CN113586165B - Turbine blade with single kerosene cooling channel - Google Patents

Abstract

The present invention relates to a turbine blade having a single kerosene cooling passage, comprising: the cooling structure comprises a turbine blade body and a cooling 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 front edge and a blade tail edge are respectively formed at the connection part of the blade pressure surface and the blade suction surface; the cooling channel comprises a plurality of U-shaped channels which are sequentially connected in series, and an inlet and an outlet of the cooling channel are both arranged on the blade top, wherein the inlet is close to the front edge of the blade, and the outlet is close to the tail edge of the blade; the U-shaped channels are sequentially arranged along the arc length direction of the suction surface of the blade. The cooling channel arranged on the turbine blade can effectively reduce the temperature of the blade, and the purpose of uniformly cooling the pressure surface and the suction surface of the blade is achieved.

Description

A turbine blade with a single kerosene cooling channel

technical field

The invention belongs to the field of gas turbines and aerospace engines, in particular to a turbine blade with a single kerosene cooling channel.

Background technique

Gas turbines and aerospace engines are important equipment in the energy field. In order to improve the thermal efficiency and thrust-weight ratio of the engine, the gas inlet temperature before the turbine must be increased. At present, the turbine inlet temperature has far exceeded the temperature resistance range of the blade material. In order to solve the problem of excessive turbine inlet temperature, researchers are committed to developing more temperature-resistant blade materials, or to solve the problem of excessive inlet temperature by developing cooling technology.

Common turbine blade cooling methods include internal convection cooling and external film cooling. For the internal convection cooling method, the internal cooling channel mostly adopts a rotary cooling channel, but the rotary cooling channel is limited by the heat exchange area and the contact between the cold air and the hot wall surface. Insufficient conditions such as insufficient cooling lead to uneven cooling of turbine blades.

SUMMARY OF THE INVENTION

In order to solve the above problems existing in the prior art, the present invention provides a turbine blade with a single kerosene cooling channel. 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 a single kerosene cooling channel, comprising: a turbine blade body and a cooling channel arranged 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;

The cooling channel includes several U-shaped channels serially connected in series, and the inlet and outlet of the cooling channel are both arranged on the blade tip, wherein the inlet is close to the leading edge of the blade, and the outlet is close to the blade. film trailing edge;

A plurality of the U-shaped channels are arranged in sequence along the arc length direction of the suction surface of the blade.

In one embodiment of the present invention, the cooling channel includes a connected first U-shaped channel and a second U-shaped channel, the first U-shaped channel includes a first descending portion and a first ascending portion, and the second U-shaped channel includes a first descending portion and a first ascending portion. The U-shaped channel includes a second descending portion and a second ascending portion, wherein,

The first end of the first descending part is connected to the inlet, and the second end is connected to the first end of the first ascending part;

The second end of the first ascending portion is connected to the first end of the second descending portion, the second end of the second descending portion is connected to the first end of the second ascending portion, and the second ascending portion the second end is connected to the outlet;

The first ascending part is connected with the second descending part to form an n-type structure, and the n-type structure is located near a position where the curvature of the suction surface of the blade is the largest.

In an embodiment of the present invention, the cross section of the U-shaped channel is circular, and the diameter of the U-shaped channel is 3-5 mm.

In an embodiment of the present invention, the distance between the inlet and the leading edge of the blade and the distance between the outlet and the trailing edge of the blade are both 2.8- of the diameter of the U-shaped channel 3 times.

In an embodiment of the present invention, the distance between the n-type structure and the position of the maximum curvature of the suction surface of the blade is 1-1.5 times the diameter of the U-shaped channel.

In an embodiment of the present invention, the distance between the first descending part and the first ascending part, and the distance between the second descending part and the second ascending part are the 1.5-2 times the diameter of the U-shaped channel;

The distance between the first ascending part and the second descending part is 1.2-2 times the diameter of the U-shaped channel.

In an embodiment of the present invention, the length of the first descending portion and the second ascending portion is 4.5-7.5 times the diameter of the U-shaped channel;

The length of the first ascending part and the second descending part is 3.3-5.5 times the diameter of the U-shaped channel;

The distance between the bottom of the first U-shaped channel and the second U-shaped channel and the blade root is both 0.75-1.5 times the diameter of the U-shaped channel;

The distance between the top of the n-type structure and the blade tip is 0.6-1.2 times the diameter of the U-shaped channel.

