Turbine blade and cooling structure

Abstract

The invention provides a turbine blade and a cooling structure, and relates to the technical field of aviation turbine blade cooling. The turbine blade comprises a blade body, an air inlet cooling channel formed in the blade body and an impact cavity in the blade body. The impact cavity is communicated with the air inlet cooling channel through an impact hole, and the impact hole is formed in the suction surface side of the air inlet cooling channel; a tail edge internal cooling channel communicated with the impact cavity is arranged in the tail edge of the blade main body; the end part of the tail edge of the blade main body is provided with a tail edge crack communicated with the tail edge internal cooling channel; a plurality of turbulent flow columns are arranged in the impingement cavity and the trailing edge internal cooling channel; the turbulent flow columns comprise a plurality of first turbulent flow columns arranged in the impingement cavity and a plurality of second turbulent flow columns arranged in the trailing edge internal cooling channel; wherein the first turbulent flow column is a turbulent flow column with a Y-shaped cooling channel; and the second turbulent flow column is a turbulent flow column with a V-shaped cooling channel. According to the scheme, uniform distribution of the surface temperature of the turbine blade is achieved.

Description

Technical Field

[0001] The invention relates to the technical field of aviation turbine blade cooling, and in particular to a turbine blade and a cooling structure. Background Art

[0002] The spoiler column cooling technology is a method of enhancing heat transfer by utilizing the disturbing effect of a columnar object on the cooling flow. When the cooling flow passes through the columnar object, the cooling flow will form a vortex around the columnar object, increase the heat exchange area, and strengthen the disturbance, thereby enhancing the convective heat transfer effect. At present, the spoiler column cooling technology is widely used in the cooling system of turbine blades. It is one of the most critical internal cooling technologies. It can not only enhance the heat transfer effect of the trailing edge of the turbine blade, but also can be combined with impingement cooling to form a composite cooling structure, which is widely used for surface cooling of the mid-chord area of ​​the turbine blade. Among them, the existing circular spoiler column is the most commonly used spoiler column cooling structure. When the cooling flow flows through the circular spoiler column, a horseshoe vortex will be formed at the leading edge of the circular spoiler column, thereby improving the cooling capacity of the leading edge and the two side areas of the spoiler column. However, when the existing circular spoiler column is used, a backflow will be generated at the trailing edge of the spoiler column, thereby weakening the heat transfer effect of the area near the trailing edge of the spoiler column, reducing the cooling capacity of the corresponding position on the blade surface, and causing the problem of poor cooling effect at the trailing edge of the spoiler column, resulting in uneven temperature distribution on the blade surface. Summary of the invention

[0003] The invention provides a turbine blade and a cooling structure, which solves the problems that when an existing circular spoiler column is applied to a turbine blade, the backflow is generated at the trailing edge of the spoiler column, resulting in poor cooling effect at the trailing edge of the spoiler column and uneven temperature distribution on the surface of the turbine blade.

[0004] In order to solve the above technical problems, the technical solution of the present invention is as follows:

[0005] The present invention provides a turbine blade, comprising:

[0006] A blade body, wherein an air intake cooling channel is arranged at a mid-chord area of ​​the blade body, and an impact cavity is arranged inside the blade body;

[0007] The impact cavity is connected to the air intake cooling channel through a plurality of impact holes, and the impact holes are arranged on the suction surface side of the air intake cooling channel;

[0008] A trailing edge internal cooling channel is provided inside the trailing edge of the blade body, and the trailing edge internal cooling channel is communicated with the impact cavity;

[0009] The trailing edge end of the blade body is provided with a trailing edge slit communicating with the trailing edge internal cooling channel;

[0010] A plurality of spoiler columns are arranged in the impact cavity and the internal cooling channel of the trailing edge, and the spoiler columns include:

[0011] A plurality of first spoiler columns disposed in the impact cavity and a plurality of second spoiler columns disposed in the cooling channel inside the trailing edge;

[0012] Wherein, the first spoiler column is a spoiler column with a Y-shaped cooling channel; the second spoiler column is a spoiler column with a V-shaped cooling channel.

[0013] Optionally, the first spoiler column includes:

[0014] A first circular cylinder, wherein a first air inlet is disposed at a front edge of the first circular cylinder, and a first air outlet and a second air outlet are disposed at a rear edge of the first circular cylinder;

[0015] A Y-shaped cooling channel connecting the first air inlet, the first air outlet and the second air outlet is provided inside the first circular cylinder.

[0016] Optionally, the first air inlet is arranged at 1 / 2 column height of the front edge of the first circular cylinder, the first air outlet is arranged at the top surface of the rear edge of the first circular cylinder, and the second air outlet is arranged at the bottom surface of the rear edge of the first circular cylinder.

[0017] Optionally, the first air inlet is elliptical, and the major diameter of the cross section of the first air inlet is 1 / 2 of the diameter of the first circular cylinder, and the minor diameter is 1 / 2 of the major diameter.

