Blade with half-crack cooling structure and engine

Abstract

The invention provides a blade with a half-crack cooling structure and an engine, and relates to the technical field of aero-engine turbine blades, the blade comprises a blade body, the blade body is provided with a cold air cavity and a crack, an air inlet of the crack communicates with the cold air cavity, and an air outlet of the crack is formed in the pressure face of the blade body and communicates with the outside. The split seam is adjacent to the tail edge of the blade body and is provided with at least one separation rib, the split seam is divided into at least two cold air flow channels by the separation ribs, all the cold air flow channels are arranged at intervals in the first direction, the first direction is the height direction of the blade body, the cold air flow channels extend in the second direction, and an included angle is formed between the second direction and the first direction; and the cross sectional area of the part, close to the air inlet of the crack, of the cold air flow channel is gradually reduced in the direction from the air inlet of the crack to the air outlet. The flow resistance in the cold air flow channel can be reduced, and the smooth degree of cold air entering the cold air flow channel is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine turbine blades, and in particular to a blade and an engine with a half-slit cooling structure. Background Art

[0002] An important way to improve the power performance of aircraft engines is to increase the gas temperature before the turbine. At present, the temperature before the turbine of some advanced aircraft engines has reached 2000K, which is much higher than the temperature limit that the turbine blade material can withstand. Therefore, efficient cooling methods must be used to cool down the key parts of the turbine blade. Among them, the trailing edge of the blade is the weakest part of the blade and is most prone to blade ablation and fracture accidents. Therefore, an effective cooling structure needs to be designed for the trailing edge of the blade.

[0003] The most commonly used method in the related art is to design a half-slit air film cooling structure on the trailing edge of the blade. The principle of the half-slit cooling structure is to cut off part of the wall surface on the pressure side of the trailing edge of the blade, and introduce the cold air in the internal channel of the blade to form a cooling air film on the wall surface after the cut, thereby isolating the trailing edge of the blade from the high-temperature mainstream combustion gas and avoiding direct contact between the two, so as to achieve cooling protection for the trailing edge of the blade. However, the above trailing edge half-slit air film cooling structure still has the following problems in actual use:

[0004] 1. The internal cold air passage of the horizontal exhaust trailing edge split has large flow resistance;

[0005] 2. The ribs between the cold air channels will cause uneven distribution of air film in the downstream area of ​​the blades;

[0006] 3. Uneven mixing of cold air and mainstream gas can easily affect the uniformity of the airflow entering the downstream blades. Summary of the invention

[0007] The present invention aims to solve one of the technical problems in the related art at least to a certain extent.

[0008] To this end, an embodiment of one aspect of the present invention provides a blade with a half-slit cooling structure, which can reduce the flow resistance in the cold air flow channel and improve the smoothness of cold air entering the cold air flow channel.

[0009] Another aspect of the present invention provides an engine.

[0010] According to an embodiment of the present invention, a blade with a semi-split cooling structure includes a blade body, the blade body is provided with a cold air cavity and a split, the air inlet of the split is connected with the cold air cavity, the air outlet of the split is formed on the pressure surface of the blade body and is connected with the outside, the split is adjacent to the trailing edge of the blade body and is provided with a partition rib, the partition rib is at least one and divides the split into at least two cold air flow channels, all of the cold air flow channels are arranged at intervals along a first direction, the first direction is the height direction of the blade body, the cold air flow channels extend along a second direction, the second direction forms an angle with the first direction; the cross-sectional area of ​​the part of the cold air flow channel adjacent to the air inlet of the split gradually decreases in the direction from the air inlet of the split toward the air outlet.