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

1. The turbine blade with a single kerosene cooling channel of the present invention is provided with a cooling channel inside the turbine blade body, and the cooling channel includes several U-shaped channels connected in series in sequence, and the fluid in the channel is close to the blade tip or blade root. Three flow direction changes occur at the location, and the flow boundary layer and the thermal boundary layer will develop again, and the redevelopment of the boundary layer will lead to an increase in the convective heat transfer coefficient in a single channel, thereby achieving the effect of strengthening heat transfer;

2. The turbine blade with a single kerosene cooling channel of the present invention forms a channel with an n-type structure near the position where the curvature of the suction surface of the blade is the largest. Since the external convective heat transfer coefficient is large at the position where the curvature of the suction surface of the blade is the largest, the The channel is arranged in this position, which can effectively reduce the temperature of the position, and achieve the purpose of uniform cooling of the blade pressure surface and the blade suction surface;

3. The turbine blade with a single kerosene cooling channel of the present invention has a simple structure, is easy to process, and has low flow resistance.

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 a single kerosene cooling channel 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 a single kerosene cooling channel provided by an embodiment of the present invention;

4 is a schematic structural diagram of a cooling channel 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 velocity vector diagram of a U-shaped channel section provided by an embodiment of the present invention;

7 is a distribution diagram of the surface Nusselt number of cooling channels under different flow rates provided by an embodiment of the present invention;

8 is a schematic structural diagram of a comparative cooling channel provided by an embodiment of the present invention;

9 is a cross-sectional temperature distribution diagram of a blade mid-diameter surface of a cooling channel provided by an embodiment of the present invention and a comparative cooling channel;

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

11 is a simulation and experimental error result diagram of the dimensionless value of the average temperature of the surface of the cooling channel structure provided by the embodiment of the present invention;

FIG. 12 is a relationship diagram of the kerosene temperature rise and the heat exchange and the kerosene flow rate in the cooling channel provided by the 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 a single kerosene cooling channel proposed by 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 combination. FIG. 1 is a perspective perspective view of a turbine blade with a single kerosene cooling channel provided by an embodiment of the present invention, and 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 a single kerosene cooling channel of this embodiment includes a turbine blade body 10 and a cooling channel 20 provided in the interior thereof.

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.

Specifically, the cooling channel 20 includes several U-shaped channels connected in series. The inlet 201 and the outlet 202 of the cooling channel 20 are both disposed on the blade tip 101 , wherein the inlet 201 is close to the leading edge 105 of the blade, and the outlet 202 is close to the trailing edge 106 of the blade ; Several U-shaped channels are arranged in turn along the arc length direction of the blade suction surface 104 .

In this embodiment, the turbine blade body 10 and the cooling channel 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 a single kerosene cooling channel provided by an embodiment of the present invention, wherein (a) is a front view, and (b) is a Right view, (c) is a top view; FIG. 4 is a schematic structural diagram of a cooling channel 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, in this embodiment, the cooling channel 20 includes a connected first U-shaped channel 203 and a second U-shaped channel 204, and the first U-shaped channel 203 includes a first descending portion 2031 and a first ascending portion 2032, The second U-shaped channel 204 includes a second descending portion 2041 and a second ascending portion 2042 .

The first end of the first descending portion 2031 is connected to the inlet 201, the second end is connected to the first end of the first ascending portion 2032; the second end of the first ascending portion 2032 is connected to the first end of the second descending portion 2041, The second ends of the two descending portions 2041 are connected to the first ends of the second ascending portions 2042 , and the second ends of the second ascending portions 2042 are connected to the outlet 202 .

In this embodiment, since the arc length of the blade suction surface 104 is relatively long, the cooling channels 20 are mainly arranged along the arc length direction of the blade suction surface 104 .

Due to the large curvature of the blade leading edge 105 and the blade trailing edge 106, the first descending portion 2031 of the first U-shaped channel 203 is located close to the blade leading edge 105, the blade pressure surface 103 and the blade suction surface 104, and the second U-shaped channel 203 is located near the blade leading edge 105, the blade pressure surface 103 and the blade suction surface 104. The second riser 2042 of the shaped channel 204 is located close to the blade trailing edge 106 , the blade pressure surface 103 and the blade suction surface 104 .