[0018] Optionally, the Y-shaped cooling channel includes:

[0019] An air inlet channel, a third cooling channel, and a fourth cooling channel arranged at a second preset angle with the third cooling channel, which are arranged inside the first circular cylinder;

[0020] Wherein, the air inlet channel is connected to the first air inlet;

[0021] The third cooling channel is in communication with the air inlet channel and the first air outlet;

[0022] The fourth cooling channel is in communication with the air inlet channel and the second air outlet.

[0023] Optionally, the second spoiler column includes:

[0024] A second circular cylinder, wherein a second air inlet is disposed at a front edge of the second circular cylinder, and a third air outlet and a fourth air outlet are disposed at a rear edge of the second circular cylinder;

[0025] A V-shaped cooling channel connecting the second air inlet, the third air outlet and the fourth air outlet is provided inside the second circular cylinder.

[0026] Optionally, the V-shaped cooling channel includes:

[0027] A first cooling channel disposed inside the second circular cylinder and a second cooling channel disposed at a first preset angle with the first cooling channel;

[0028] Wherein, the first cooling channel connects the second air inlet and the third air outlet;

[0029] The second cooling channel connects the second air inlet and the fourth air outlet.

[0030] Optionally, the impact holes are evenly spaced and distributed on the suction surface side of the intake cooling channel.

[0031] Optionally, a plurality of rows of the first spoiler columns are arranged in the impact cavity, the first spoiler columns in each row are arranged alternately, and each first spoiler column is located in the middle of two impact holes.

[0032] The present invention also provides a cooling structure, comprising:

[0033] a plurality of first spoiler columns and / or a plurality of second spoiler columns;

[0034] Wherein, the first spoiler column is a spoiler column with a Y-shaped cooling channel; the second spoiler column is a spoiler column with a V-shaped cooling channel.

[0035] The above solution of the present invention includes at least the following beneficial effects:

[0036] The turbine blade of the present invention comprises: a blade body, an intake cooling channel is arranged at the mid-chord area of ​​the blade body, an impact cavity is arranged inside the blade body; the impact cavity is connected to the intake cooling channel through a plurality of impact holes, and the impact holes are arranged on the suction side of the intake cooling channel; a trailing edge internal cooling channel is arranged inside the trailing edge of the blade body, and the trailing edge internal cooling channel is connected to the impact cavity; a trailing edge slit connected to the trailing edge internal cooling channel is arranged at the trailing edge end of the blade body; a plurality of spoiler columns are arranged in the impact cavity and the trailing edge internal cooling channel, and the spoiler columns include: a plurality of first spoiler columns arranged in the impact cavity and a plurality of second spoiler columns arranged in the trailing edge internal cooling channel; wherein the first spoiler column is a spoiler column with a Y-shaped cooling channel; and the second spoiler column is a spoiler column with a V-shaped cooling channel. The cooling effect at the trailing edge of the spoiler column is enhanced, and the uniform distribution of the surface temperature of the turbine blade is achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 is a schematic diagram of the internal structure of the turbine blade of the present invention;

[0038] Figure 2is a three-dimensional diagram of a second spoiler column in a turbine blade of the present invention;

[0039] Figure 3 is a vertical cross-sectional view of a second spoiler column in a turbine blade of the present invention;

[0040] Figure 4 is a three-dimensional diagram of a first spoiler column in a turbine blade of the present invention;

[0041] Figure 5 is a vertical cross-sectional view of a first spoiler column in a turbine blade of the present invention;

[0042] Figure 6 is a schematic diagram of the arrangement of the second spoiler columns in the turbine blade of the present invention;

[0043] Figure 7 is a schematic diagram of the arrangement of the first spoiler column in the turbine blade of the present invention;

[0044] Figure 8 It is a schematic diagram of the structure in which the second spoiler column in the turbine blade of the present invention is arranged in the impact cavity;

[0045] Description of reference numerals:

[0046] 11. first circular cylinder; 12. first air inlet; 13. first air outlet; 14. second air outlet; 21. second circular cylinder; 22. second air inlet; 23. third air outlet; 24. fourth air outlet; 25. first cooling channel; 26. second cooling channel; 31. air inlet channel; 32. third cooling channel; 33. fourth cooling channel; 41. blade body; 42. air inlet cooling channel; 43. impact cavity; 44. impact hole; 45. first spoiler column; 46. trailing edge internal cooling channel; 47. second spoiler column; 48. trailing edge slit. DETAILED DESCRIPTION

[0047] The exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present invention and to enable the scope of the present invention to be fully communicated to those skilled in the art.