[0011] The blade with a semi-split cooling structure according to the embodiment of the present invention can construct at least two cold air flow channels arranged along its height direction on the blade body through the cooperation of the split on the blade body and the partition ribs in the split, so that the cold air in the cold air cavity can flow into the cold air flow channel from the air inlet of the split, and be led out to the trailing edge of the blade body through the air outlet of the split, forming a cooling air film on the pressure surface of the blade body, isolating the trailing edge of the blade body from the high-temperature mainstream combustion gas, and realizing cooling protection of the trailing edge part of the blade body. At the same time, because the cross-sectional area of ​​the part of the air inlet of the cold air flow channel adjacent to the split gradually decreases in the direction from the air inlet toward the air outlet, that is, the diameter of at least part of the cold air flow channel itself from the inlet toward the outlet gradually decreases, under the action of this structure, the step flow degree on the leeward side of the partition rib is weakened, so the drastic change of the cold air flow velocity can be avoided, so that the cold air can smoothly enter the cold air flow channel. Compared with the related art, the present invention can reduce the flow resistance in the cold air flow channel and improve the smoothness of the cold air entering the cold air flow channel.

[0012] In some embodiments, the cold air flow channel includes a first wall surface and a second wall surface arranged opposite to each other along the first direction, and the first wall surface and the second wall surface each have a first section, a middle section and a second section sequentially connected along the second direction;

[0013] The end of the first section of each of the first wall and the second wall facing away from the middle section is connected to the inner wall of the cold air cavity, and the distance between the first section of the first wall and the first section of the second wall gradually decreases in the direction from the air inlet of the slit toward the air outlet.

[0014] In some embodiments, the first wall surface and the second wall surface are mirror-symmetrical with respect to a reference plane, and the reference plane is perpendicular to the first direction.

[0015] In some embodiments, on the projection plane perpendicular to the third direction, the width of the projection contour line of the inlet of the cold air flow duct is B, and the contraction amplitude of the first segment of each of the first wall surface and the second wall surface is defined as α, and the contraction amplitude is the difference between the projection of the corresponding first segment and the projection of the reference plane at the longest spacing and the shortest spacing, 0.075B≤α≤0.125B, wherein the third direction is perpendicular to both the first direction and the second direction.

[0016] In some embodiments, the length of the cold air flow channel is L, the length of the projection contour line of the first section of each of the first wall surface and the second wall surface on the reference plane is the span length β, and 0.3L≤β≤0.4L.

[0017] In some embodiments, on a projection surface perpendicular to the third direction, a projection contour line of a middle segment of each of the first wall surface and the second wall surface is a first wave line extending along the second direction, and an amplitude of the first wave line is A1, 0.1B≤A1≤0.15B.

[0018] In some embodiments, the wavelength of the first wave line is l1, 0.2L≤l1≤0.25L.

[0019] In some embodiments, the length of the projection contour line of the middle section of each of the first wall surface and the second wall surface on the reference plane is the spanwise length γ, and 0.45L≤γ≤0.55L.

[0020] In some embodiments, the end of the second section of each of the first wall and the second wall facing away from the middle section is connected to the air outlet of the slit, and the distance between the second section of the first wall and the second section of the second wall gradually increases in the direction from the air inlet of the slit toward the air outlet.

[0021] In some embodiments, on the projection surface perpendicular to the third direction, the expansion amplitude of the second segment of each of the first wall surface and the second wall surface is defined as λ, and the expansion amplitude is the difference between the projection of the corresponding second segment and the projection of the reference plane at the longest spacing and the shortest spacing, 0.1B≤λ≤0.15B.

[0022] In some embodiments, the length of the second segment of each of the first wall and the second wall is s, 0.1L≤s≤0.15L.

[0023] In some embodiments, the cold air flow channel further includes a third wall surface, the third wall surface is opposite to the third direction and is located between the first wall surface and the second wall surface, and the third wall surface is connected to the inner wall surface of the cold air cavity and the air outlet of the split slit;

[0024] On a projection surface perpendicular to the first direction, a projection contour line of the third wall surface is a second wave line extending along the second direction, and an amplitude of the second wave line is A2, 0.175B≤A2≤0.225B.

[0025] In some embodiments, the wavelength of the second wave line is l2, 0.225B≤l2≤0.275B.

[0026] In some embodiments, the pressure surface and the suction surface of the blade body form a trailing edge extending along the first direction at the connection of the trailing edge, the height of the blade body is H, and on the projection surface perpendicular to the third direction, the projection contour line of the trailing edge is a third wave line extending along the first direction, the amplitude of the third wave line is A3, 0.05H≤A3≤0.1H.

[0027] In some embodiments, the wavelength of the third wave line is l3, 0.15H≤l3≤0.2H.