Further, in this embodiment, the first ascending portion 2032 is connected with the second descending portion 2041 to form an n-type structure, and the n-type structure is located near the position where the curvature of the suction surface 104 of the blade is the largest. The position of the axis of symmetry has the largest curvature and the largest pressure gradient between the front and rear, which is easy to induce transition, and the heat transfer coefficient between the blade and the high-temperature gas increases. Therefore, the first ascending part 2032 and the second descending part 2041 are connected to form an n-type channel arrangement. In the place where the curvature of the blade suction surface 104 is the largest, the temperature of the position can be effectively reduced, so as to achieve the purpose of uniform cooling of the blade pressure surface 103 and the blade suction surface 104 .

It should be noted that both the first U-shaped channel 203 and the second U-shaped channel 204 are vertically arranged along the height direction of the turbine blade body 10 .

Further, the section of the U-shaped channel is circular, and the diameter of the U-shaped channel is 3-5mm.

Further, optionally, the distance between the inlet 201 and the leading edge 105 of the blade, and the distance between the outlet 202 and the trailing edge 106 of the blade are both 2.8-3 times the diameter of the U-shaped channel.

In this embodiment, the diameter of the U-shaped channel is 4 mm, and the distance between the inlet 201 and the leading edge 105 of the blade and the distance between the outlet 202 and the trailing edge 106 of the blade are both 2.8 times the diameter of the U-shaped channel.

Further, optionally, the distance between the n-type structure and the position of the maximum curvature of the blade suction surface 104 is 1-1.5 times the diameter of the U-shaped channel.

In this embodiment, the distance between the n-type structure and the position where the curvature of the suction surface 104 of the blade is at the maximum curvature is 1.25 times the diameter of the U-shaped channel.

Further, optionally, the distance between the first descending portion 2031 and the first ascending portion 2032, as well as the distance between the second descending portion 2041 and the second ascending portion 2042, are both 1.5- of the diameter of the U-shaped channel. 2 times.

In this embodiment, the distance between the first descending portion 2031 and the first ascending portion 2032 (ie, the diameter of the turning point of the first U-shaped channel 203 ), and the distance between the second descending portion 2041 and the second ascending portion 2042 The distance between them (that is, between the turning points of the second U-shaped channel 204 ) is both twice the diameter of the U-shaped channel.

Further, optionally, the distance between the first ascending part 2032 and the second descending part 2041 is 1.2-2 times the diameter of the U-shaped channel.

In this embodiment, the distance between the first ascending portion 2032 and the second descending portion 2041 (ie, the diameter at the turning point of the n-type structure) is 1.6 times the diameter of the U-shaped channel.

Further, optionally, the length of the first descending part 2031 and the second ascending part 2042 is 4.5-7.5 times the diameter of the U-shaped channel; the length of the first ascending part 2032 and the second descending part 2041 is the length of the U-shaped channel 3.3-5.5 times the diameter; the distance between the bottom of the first U-shaped channel 203 and the second U-shaped channel 204 and the blade root 102 is 0.75-1.5 times the diameter of the U-shaped channel; the top of the n-type structure and the blade The distance between the tops 101 is 0.6-1.2 times the diameter of the U-shaped channel.

In this embodiment, the lengths of the first descending portion 2031 and the second ascending portion 2042 (that is, the length of L1 in FIG. 3(b)) are 5.75 times the diameter of the U-shaped channel; The length of the descending portion 2041 (that is, the length of L3 in (b) in FIG. 3 ) is 4.1 times the diameter of the U-shaped channel;

The distance between the bottom of the first U-shaped channel 203 and the second U-shaped channel 204 and the blade root 102 (that is, the length of L2 in (b) in FIG. 3 ) is both 0.75 times the diameter of the U-shaped channel; n-type structure The distance between the top of the blade tip 101 (ie the length of L4 in (b) in FIG. 3 ) is 0.8 times the diameter of the U-shaped channel.

The working process of the turbine blade with a single kerosene cooling channel in this embodiment is as follows: the cooling fluid enters from the inlet 201, passes through the first U-shaped channel 203 and the second U-shaped channel 204 in sequence, and finally flows out from the outlet 202. In this embodiment , the cooling fluid is kerosene.