[0048] like Figures 1 to 8 As shown, an embodiment of the present invention provides a turbine blade, comprising:

[0049] A blade body 41, wherein an air intake cooling passage 42 is disposed at a mid-chord region of the blade body 41, and an impact cavity 43 is disposed inside the blade body 41;

[0050] The impact cavity 43 is connected to the air intake cooling channel 42 through a plurality of impact holes 44, and the impact holes 44 are arranged on the suction surface side of the air intake cooling channel 42;

[0051] A trailing edge internal cooling channel 46 is provided inside the trailing edge of the blade body 41, and the trailing edge internal cooling channel 46 is communicated with the impact cavity 43;

[0052] The trailing edge end of the blade body 41 is provided with a trailing edge slit 48 communicating with the trailing edge internal cooling channel 46;

[0053] A plurality of spoiler columns are disposed in the impact cavity 43 and the trailing edge internal cooling channel 46, and the spoiler columns include:

[0054] A plurality of first spoiler columns 45 disposed in the impact cavity 43 and a plurality of second spoiler columns 47 disposed in the trailing edge internal cooling channel 46;

[0055] The first spoiler column 45 is a spoiler column with a Y-shaped cooling channel; the second spoiler column 47 is a spoiler column with a V-shaped cooling channel.

[0056] The first spoiler column 45 comprises:

[0057] A first circular cylinder 11, wherein a first air inlet 12 is disposed at a front edge of the first circular cylinder 11, and a first air outlet 13 and a second air outlet 14 are disposed at a rear edge of the first circular cylinder 11;

[0058] A Y-shaped cooling channel connecting the first air inlet 12 , the first air outlet 13 , and the second air outlet 14 is defined inside the first circular cylinder 11 .

[0059] In this embodiment, the turbine blade is a turbine blade of an aircraft engine; when in use, the mainstream flows from the leading edge to the trailing edge along the blade profile of the blade body 41, while the cooling flow flows into the intake cooling channel 42 perpendicularly to the blade body 41, and then impacts the target surface of the impact cavity 43 through the impact hole 44, then passes through the spoiler column in the impact cavity 43 and generates disturbance, and finally flows through the spoiler column of the cooling channel 46 inside the trailing edge, flows out from the trailing edge slit 48, and merges with the mainstream; specifically, when the cooling flow flows into the intake cooling channel 42, it enters the impact cavity 43 at a relatively high speed through the impact hole 44 on the suction side of the intake cooling channel 42, and then impacts the target surface in the impact cavity 43, generating a strong disturbance to the boundary layer on the target surface, making the boundary layer thinner, and at the same time strengthening the disturbance of turbulence in other areas of the impact cavity 43; a first spoiler column 45 cooling structure is arranged behind each row of impact holes 44, and after the fluid is disturbed by the first spoiler column 45, the heat exchange area is increased. , the low-temperature area continues to diffuse toward the periphery, and a small portion of the cooling flow will enter the first air inlet 12 on the first spoiler column 45, and then flow out from the first air outlet 13 on the top surface of the trailing edge of the first spoiler column 45 and the second air outlet 14 on the bottom surface, impacting the wall surface of the impact cavity 43, greatly enhancing the disturbance effect of the wall flow field and strengthening the heat exchange; then the cooling flow flows into the trailing edge internal cooling channel 46 of the blade body 41, and the arrangement of the spoiler columns in the trailing edge internal cooling channel 46 can enhance the disturbance in the trailing edge internal cooling channel 46, thereby enhancing the heat exchange effect of the trailing edge, and at the same time, a small portion of the cooling flow will enter the V-shaped cooling channel of the second spoiler column 47 in the trailing edge internal cooling channel 46, and then flow out from the first air outlet 13 on the top surface and the second air outlet 14 on the bottom surface of the second spoiler column 47 through the V-shaped cooling channel, impacting the wall surface of the trailing edge internal cooling channel 46, thereby increasing the heat exchange effect, and finally flowing out from the trailing edge slit 48 to merge with the mainstream;

[0060] In this embodiment, the turbine blade is designed with an impact hole 44 on the suction surface side, a first spoiler column 45 in the impact cavity 43, and a second spoiler column 47 at the trailing edge, which can effectively enhance the heat exchange effect of the suction surface and the trailing edge surface of the turbine blade and make the temperature distribution of the suction surface and the trailing edge of the blade more uniform.

[0061] In this embodiment, the first spoiler column is arranged in the impact cavity 43 of the turbine blade. When arranged, the top surface of the first circular cylinder 11 is connected to the upper side wall in the impact cavity 43, and the bottom surface of the first circular cylinder 11 is connected to the lower side wall in the impact cavity 43; the first spoiler column 45 is a circular cylinder structure. When the cooling flow flows through the circular cylinder of the spoiler column, a horseshoe vortex is formed at the leading edge of the first spoiler column 45, thereby strengthening the cooling capacity of the leading edge and the two side areas of the first spoiler column 45. At the same time, a small part of the cooling flow will flow into the cooling vortex opened inside the first spoiler column 45 through the first air inlet 12. The air flows through a cooling channel (Y-shaped cooling channel) and then flows out from the first air outlet 13 and the second air outlet 14 on the top and bottom surfaces of the trailing edge of the first spoiler column 45, impacting the wall surface of the cooling channel inside the turbine blade, thereby intensifying the disturbance of the wall flow field and destroying the reflow area at the trailing edge of the first spoiler column 45, thereby improving the heat exchange effect at the trailing edge of the first spoiler column 45, thereby compensating for the deficiency of the existing circular spoiler column structure in which the heat exchange is weakened due to the reflow at the trailing edge, so that the spoiler column has a directional enhanced cooling effect, enhances the cooling effect at the trailing edge of the spoiler column, and achieves a uniform distribution of the surface temperature of the turbine blade.