[0028] An engine according to an embodiment of the present invention comprises the blades described in any one of the above embodiments.

[0029] The technical advantages of the engine according to the embodiment of the present invention are the same as the technical advantages of the above-mentioned blades, which will not be repeated here.

[0030] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 is a schematic structural diagram of a blade with a half-slit cooling structure according to an embodiment of the present invention.

[0032] Figure 2 yes Figure 1 Schematic diagram of the cross-sectional structure.

[0033] Figure 3 It is a schematic structural diagram of the partition ribs and the cold air flow channel portion in a blade with a half-slit cooling structure according to an embodiment of the present invention.

[0034] Figure 4 yes Figure 3 The cross-sectional structure of Figure 1 .

[0035] Figure 5 yes Figure 3 The cross-sectional structure of Figure 2 .

[0036] Reference numerals:

[0037] 1. Blade body, 11. Pressure surface, 12. Suction surface, 13. Trailing edge;

[0038] 2. Cold air cavity;

[0039] 3. Split, 31. Air inlet of the split, 32. Air outlet of the split;

[0040] 4. Separation ribs;

[0041] 5. cold air flow channel, 51. first wall surface, 52. second wall surface, 53. third wall surface. DETAILED DESCRIPTION

[0042] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0043] like Figures 1 to 4 As shown, a blade with a semi-split cooling structure according to an embodiment of the present invention includes a blade body 1, the blade body 1 is provided with a cold air cavity 2 and a split 3, the air inlet 31 of the split slit is connected to the cold air cavity 2, the air outlet 32 ​​of the split slit is formed on the pressure surface 11 of the blade body 1 and is connected to the outside, the split slit 3 is adjacent to the trailing edge of the blade body 1 and is provided with a partition rib 4, there is at least one partition rib 4 and the split slit 3 is divided into at least two cold air flow channels 5, all the cold air flow channels 5 are arranged at intervals along a first direction, the first direction is the height direction of the blade body 1, the cold air flow channels 5 extend along a second direction, the second direction forms an angle with the first direction; the cross-sectional area of ​​the portion of the cold air flow channel 5 adjacent to the air inlet 31 of the split slit gradually decreases along the direction from the air inlet 31 of the split slit toward the air outlet 32 ​​of the split slit.

[0044] It can be understood that, according to the blade with a semi-slit cooling structure according to the embodiment of the present invention, by cooperating with the slit 3 on the blade body 1 and the partition rib 4 in the slit 3, at least two cold air flow channels 5 arranged along the height direction can be constructed on the blade body 1, so that the cold air in the cold air cavity 2 can flow into the cold air flow channel 5 from the air inlet 31 of the slit, and be led out to the trailing edge of the blade body 1 through the air outlet 32 ​​of the slit, forming a cooling air film on the pressure surface 11 of the blade body 1, isolating the trailing edge of the blade body 1 from the high-temperature mainstream combustion gas, and achieving the purpose of cooling the blade body 1. The cooling protection of the trailing edge portion is provided. At the same time, the cross-sectional area of ​​the portion of the air inlet 31 of the cold air flow duct 5 adjacent to the split gradually decreases in the direction from the air inlet toward the air outlet, that is, the diameter of at least part of the cold air flow duct 5 itself from the inlet toward the outlet gradually decreases. Under the action of this structure, the step flow degree on the leeward side of the dividing rib 4 is weakened, so the drastic change of the cold air flow velocity can be avoided, so that the cold air can smoothly enter the cold air flow duct 5. Compared with the related art, the present invention can reduce the flow resistance in the cold air flow duct 5 and improve the smoothness of the cold air entering the cold air flow duct 5.

[0045] In addition, the inlet of the cold air flow duct 5 is a part of the air inlet 31 of the slit, and the outlet of the cold air flow duct 5 is a part of the air outlet 32 ​​of the slit. In other words, the inlet of the cold air flow duct 5 is located in the air inlet 31 of the slit, and the outlet of the cold air flow duct 5 is located in the air outlet 32 ​​of the slit.