In the turbine blade with a single kerosene cooling channel in this embodiment, a cooling channel is provided inside the turbine blade body. The cooling channel includes several U-shaped channels connected in series, and the fluid in the channel is close to the blade tip or the blade root. The three-time flow direction change occurs at the location where the flow boundary layer and the thermal boundary layer will develop again, and the redevelopment of the boundary layer will lead to an increase in the convective heat transfer coefficient in a single channel, thereby achieving the effect of strengthening heat transfer; An n-type channel is formed at the position with the largest curvature of the suction surface of the blade. Since the external convective heat transfer coefficient is large at the position with the largest curvature of the suction surface of the blade, arranging the channel at this position can effectively reduce the temperature at this position and realize the blade pressure. The purpose of uniform cooling of the surface and the suction surface of the blade.

The turbine blade with a single kerosene cooling channel of this embodiment has a simple structure, is easy to process, and has low flow resistance.

Embodiment 2

This embodiment verifies the cooling effect of the turbine blade with a single kerosene cooling channel of the first embodiment 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. Please refer to Figure 5 for the simulation results. 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 cooling effect of the blade pressure surface and the blade suction surface is relatively good. Compared with the mainstream gas temperature of 1000K, the temperature of the blade pressure surface and the blade suction surface is reduced by about 200K, and the temperature of the leading edge of the blade is reduced by about 100K.

Further, the velocity vector diagram of the U-shaped channel section in the cooling channel is analyzed, please refer to FIG. 6 , which is the velocity vector diagram of the U-shaped channel section provided by the embodiment of the present invention. It can be seen from the figure that the fluid is in the front area of the elbow, and the fluid velocity near the inner wall is high, and the fluid passing through the elbow area is thrown to the outer wall by centrifugal force to generate a secondary flow. Through the enhanced heat transfer field synergistic theoretical analysis, under the given conditions of flow velocity and physical properties of the fluid, the heat transfer intensity at the convective heat transfer interface depends not only on the velocity field and the temperature gradient field itself, but also on the sandwich between them. The angle depends not only on the absolute values of the velocity field, the temperature gradient field, and the included angle field, but also on the mutual collocation of these three scalar values. The combination of the velocity field and the temperature gradient field in the convective heat transfer can enhance the heat transfer. At this time, the velocity field and the temperature gradient field cooperate well.

The synergy between the velocity field and the temperature gradient field is reflected in three aspects:

1) The angle between the speed and the temperature gradient should be as small as possible, and the two should be as parallel as possible;

2) The local values of velocity, temperature gradient and included angle cosine should be relatively large at the same time, that is, where the included angle cosine is large, the value of velocity and temperature gradient should also be relatively large;

3) The fluid velocity profile and temperature profile should be as uniform as possible (under certain conditions of maximum flow velocity and temperature difference).

In the area behind the elbow, the fluid velocity decreases near the wall surface, resulting in flow vortices, and the flow area becomes smaller, and the velocity near the outer wall surface is larger. Therefore, a high heat transfer area will be formed in the area near the inner wall before the elbow and near the outer wall after the elbow, where the synergistic angle between the velocity field and the temperature gradient field is the smallest, which is most conducive to heat transfer.

Further, please refer to FIG. 7. FIG. 7 is a distribution diagram of the surface Nusselt number of the cooling channel under different flow rates provided by the embodiment of the present invention, (the kerosene flow rates are 10.5g/s, 7.8g/s, 5.7g/s, respectively. s, 4.1g/s) It can be seen from the figure that the overall distribution of the Nusselt number on the surface of the cooling channel is relatively uniform, and there is a high heat exchange area at the turn of the U-shaped channel, and the heat exchange can be seen at three turns. The case where the thermal coefficient is enhanced. Because the fluid exchanges heat in the tube, when the fluid flows through the elbow, due to centrifugal force, a secondary circulation is generated in the cross section, which increases the disturbance between the fluids and enhances the heat exchange effect. Strong convection is usually turbulent energy loss proportional to heat exchange in a certain area. In order to increase the heat exchange area and enhance the heat exchange, the heat exchange channels or pipes are usually made into the form of winding elbows. When the velocity boundary layer of the fluid develops again, a vortex structure is created in this region. The longitudinal vortex induced by the secondary flow in the channel is an accompanying flow that occurs in the direction perpendicular to the main flow. The intensity of this accompanying movement is usually much smaller than that of the main flow, but its effect on strengthening the heat transfer process is more obvious. The size, location and frequency of the secondary flow will cause fluid velocity deflection and flow field pressure changes. By adjusting the geometry of the section or other parameters to control the secondary flow, heat transfer can be further enhanced.

