blade, so as to reduce the temperature of the leading edge of the blade, it can well strengthen the blade pressure The cooling effect of the surface and the suction surface of the blade, the average temperature of the pressure surface of the blade is 600K, the temperature of the suction surface of the blade decreases more obviously, and the temperature can be reduced to 550K in most areas, and the cooling effect is obvious.

Further, in order to compare with the cooling microchannel of this embodiment, a single cooling channel of conventional size is provided, please refer to FIG. 6 , FIG. 6 is a schematic structural diagram of the single cooling channel of conventional size provided by the embodiment of the present invention, Among them, (a) is a front view, (b) is a right view, (c) is a top view, and (d) is a perspective view. As shown in the figure, the diameter of a single cooling channel of conventional size is 4mm, the structure is a double U-shaped structure, the cross section is circular, and the direction of inlet and outlet is consistent with the cooling microchannel structure.

Further, to compare the temperature distribution at the middle diameter of the blade of the conventional-sized single cooling channel and the micro-channel cooling structure, please refer to FIG. 7, FIG. The temperature distribution map at the middle diameter of the blade of the channel, it can be seen from the figure,

Cooling microchannels significantly reduce the temperature at the leading edge of the blade as well as at the rest of the airfoil. The overall temperature of the cooling microchannel is 100-150K lower than that of a conventionally sized single cooling channel. Secondly, the high temperature area at the leading edge of the blade is significantly reduced in the cooling microchannel, and the temperature rise rate of the cooling microchannel at the leading edge of the blade is greater than that of a single cooling channel of conventional size. The highest temperature position of the cooling channel of both structures occurs near the leading edge, mainly because the leading edge of the blade is the area with the highest temperature, and more heat will be first introduced into the area closest to the leading edge of the blade through the leading edge surface of the blade. cooling channel. The temperature of the cooling microchannel near the suction surface of the blade is lower, so in the design, the number of fluid microchannels near the suction surface of the blade can be less than the part near the pressure surface of the blade.

A single cooling channel of conventional size can be regarded as composed of two U-shaped channels, and a cooling microchannel can be regarded as composed of multiple U-shaped channels in parallel. There is a high heat transfer area at the turn of the U-shaped channel. The main reason is that when the fluid encounters obstacles or needs to change the flow direction, the flow boundary layer develops again. When the boundary layer develops again, the fluid temperature boundary layer in the inlet section is thinner. , the temperature gradient at this position is large, so the heat exchange is strong, which is the so-called inlet effect, thereby strengthening the heat exchange. The designed cooling micro-channel is composed of multiple U-shaped channels in parallel, and there are many bends. If the boundary layer of the fluid is not fully developed, it will be destroyed, so the heat exchange effect is better.

Further, the heat transfer coefficient of the fluid microchannel increases significantly with the decrease of the diameter. Compared with the larger diameter channel, the boundary layer is thinner, the convective heat transfer process is stronger, and the heat transfer effect is more obvious. Please refer to FIG. 8. FIG. 8 is a streamline diagram of the fluid in the cooling microchannel provided by the embodiment of the present invention. It can be seen from the figure that the flow of the fluid in the cooling microchannel is a complex three-dimensional flow with a swirl. This phenomenon is particularly evident in transition sections and confluence branches. A large number of vortices are formed in the confluence area near the wall, which increases the disturbance and mixing between the fluids. After the boundary layer is formed, it is quickly destroyed, so that the heat transfer coefficient increases significantly.

For cooling microchannels, the reduction in diameter is a distinguishing feature of the structure. Whether it is laminar or turbulent flow, the convective heat transfer coefficient is approximately inversely proportional to the diameter of the tube. Under the same average flow rate, the smaller the pipe diameter, the greater the fluid velocity gradient on the solid wall, the greater the temperature gradient, and the greater the heat transfer. Please refer to FIG. 9. FIG. 9 is a graph of the average surface heat transfer coefficient of a single cooling channel of a conventional size and a cooling microchannel provided by an embodiment of the present invention. Comparing the average heat transfer coefficient of a single cooling channel of a conventional size and a cooling microchannel, it can be found that , the surface heat transfer coefficient of the cooling microchannel is significantly higher than that of a single cooling channel of conventional size, and the increase of heat transfer increases with the increase of kerosene flow rate. Cooling microchannels can significantly increase the heat transfer, thereby reducing the thermal load on the blade surface.