[0062] In order to ensure the cooling effect of different chord length positions of the turbine blades, the spoiler column for the turbine blade of the invention has two different cooling channels designed in the spoiler column, namely a V-shaped cooling channel and a Y-shaped cooling channel; wherein the V-shaped cooling channel is suitable for opening inside the tall spoiler column, and the Y-shaped cooling channel is suitable for opening inside the short spoiler column; wherein the tall spoiler column is a spoiler column with a height-to-diameter ratio greater than 1, and the short spoiler column is a spoiler column with a height-to-diameter ratio less than 1;

[0063] In this embodiment, the diameter and height of the spoiler column depend on the size of the cooling channel inside the turbine blade. The larger the size of the cooling channel inside the turbine blade, the higher the height of the spoiler column. The diameter of the spoiler column can be set according to specific needs or a preset ratio. In a preferred embodiment, the diameter of the spoiler column is 20 mm, and the ratio of the height to the diameter of the spoiler column is 1.5.

[0064] In an optional embodiment of the present invention, the first air inlet 12 is arranged at 1 / 2 column height of the front edge of the first circular cylinder 11, the first air outlet 13 is arranged on the top surface of the rear edge of the first circular cylinder 11, and the second air outlet 14 is arranged on the bottom surface of the rear edge of the first circular cylinder 11.

[0065] The first air inlet 12 is elliptical, and the major diameter of the cross section of the first air inlet 12 is 1 / 2 of the diameter of the first circular cylinder 11, and the minor diameter is 1 / 2 of the major diameter.

[0066] In this embodiment, the first air outlet 13 is arranged on the top surface of the rear edge of the first circular cylinder 11, and is located at the connection between the top surface of the first circular cylinder 11 and the side surface of the first circular cylinder 11; the second air outlet 14 is arranged on the bottom surface of the rear edge of the first circular cylinder 11, and is located at the connection between the bottom surface of the first circular cylinder 11 and the side surface of the first circular cylinder 11; the first air inlet 12 is an elliptical hole structure, and the major diameter of the elliptical hole cross-section is 1 / 2 of the diameter of the first circular cylinder 11, and the minor diameter is 1 / 2 of the major diameter.

[0067] In an optional embodiment of the present invention, the Y-shaped cooling channel comprises:

[0068] An air inlet channel 31, a third cooling channel 32, and a fourth cooling channel 33 arranged at a second preset angle with the third cooling channel 32, which are arranged inside the first circular cylinder 11;

[0069] Wherein, the air inlet channel 31 is connected to the first air inlet 12;

[0070] The third cooling channel 32 is in communication with the air inlet channel 31 and the first air outlet 13;

[0071] The fourth cooling channel 33 is in communication with the air inlet channel 31 and the second air outlet 14 .

[0072] In this embodiment, the third cooling channel 32 and the fourth cooling channel 33 are symmetrically arranged in the first circular cylinder 11; for the spoiler column with a Y-shaped cooling channel arranged inside, when the cooling flow flows into the first air inlet 12, it first passes through the air inlet channel 31 with a length of a preset distance, and then is divided into two paths, and then passes through the third cooling channel 32 and the fourth cooling channel 33, and flows out from the first air outlet 13 on the top surface of the trailing edge of the spoiler column (first circular cylinder 11) and the second air outlet 14 on the bottom surface, and impacts on the wall surface of the cooling channel inside the turbine blade; thereby strengthening the disturbance of the wall flow field, destroying the reflow area at the trailing edge of the spoiler column, and improving the heat exchange effect at the trailing edge of the spoiler column, so that the spoiler column has a directional enhanced cooling effect, enhances the cooling effect on the surface of the turbine blade at the trailing edge of the spoiler column, and achieves a uniform distribution of the surface temperature of the turbine blade;

[0073] In this embodiment, the length of the air inlet channel 31 can be determined according to the angle between the third cooling channel 32 and the fourth cooling channel 33, and the angle between the third cooling channel 32 and the flow direction of the cooling flow is the same as the angle between the fourth cooling channel 33 and the flow direction of the cooling flow; in a preferred embodiment, the angle between the third cooling channel 32 and the flow direction of the cooling flow (the direction of the air inlet channel 31) can be selected according to demand, and the selected range is preferably 30 to 60 degrees; in a preferred embodiment, the length of the air inlet channel 31 is 8 mm, and the angle between the third cooling channel 32 and the flow direction of the cooling flow is 39.81°.