Further, in order to compare with the cooling channel of this embodiment, a comparison cooling channel is provided, please refer to FIG. 8 , FIG. 8 is a schematic structural diagram of a comparison cooling channel provided by the embodiment of the present invention, wherein, (a) The picture 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, in this comparative cooling channel, the first U-shaped channel and the second U-shaped channel are connected. Type channel merge.

Please refer to FIG. 9. FIG. 9 is a cross-sectional temperature distribution diagram of the blade mid-diameter surface of the cooling passage provided by the embodiment of the present invention and the comparative cooling passage. As shown in the figure, the cooling passage of the present embodiment and the comparative cooling passage have the leading edge temperature of the blade. The distribution difference is small, and the dimensionless temperature ratio of the blade leading edge to the mainstream temperature is about 0.95. Because of the characteristics of the blade structure, the mainstream of the leading edge directly impacts, and the heat load is the largest, and the temperature here is closest to the mainstream temperature. However, the cooling channel of this embodiment can significantly reduce the surface temperature of the blade pressure surface and the blade suction surface. The main reason for the small temperature difference of the leading edge is that the cooling channel of this embodiment and the comparison cooling channel have the same distance from the leading edge.

In addition, as previously analyzed, the form of U-shaped pipe can increase the local heat transfer coefficient at the elbow, thereby promoting the increase of the overall heat transfer coefficient. Therefore, in addition to the advantages of evenly distributing the pipes, the cooling channel of this embodiment also adds two-pass U-shaped pipes, which improves the overall heat transfer coefficient, which is beneficial to the overall temperature reduction of the blade. Therefore, the cooling channel structure designed in this embodiment can uniformly cool the blades by increasing the number of pipe turns within a certain space range, and can also ensure a certain cooling effect on the suction surface with poor cooling effect.

In order to verify the accuracy of the numerical simulation, the experimental data of the flow heat transfer of the turbine blade with a single kerosene cooling channel of this embodiment are tested. A blade cooling experimental device is provided, which mainly includes a gas generator, a transition section, a test section, a kerosene cooling circuit, a test and measurement instrument, and the like.

Among them, the mainstream gas consists of alcohol fuel and oxidant air. 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. The experimental equipment is mainly composed of air source, alcohol storage tank, nitrogen blowing system, gas generator, cooling air system, cooling kerosene system, regulating valve, etc. The experimental equipment is mainly composed of temperature sensor, pressure transmitter, orifice flowmeter, etc. composition.

Please refer to FIG. 10. FIG. 10 is a simulation and experimental error result diagram of the dimensionless value of the kerosene temperature rise at the inlet and outlet of the cooling channel provided by the embodiment of the present invention. The working conditions can ensure that the error between the numerical simulation and the test is within 10%. The larger error occurs in the case of small flow rate, because when the flow rate is small, the measurement error of the test may be larger, resulting in a larger error between the simulation and the test.

The heat transfer of the inner wall can also be derived from the data measured by the experiment to obtain the dimensionless value of the average temperature in the cooling channel of the blade. Please refer to FIG. 11. FIG. 11 is a simulation and experimental error result diagram of the dimensionless value of the average temperature of the surface of the cooling channel structure provided by the embodiment of the present invention. As shown in the figure, the heat transfer experimental data is compared with the numerical simulation value, The simulation error of the dimensionless value of the average surface temperature of the cooling channel is within 10%, which verifies the accuracy of the internal and external coupling calculation, and the calculated value is in good agreement with the experimental value. In the conventional single-channel cooling structure, the temperature difference between the cooling channel inside the blade and the mainstream is about 250K.

Please refer to FIG. 12 . FIG. 12 is a diagram showing the relationship between the kerosene temperature rise and the heat exchange and the kerosene flow rate in the cooling channel provided by the embodiment of the present invention. It can be seen from the figure that the kerosene temperature rise is approximately linear with the kerosene flow rate. The kerosene temperature rise is between 45 and 100 °C.