In order to verify the accuracy of the numerical simulation, the experimental data of the flow heat transfer of the turbine blades with kerosene cooling microchannels of this embodiment are tested. The measured data are the inlet and outlet temperature and pressure of the mainstream, the inlet and outlet temperature and pressure of the cooling fluid, and the temperature value of a single point of the blade. As a reference for numerical simulation, the experimental results can provide reliable comparative verification.

Please refer to FIG. 10. FIG. 10 is a schematic diagram of a turbine blade cooling experimental device provided by an embodiment of the present invention. The experimental device mainly includes a gas generator, a transition section, a test section, a kerosene cooling circuit, and a test and measurement instrument. Among them, the test section is connected with the gas generator through the transition section. During the experiment, the test device provides stable alcohol fuel and oxidant air for the combustion chamber, and generates high-temperature gas after ignition, which is passed into the experimental test section. The experimental test section is connected by the flange and the adapter section, and the experimental test blade is welded in the middle of the test section. The inlet and outlet of the experimental section are respectively set with temperature and pressure measurement points, a temperature measurement point is set on the blade surface, and a pair of temperature and pressure measurement points are set at the cooling flow inlet and outlet.

In the experiment, the cooling effect of the micro-channel cooling structure was compared by measuring the inlet and outlet temperature of kerosene, calculating the heat transfer Q and the heat transfer coefficient h, and combining the difference between the inlet temperature Tin and the blade measuring point temperature Ty. The high-temperature mainstream gas is generated by the ignition of air and alcohol through double spark plugs, and the temperature is maintained at about 1000K. The cooling fluid adopts RP-3 aviation kerosene. During the experiment, ensure that the mass flow of the mainstream gas and the cooling fluid remains stable, and the mainstream gas is kept at 100g/s throughout the experiment. point value.

Please refer to FIG. 11. FIG. 11 is a simulation and experimental error diagram of the dimensionless value of the inlet and outlet kerosene temperature rise of the cooling microchannel provided by the embodiment of the present invention. As shown in the figure, for the working condition of the mainstream gas temperature of 1000K, with the When the flow rate increases, the variation trend of simulation results and experimental results is similar. Most of the errors between numerical simulation and experiment of kerosene temperature rise are between ±8%, and the deviation of experimental data is within 10%. The larger part of the error between the experiment and the simulation occurs when the flow rate is small. At this time, the kerosene temperature rise is the largest, about 100 °C, and the error is mainly caused by the flow measurement error.

Please refer to FIG. 12. FIG. 12 is a diagram showing the relationship between kerosene temperature rise and heat exchange in the cooling microchannel and kerosene flow rate provided by an embodiment of the present invention. It can be seen from the figure that the kerosene temperature rise at the inlet and outlet of the cooling microchannel varies with the flow rate. increases and decreases with an approximate linear relationship. The heat exchange of kerosene in the cooling microchannel increases with the increase of kerosene flow, and the increase rate gradually slows down.

The kerosene cooling test conditions and test results of the turbine blades with kerosene cooling microchannels in this embodiment are shown in Table 1. It can be seen that the highest temperature of the turbine blades occurs at the leading edge of the blade. According to the experimental measurement, the main flow and the leading edge of the blade The temperature difference is between 134-209K, that is, the turbine blade can reduce the temperature of 134K under the working condition of the minimum kerosene flow rate of 4g/s. Within the range of ensuring the melting point temperature of the blade material, the kerosene cooling microchannel of the present invention can increase the mainstream temperature by 13.4%, which is significant for improving the thermal efficiency and thrust-to-weight ratio of the turbine engine.

Table 1 Micro-channel kerosene cooling test conditions and test results

It should be noted that, in this document, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any relationship between these entities or operations. any such actual relationship or sequence exists. Moreover, the terms "comprising", "comprising" or any other variation are intended to encompass a non-exclusive inclusion, whereby an article or device comprising a list of elements includes not only those elements, but also other elements not expressly listed. Without further limitation, an element qualified by the phrase "comprising a..." does not preclude the presence of additional identical elements in the article or device that includes the element. Words like "connected" or "connected" are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The orientation or positional relationship indicated by "up", "bottom", "left", "right", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying The device or element referred to must have a particular orientation, be constructed and operate in a particular orientation, and therefore should not be construed as limiting the invention.