[0074] In an optional embodiment of the present invention, the second spoiler column 47 includes:

[0075] A second circular cylinder 21, wherein a second air inlet 22 is disposed at a front edge of the second circular cylinder 21, and a third air outlet 23 and a fourth air outlet 24 are disposed at a rear edge of the second circular cylinder 21;

[0076] A V-shaped cooling channel connecting the second air inlet 22 , the third air outlet 23 , and the fourth air outlet 24 is defined inside the second circular cylinder 21 .

[0077] In this embodiment, the second air inlet 22 is arranged at 1 / 2 column height of the front edge of the second circular cylinder 21, the third air outlet 23 is arranged on the top surface of the rear edge of the second circular cylinder 21, and the fourth air outlet 24 is arranged on the bottom surface of the rear edge of the second circular cylinder 21.

[0078] The second air inlet 22 is elliptical, and the major diameter of the cross section of the second air inlet 22 is 1 / 2 of the diameter of the second circular cylinder 21 , and the minor diameter is 1 / 2 of the major diameter.

[0079] In an optional embodiment of the present invention, the V-shaped cooling channel comprises:

[0080] A first cooling channel 25 disposed inside the second circular cylinder 21 and a second cooling channel 26 disposed at a first preset angle with the first cooling channel 25;

[0081] Wherein, the first cooling channel 25 connects the second air inlet 22 and the third air outlet 23;

[0082] The second cooling channel 26 connects the second air inlet 22 and the fourth air outlet 24 .

[0083] In this embodiment, the first cooling channel 25 and the second cooling channel 26 are symmetrically arranged in the second circular cylinder 21; for the spoiler column with a V-shaped cooling channel arranged inside, when the cooling flow flows into the second air inlet 22, it is divided into two paths, and then flows out from the third air outlet 23 on the top surface of the trailing edge of the second circular cylinder 21 and the fourth air outlet 24 on the bottom surface through the first cooling channel 25 and the second cooling channel 26 respectively, and impacts on the wall surface of the cooling channel inside the turbine blade, thereby strengthening the disturbance of the wall flow field and destroying the reflow area at the trailing edge of the spoiler column, thereby achieving The heat exchange effect at the trailing edge of the spoiler column is improved, so that the spoiler column has a directional enhanced cooling effect, the cooling effect on the surface of the turbine blade at the trailing edge of the spoiler column is enhanced, and the uniform distribution of the surface temperature of the turbine blade is achieved; in this embodiment, the angle between the first cooling channel 25 and the flow direction of the cooling flow and the angle between the second cooling channel 26 and the flow direction of the cooling flow (the flow direction of the cooling flow is the direction in which the cooling flow enters the second air inlet 22 vertically) are the same, and both depend on the column height of the spoiler column; in a preferred embodiment, the angle is 36.87°.

[0084] In an optional embodiment of the present invention, the impact holes 44 are arranged at equal intervals on the suction surface side of the intake cooling channel 42 .

[0085] In this embodiment, the impact holes 44 can be arranged in 4 rows and are evenly spaced along the mainstream flow direction on the suction side of the intake cooling channel 42. The number of impact holes 44 in each row can be determined according to the height and requirements of the blade body 41; the distance between the two impact holes 44 in each row of impact holes 44 and the distance between the two impact holes 44 in two adjacent rows can be determined according to the diameter of the impact hole 44. For example, when the diameter of the impact hole 44 is 1 mm, the ratio of the spacing between the two impact holes 44 in the same row (i.e., the longitudinal spacing) to the diameter can be set to 4.75; the ratio of the spacing between the two impact holes 44 between two adjacent rows (i.e., the lateral spacing) to the diameter can be set to 6.