[0046] Specifically, the cold air cavity 2 and the slit 3 can both extend along the first direction. There can be a plurality of partition ribs 4 to divide the slit 3 into a plurality of cold air flow channels 5, wherein the plurality of partition ribs 4 can be arranged at equal intervals or unequal intervals along the first direction, and in order to ensure the cooling and protective effect of the cooling air film on the trailing edge of the blade, so that the air film in the downstream area of ​​the blade (that is, the part of the blade adjacent to the trailing edge) is evenly distributed, it is preferred that the plurality of partition ribs 4 are arranged at equal intervals along the first direction, that is, the plurality of partition ribs 4 are evenly distributed along the blade height direction.

[0047] It should be noted that the cold air cavity 2 is not limited to being suitable for passing cooling air, and other working fluids that can be used to cool the blades can also be used, and no specific limitation is made here.

[0048] like Figures 3 to 5 As shown, in some embodiments, the cold air flow channel 5 includes a first wall 51 and a second wall 52 arranged opposite to each other along a first direction, and the first wall 51 and the second wall 52 both have a first section, a middle section and a second section sequentially connected along a second direction.

[0049] The end of the first section of each of the first wall surface 51 and the second wall surface 52 away from the middle section is connected to the inner wall surface of the cold air cavity 2, wherein the inner wall surface of the cold air cavity 2 is the inner wall surface of the blade body 1 used to surround the cold air cavity 2. The distance between the first section of the first wall surface 51 and the first section of the second wall surface 52 gradually decreases in the direction from the air inlet 31 of the split slit toward the air outlet 32 ​​of the split slit, that is, the distance between the two changes smoothly in the direction from the inlet to the outlet of the cold air flow channel 5 and gradually becomes smaller.

[0050] It can be understood that the first section of the first wall 51 and the first section of the second wall 52 in the cold air flow duct 5 construct a tapered portion of the cold air flow duct 5 in the slit 3, and the middle section of the two can construct the middle portion of the cold air flow duct 5 in the slit 3, and the tapered portion is connected to the cold air cavity 2 (that is, the tapered portion is formed with the inlet of the cold air flow duct 5). The tapered portion structure can weaken the step flow degree on the leeward side of the partition rib 4 at the inlet of the cold air flow duct 5, thereby avoiding drastic changes in flow velocity.

[0051] Specifically, the thickness direction of the partition rib 4 may be consistent with the first direction. In this case, one of the two opposite walls of the partition rib 4 along the thickness direction may be the first wall 51 , and the other wall may be the second wall 52 .

[0052] like Figures 3 to 5 As shown, in some embodiments, the first wall surface 51 and the second wall surface 52 are mirror-symmetrical relative to a reference plane, and the reference plane is perpendicular to the first direction.

[0053] It can be understood that the first wall 51 and the second wall 52 of the cold air flow duct 5 are designed to adopt the above-mentioned mirror-symmetrical structure, which facilitates the processing and forming of the cold air flow duct 5, reduces the production cost, and can further ensure the uniformity of the air film distribution in the downstream area of ​​the blade, thereby improving the protection effect of the trailing edge wall of the blade.

[0054] Furthermore, on the projection plane perpendicular to the third direction, the width of the projection contour line of the inlet of the cold air flow channel 5 is B, and the contraction amplitude of the first section of each of the first wall surface 51 and the second wall surface 52 is defined as α, and the contraction amplitude is the difference between the projection of the corresponding first section and the projection of the reference plane at the longest spacing and the shortest spacing, 0.075B≤α≤0.125B, wherein the third direction is perpendicular to both the first direction and the second direction. That is, along the flow direction of the cold air (or in the direction from the inlet to the outlet of the cold air flow channel 5), the two opposite walls of the partition rib 4 along the thickness direction gradually approach the center line direction of the cold air flow channel 5 at the first section.

[0055] In other words, since the first wall 51 and the second wall 52 are mirror-symmetrical, the shrinkage amplitude of the first segment of each of the first wall 51 and the second wall 52 is equal, wherein the shrinkage amplitude is the difference between the projection of the corresponding first segment and the projection of the reference plane at the longest distance and the shortest distance, that is, the longest distance between the projection of the first segment of the first wall 51 (or the first segment of the second wall 52) and the projection of the reference plane, minus the shortest distance between the projection of the first segment of the first wall 51 (or the first segment of the second wall 52) and the projection of the reference plane, to obtain the shrinkage amplitude α.