The above content is a further detailed description of the present invention in combination with specific preferred embodiments, and it cannot be considered that the specific implementation of the present invention is limited to these descriptions. For those of ordinary skill in the technical field of the present invention, without departing from the concept of the present invention, some simple deductions or substitutions can be made, which should be regarded as belonging to the protection scope of the present invention.

Claims (7)

1. A turbine blade with kerosene cooling microchannels, characterized in that, comprising: a turbine blade body (10) and a cooling microchannel (20) arranged in its interior, wherein, The turbine blade body (10) includes a blade tip (101), a blade root (102), and a blade body located between the blade tip (101) and the blade root (102), the blade body being driven by blade pressure The blade surface (103) and the blade suction surface (104) are surrounded by a blade leading edge (105) and a blade trailing edge respectively formed at the connection between the blade pressure surface (103) and the blade suction surface (104). (106); Both the inlet (21) and the outlet (22) of the cooling microchannel (20) are arranged on the blade tip (101), wherein the inlet (21) is close to the leading edge (105) of the blade, and the an outlet (22) near the blade trailing edge (106); The cooling microchannel (20) includes an inlet branch section (201), a first branch branch (202), a second branch branch (203), a first transition section (204), a second transition section (205), The first confluence branch (206), the second confluence branch (207) and the outlet confluence section (208), wherein, The first branching branch (202), the first converging branch (206) and the first transition section (204) are all set according to the curvature of the suction surface (104) of the blade; the second branching The branch (203), the second confluence branch (207) and the second transition section (205) are all arranged according to the curvature of the blade pressure surface (103); The first end of the inlet splitting section (201) is connected to the inlet (21), and the second end is respectively connected to the first splitting branch (202) and the second splitting branch (203); the The first end of the outlet confluence section (208) is connected to the outlet (22), and the second end is respectively connected to the first confluence branch (206) and the second confluence branch (207); The first branch branch (202) and the first confluence branch (206) are respectively connected with the first transition section (204) through a plurality of fluid microchannels (209); the second branch branch ( 203) and the second confluence branch (207) are respectively connected with the second transition section (205) through a plurality of the fluid microchannels (209); The first branching branch (202), the second branching branch (203), the first converging branch (206) and the second converging branch (207) are all located close to the blade tip (101) ), the first transition section (204) and the second transition section (205) are both located close to the blade root (102). 2 . The turbine blade with kerosene cooling microchannels according to claim 1 , wherein the inlet splitting section ( 201 ) and the outlet confluence section ( 208 ) are both in the shape of a truncated cone, and the diameter of the top surface of the truncated truncated cone. 3 . The diameter of the bottom surface is 1.5-2mm, the diameter of the bottom surface is 4-4.5mm, and the larger diameter of the circular truncated cone is used as the first end to connect with the inlet (21) or the outlet (22). 3. The turbine blade with kerosene cooling microchannels according to claim 1, wherein a plurality of the fluid microchannels (209) are vertically arranged along the blade height direction of the turbine blade body (10), The fluid microchannel (209) has a diameter of 0.8mm-1.2mm and a height of 20-25mm. 4. The turbine blade with kerosene cooling microchannels according to claim 1, characterized in that, the distance between a plurality of the fluid microchannels (209) connected with the first transition section (204) is equal to the distance between the fluid microchannels 2.5-3 times the diameter of the channel (209). 5. The turbine blade with kerosene cooling microchannels according to claim 1, characterized in that, the distance between a plurality of the fluid microchannels (209) connected with the second transition section (205) is equal to the distance of the fluid microchannels (209). 2.5-4 times the diameter of the channel (209). 6. The turbine blade with kerosene cooling microchannels according to claim 1, wherein the first branch branch (202), the second branch branch (203), and the first transition section (204), the second transition section (205), the first confluence branch (206) and the second confluence branch (207) have a diameter of 1.5 of the diameter of the fluid microchannel (209) -3 times. 7. The turbine blade with kerosene cooling microchannels according to claim 1, wherein the fluid microchannel (209) close to the blade leading edge (105) is located between the fluid microchannel (209) and the blade leading edge (105). The distance between them is 3-6 times the diameter of the fluid microchannel (209).

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