[0086] In this embodiment, after the cooling flow flows into the intake cooling channel 42, it enters the impact cavity 43 at a relatively high speed through the impact holes 44 on the suction side of the intake cooling channel 42, causing strong disturbances to the boundary layer on the target surface, thinning the boundary layer, and strengthening the mixing of turbulence in other areas of the impact cavity 43; a first spoiler column 45 cooling structure is arranged behind each row of impact holes 44, and after the fluid is disturbed by the first spoiler column 45, the heat exchange area increases, and the low-temperature area continues to diffuse toward the periphery; wherein, the height of the first spoiler column 45 depends on the size of the internal cooling channel, and in the specific setting, the top surface of the first spoiler column 45 is connected to the upper side wall of the impact cavity 43, and the bottom surface of the first spoiler column 45 is connected to the lower side wall of the impact cavity 43; in this embodiment, the diameter of the first spoiler column 45 can be set to 2 mm, the height of the first spoiler column 45 can be set to 0.8 mm, and the two first spoiler columns 45 between two adjacent rows can be connected to each other. 45 and the ratio of the spacing (being the lateral spacing) and the diameter between the first spoiler column 45 and the first spoiler column 45 is 2.5, the ratio of the spacing (being the longitudinal spacing) and the diameter between the two first spoiler columns 45 and the first spoiler column 45 between the same row is 1, the air inlet channel 31 length of the first spoiler column 45 is 1.4mm, and the angle between the 3rd cooling channel 32 and the cooling flow flow direction is 33.69 °; The second spoiler column 47 is set to 4 rows, is positioned in the trailing edge internal cooling channel 46, is staggered, and the number of the second spoiler column 47 in every row can be arranged according to the height of the blade; The second spoiler column 47 diameter can be set to 2mm, the ratio of the spacing (being the lateral spacing) and the diameter between the two second spoiler columns 47 and the second spoiler column 47 between two adjacent rows is 1.5, and the ratio of the spacing (being the longitudinal spacing) and the diameter between the two first spoiler columns 45 and the first spoiler column 45 between the same row is 1.25.

[0087] In an optional embodiment of the present invention, a plurality of rows of the first spoiler columns 45 are disposed in the impact cavity 43 , the first spoiler columns 45 in each row are arranged in a staggered manner, and each first spoiler column 45 is located in the middle of two impact holes 44 .

[0088] In this embodiment, the number of the first spoiler columns 45 can be determined according to the number of the impact holes 44 . Specifically, each first spoiler column 45 is located in the middle of two impact holes 44 , that is, one first spoiler column 45 is required to be provided for every two impact holes 44 .

[0089] In a preferred embodiment, when the size of the impact cavity 43 at the mid-chord area of ​​the blade body 41 is 200*20mm and the wall thickness is 10mm or 15mm, the diameter of the impact hole 44 can be set to 15mm, the ratio of the transverse spacing between the impact holes to the diameter can be set to 5.33, and the ratio of the longitudinal spacing between the impact holes to the diameter can be set to 3.33; the first spoiler columns 45 are arranged in 4 rows, located in the middle of the two rows of impact holes, and the number of the first spoiler columns 45 in each row is set to Depending on the height of the blade, in this embodiment, the diameter of the first spoiler column 45 is 20 mm, the ratio of the height to the diameter of the first spoiler column 45 is set to 1, the ratio of the lateral spacing between the first spoiler column 45 and the first spoiler column 45 to the diameter is set to 2, the ratio of the longitudinal spacing between the first spoiler column 45 and the first spoiler column 45 to the diameter is set to 2.5, the length L of the air inlet channel 31 of the first spoiler column 45 is 8 mm, and the angle between the third cooling channel 32 and the flow direction of the cooling flow is 39.81°

[0090] In an optional embodiment of the present invention, a plurality of rows of second spoiler columns 47 are disposed in the trailing edge internal cooling channel 46 , and the second spoiler columns 47 in each row are arranged in an alternating manner.

[0091] In this embodiment, the ratio of the transverse and longitudinal spacing to the diameter of the second spoiler column 47 can be set according to the specific size of the cooling channel 46 inside the trailing edge; in this embodiment, when the diameter of the first spoiler column 45 is 20 mm, the ratio of the height of the first spoiler column 45 to the diameter is set to 1, the ratio of the transverse spacing between the first spoiler column 45 and the first spoiler column 45 to the diameter is set to 2, the ratio of the longitudinal spacing between the first spoiler column 45 and the first spoiler column 45 to the diameter is set to 2.5, the length L of the air inlet channel 31 of the first spoiler column 45 is 8 mm, and the angle between the third cooling channel 32 and the flow direction of the cooling flow is 39.81°, the ratio of the transverse spacing of the second spoiler column 47 to the diameter is 2, and the ratio of the longitudinal spacing to the diameter is 2.5.

[0092] It is worth noting that the above values ​​are only for the present embodiment, and the diameter, column height, lateral spacing and longitudinal spacing of the spoiler column, as well as the major and minor diameters of the air inlet, and the angle between the cooling channel and the flow direction of the cooling flow can all be set according to the size of the turbine blade cooling channel, and are not unique.