The kerosene cooling test conditions and test results of the turbine blade with a single kerosene cooling channel in this embodiment are shown in Table 1. It can be seen that the highest temperature of the turbine blade occurs at the leading edge of the blade. According to the experimental measurement, the difference between the main flow and the leading edge is The temperature difference is between 110-153K, that is, the turbine blade can reduce the temperature by 110K under the working condition of the minimum kerosene flow rate of 3.2g/s. Within the range of ensuring the melting point temperature of the blade material, the cooling passage of this embodiment can increase the mainstream temperature by 11% through kerosene cooling, which is significant for improving the thermal efficiency and thrust-to-weight ratio of the turbine engine.

Table 1 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 (6)

1. A turbine blade having a single kerosene cooling passage, comprising: a turbine blade body (10) and a cooling channel (20) disposed therein, wherein,

the turbine blade body (10) comprises a blade top (101), a blade root (102) and a blade body located between the blade top (101) and the blade root (102), the blade body is formed by enclosing a blade pressure surface (103) and a blade suction surface (104), and a blade leading edge (105) and a blade trailing edge (106) are respectively formed at the connection position of the blade pressure surface (103) and the blade suction surface (104);

the cooling channel (20) comprises a plurality of U-shaped channels which are sequentially connected in series, an inlet (201) and an outlet (202) of the cooling channel (20) are both arranged on the blade top (101), wherein the inlet (201) is close to the blade leading edge (105), and the outlet (202) is close to the blade trailing edge (106);

the U-shaped channels are sequentially arranged along the arc length direction of the suction surface (104) of the blade;

the turbine blade body (10) and the cooling channel (20) are both of an axisymmetrical structure;

the cooling channel (20) comprises a first U-shaped channel (203) and a second U-shaped channel (204) which are connected, the first U-shaped channel (203) comprises a first descending part (2031) and a first ascending part (2032), the second U-shaped channel (204) comprises a second descending part (2041) and a second ascending part (2042), wherein,

a first end of the first descending portion (2031) is connected to the inlet (201), and a second end is connected to a first end of the first ascending portion (2032);

a second end of the first rising portion (2032) is connected to a first end of the second falling portion (2041), a second end of the second falling portion (2041) is connected to a first end of the second rising portion (2042), and a second end of the second rising portion (2042) is connected to the outlet (202);

the first rising portion (2032) and the second falling portion (2041) are connected to form an n-type structure, and the n-type structure is located at a position close to the suction surface (104) of the blade where the curvature is maximum.

2. The turbine blade with a single kerosene cooling passage according to claim 1, wherein said U-shaped passage has a circular cross-section, and the diameter of said U-shaped passage is 3-5 mm.

3. The turbine blade with a single kerosene cooling channel according to claim 1, characterized in that the distance between the inlet (201) and the blade leading edge (105), and the distance between the outlet (202) and the blade trailing edge (106) are each 2.8-3 times the diameter of the U-shaped channel.

4. The turbine blade with a single kerosene cooling passage according to claim 1, characterized in that the distance between said n-type structure and the position where the curvature of said blade suction surface (104) is the largest is 1-1.5 times the diameter of said U-shaped passage.

5. The turbine blade with a single kerosene cooling passage according to claim 1, characterized in that the distance between the first descending portion (2031) and the first ascending portion (2032), and the distance between the second descending portion (2041) and the second ascending portion (2042) are each 1.5-2 times the diameter of the U-shaped passage;

the distance between the first rising portion (2032) and the second falling portion (2041) is 1.2-2 times the diameter of the U-shaped channel.

6. The turbine blade with a single kerosene cooling passage according to claim 1, characterized in that the length of the first descending portion (2031) and the second ascending portion (2042) is 4.5-7.5 times the diameter of the U-shaped passage;

the length of the first ascending part (2032) and the second descending part (2041) is 3.3-5.5 times the diameter of the U-shaped channel;

the distance between the bottom of the first U-shaped channel (203) and the bottom of the second U-shaped channel (204) and the blade root (102) is 0.75-1.5 times of the diameter of the U-shaped channels;

the distance between the top of the n-type structure and the blade top (101) is 0.6-1.2 times of the diameter of the U-shaped channel.

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