[0093] During operation of the turbine blade of the present invention, after the cooling flow flows into the air intake cooling channel 42, it enters the impact cavity 43 at a relatively high speed through the impact holes 44 on the suction side of the air intake cooling channel 42, causing strong disturbance to the boundary layer on the target surface, making the boundary layer thinner, and strengthening the mixing of turbulent flows in other areas of the impact cavity 43; a first spoiler column 45 cooling structure is arranged behind each row of impact holes 44, and after the fluid is disturbed by the first spoiler column 45, the heat exchange area increases, the low temperature area continues to diffuse toward the periphery, and a small portion of the cooling flow enters the first air inlet 12 on the first spoiler column 45, and then flows out from the top and bottom cooling holes (first The cooling flow flows out from the air outlet 13 and the second air outlet 14, and impacts the wall surface of the impact cavity, which greatly strengthens the disturbance effect of the wall flow field; then the cooling flow flows into the internal cooling channel 46 of the trailing edge of the blade body 41, and the arrangement of the second spoiler column 47 in the internal cooling channel 46 of the trailing edge strengthens the disturbance in the trailing edge channel, and enhances the heat exchange effect of the trailing edge. At the same time, a small part of the cooling flow will enter the first air inlet 12 on the second spoiler column 47, and then flow out from the top and bottom cooling holes (the third air outlet 23 and the fourth air outlet 24) of the trailing edge of the second spoiler column 47, impacting the wall surface of the internal cooling channel of the trailing edge, strengthening the heat exchange, and finally flowing out from the trailing edge slit 48 to merge with the mainstream;

[0094] The cooling structure of the turbine blade described in the present invention is a composite cooling structure of an impact column + a first spoiler column 45 arranged in the internal cooling channel on the suction surface side, and a cooling structure of a second spoiler column 47 arranged in a staggered row is arranged on the trailing edge. This arrangement can give full play to the advantages of the cooling structures of the first spoiler column 45 and the second spoiler column 47, enhance the heat exchange effect of the suction surface and the trailing edge surface of the blade, and make the temperature distribution of the suction surface and the trailing edge of the blade more uniform.

[0095] An embodiment of the present invention provides a cooling structure, comprising:

[0096] A plurality of first spoiler columns 45 and / or a plurality of second spoiler columns 47;

[0097] The first spoiler column 45 is a spoiler column with a Y-shaped cooling channel; the second spoiler column 47 is a spoiler column with a V-shaped cooling channel.

[0098] In an optional embodiment of the present invention, the first spoiler column 45 includes:

[0099] A first circular cylinder 11, wherein a first air inlet 12 is disposed at a front edge of the first circular cylinder 11, and a first air outlet 13 and a second air outlet 14 are disposed at a rear edge of the first circular cylinder 11;

[0100] A Y-shaped cooling channel connecting the first air inlet 12 , the first air outlet 13 , and the second air outlet 14 is defined inside the first circular cylinder 11 .

[0101] In an optional embodiment of the present invention, the first air inlet 12 is arranged at 1 / 2 column height of the front edge of the first circular cylinder 11, the first air outlet 13 is arranged on the top surface of the rear edge of the first circular cylinder 11, and the second air outlet 14 is arranged on the bottom surface of the rear edge of the first circular cylinder 11.

[0102] In an optional embodiment of the present invention, the first air inlet 12 is elliptical, and the major diameter of the cross section of the first air inlet 12 is 1 / 2 of the diameter of the first circular cylinder 11, and the minor diameter is 1 / 2 of the major diameter.

[0103] In an optional embodiment of the present invention, the Y-shaped cooling channel comprises:

[0104] An air inlet channel 31, a third cooling channel 32, and a fourth cooling channel 33 arranged at a second preset angle with the third cooling channel 32, which are arranged inside the first circular cylinder 11;

[0105] Wherein, the air inlet channel 31 is connected to the first air inlet 12;

[0106] The third cooling channel 32 is in communication with the air inlet channel 31 and the first air outlet 13;

[0107] The fourth cooling channel 33 is in communication with the air inlet channel 31 and the second air outlet 14 .

[0108] In an optional embodiment of the present invention, the second spoiler column 47 includes:

[0109] A second circular cylinder 21, wherein a second air inlet 22 is disposed at a front edge of the second circular cylinder 21, and a third air outlet 23 and a fourth air outlet 24 are disposed at a rear edge of the second circular cylinder 21;

[0110] A V-shaped cooling channel connecting the second air inlet 22 , the third air outlet 23 , and the fourth air outlet 24 is defined inside the second circular cylinder 21 .

[0111] In an optional embodiment of the present invention, the V-shaped cooling channel comprises:

[0112] A first cooling channel 25 disposed inside the second circular cylinder 21 and a second cooling channel 26 disposed at a first preset angle with the first cooling channel 25;

[0113] Wherein, the first cooling channel 25 connects the second air inlet 22 and the third air outlet 23;

[0114] The second cooling channel 26 connects the second air inlet 22 and the fourth air outlet 24 .

[0115] The cooling structure described in the present invention can be applied to the cooling system of aviation turbine blades; the circular column structure design of the spoiler column is such that when the cooling flow flows through the circular column of the spoiler column, a horseshoe vortex will be formed at the leading edge of the spoiler column, thereby strengthening the cooling capacity of the leading edge and the two side areas of the spoiler column, and at the same time, a small part of the cooling flow will flow into the V-shaped cooling channel or the Y-shaped cooling channel opened inside the spoiler column through the air inlet, and then flow out from the air outlets on the top and bottom surfaces of the trailing edge of the spoiler column, impacting the wall surface of the cooling channel inside the turbine blade, strengthening the disturbance of the wall flow field, destroying the reflow area at the trailing edge of the spoiler column, and realizing the improvement of the heat exchange effect at the trailing edge of the spoiler column, thereby compensating for the deficiency of the existing circular spoiler column structure in that the heat exchange is weakened due to the reflow generated at the trailing edge, so that the spoiler column has a directional enhanced cooling effect, enhances the cooling effect at the trailing edge of the spoiler column, and realizes the uniform distribution of the surface temperature of the turbine blade.

[0116] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A turbine blade, characterized in that: include: A blade body (41), wherein an air intake cooling channel (42) is arranged at a mid-chord region of the blade body (41), and an impact cavity (43) is arranged inside the blade body (41); The impact cavity (43) is in communication with the air intake cooling channel (42) via a plurality of impact holes (44), wherein the impact holes (44) are arranged on the suction surface side of the air intake cooling channel (42); A trailing edge internal cooling channel (46) is provided inside the trailing edge of the blade body (41), and the trailing edge internal cooling channel (46) is communicated with the impact cavity (43); The trailing edge end of the blade body (41) is provided with a trailing edge slit (48) communicating with the trailing edge internal cooling channel (46); A plurality of spoiler columns are disposed in the impact cavity (43) and the trailing edge internal cooling channel (46), and the spoiler columns include: A plurality of first spoiler columns (45) arranged in the impact cavity (43) and a plurality of second spoiler columns (47) arranged in the cooling channel (46) inside the trailing edge; Wherein, the first spoiler column (45) is a spoiler column with a Y-shaped cooling channel; and the second spoiler column (47) is a spoiler column with a V-shaped cooling channel.

2. The turbine blade according to claim 1, characterized in that The first spoiler column (45) comprises: A first circular cylinder (11), wherein a first air inlet (12) is provided at a front edge of the first circular cylinder (11), and a first air outlet (13) and a second air outlet (14) are provided at a rear edge of the first circular cylinder (11); A Y-shaped cooling channel is provided inside the first circular cylinder (11) and connects the first air inlet (12), the first air outlet (13) and the second air outlet (14).

3. The turbine blade according to claim 2, characterized in that: The first air inlet (12) is arranged at 1 / 2 column height of the front edge of the first circular cylinder (11), the first air outlet (13) is arranged on the top surface of the rear edge of the first circular cylinder (11), and the second air outlet (14) is arranged on the bottom surface of the rear edge of the first circular cylinder (11).

4. The turbine blade according to claim 2, characterized in that: The first air inlet (12) is elliptical, and the major diameter of the cross section of the first air inlet (12) is 1 / 2 of the diameter of the first circular cylinder (11), and the minor diameter is 1 / 2 of the major diameter.

5. The turbine blade according to claim 2, characterized in that: The Y-shaped cooling channel comprises: An air inlet channel (31), a third cooling channel (32), and a fourth cooling channel (33) arranged at a second preset angle with the third cooling channel (32) and arranged inside the first circular cylinder (11); Wherein, the air inlet channel (31) is connected to the first air inlet (12); The third cooling channel (32) is in communication with the air inlet channel (31) and the first air outlet (13); The fourth cooling channel (33) is in communication with the air inlet channel (31) and the second air outlet (14).

6. The turbine blade according to claim 1, characterized in that The second spoiler column (47) comprises: A second circular cylinder (21), wherein a second air inlet (22) is provided at a front edge of the second circular cylinder (21), and a third air outlet (23) and a fourth air outlet (24) are provided at a rear edge of the second circular cylinder (21); A V-shaped cooling channel is provided inside the second circular cylinder (21) and connects the second air inlet (22), the third air outlet (23) and the fourth air outlet (24).

7. The turbine blade according to claim 6, characterized in that The V-shaped cooling channel comprises: a first cooling channel (25) disposed inside the second circular cylinder (21) and a second cooling channel (26) disposed at a first preset angle with the first cooling channel (25); Wherein, the first cooling channel (25) connects the second air inlet (22) and the third air outlet (23); The second cooling channel (26) connects the second air inlet (22) and the fourth air outlet (24).

8. The turbine blade according to claim 1, characterized in that The impact holes (44) are arranged at equal intervals and distributed on the suction surface side of the intake cooling channel (42).

9. The turbine blade according to claim 1, characterized in that A plurality of rows of the first spoiler columns (45) are arranged in the impact cavity (43), the first spoiler columns (45) in each row are arranged in a staggered manner, and each first spoiler column (45) is located in the middle of two impact holes (44).

10. A cooling structure, characterized in that: include: A plurality of first spoiler columns (45) and / or a plurality of second spoiler columns (47); Wherein, the first spoiler column (45) is a spoiler column with a Y-shaped cooling channel; and the second spoiler column (47) is a spoiler column with a V-shaped cooling channel.

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