[0056] Furthermore, the length of the cold air flow channel 5 is L, the length of the projection contour line of the first section of each of the first wall surface 51 and the second wall surface 52 on the reference plane is the spanwise length β, and 0.3L≤β≤0.4L.

[0057] It can be understood that by designing the contraction amplitude and the span length of the tapered portion within the above range, the cold air can smoothly enter the cold air flow channel 5 from the cold air cavity 2 , thereby reducing the flow resistance at the inlet of the cold air flow channel 5 .

[0058] For example, the contraction amplitude of a single partition rib 4 may be 0.01 times the width of the inlet of the cold air flow channel 5 , and the spanwise length of the tapered portion may be 0.35 times the length of the cold air flow channel 5 .

[0059] like Figure 5As shown, in some embodiments, on the projection surface perpendicular to the third direction, the projection contour line of the middle section of each of the first wall surface 51 and the second wall surface 52 is a first wave line extending along the second direction, and the amplitude of the first wave line is A1, 0.1B≤A1≤0.15B. In other words, the middle section of each of the first wall surface 51 and the second wall surface 52 is a first wave-shaped (or concave-convex structure) wall surface extending along the flow direction of the cold air.

[0060] Furthermore, the wavelength of the first wave line is l1, 0.2L≤l1≤0.25L.

[0061] Further, the length of the projection contour line of the middle section of each of the first wall surface 51 and the second wall surface 52 on the reference plane is the spanwise length γ, and 0.45L≤γ≤0.55L.

[0062] It can be understood that the middle section of each of the first wall 51 and the second wall 52 adopts a first wavy wall extending along the flow direction of the cold air, which increases the contact area between the cold air flow duct 5 and the cold air and enhances the heat dissipation effect of the cold air flow duct 5. At the same time, the middle part of the cold air flow duct 5 is within the above-mentioned design parameter range, which can further improve the heat exchange performance of the trailing edge of the blade compared with the relevant technology.

[0063] For example, the amplitude of the first wavy wall surface may be 0.125 times the width of the inlet of the cold flow channel 5 , the wavelength may be 0.225 times the length of the cold flow channel 5 , and the span length may be 0.5 times the length of the cold flow channel 5 .

[0064] like Figures 2 to 5 As shown, in some embodiments, the end of the second section of each of the first wall 51 and the second wall 52 away from the middle section is connected to the air outlet 32 ​​of the split slit, and the distance between the second section of the first wall 51 and the second section of the second wall 52 gradually increases in the direction from the air inlet 31 of the split slit toward the air outlet. In other words, along the flow direction of the cold air, the two walls of the partition rib 4 facing each other along the thickness direction gradually move away from the center line direction of the cold air flow channel 5 at the second section. In other words, the second section of the first wall 51 and the second section of the second wall 52 in the cold air flow channel 5 form a gradually expanding portion of the cold air flow channel 5 in the split slit 3.

[0065] It can be understood that designing the outlet of the cold air flow channel 5 as an expansion structure can make the cooling air film in the downstream area of ​​the blade more evenly distributed, avoid the uneven distribution of the air film caused by multiple partition ribs 4, and better protect the trailing edge wall of the blade.

[0066] Furthermore, on the projection surface perpendicular to the third direction, the expansion amplitude of the second segment of each of the first wall 51 and the second wall 52 is defined as λ, and the expansion amplitude is the difference between the projection of the corresponding second segment and the projection of the reference plane at the longest spacing and the shortest spacing, 0.1B≤λ≤0.15B.

[0067] Among them, the expansion amplitude is the difference between the projection of the corresponding second segment and the projection of the reference plane at the longest distance and the shortest distance, that is, the longest distance between the projection of the second segment of the first wall 51 (or the second segment of the second wall 52) and the projection of the reference plane, minus the shortest distance between the projection of the second segment of the first wall 51 (or the second segment of the second wall 52) and the projection of the reference plane, to obtain the contraction amplitude λ.

[0068] Furthermore, the length of the second section of each of the first wall surface 51 and the second wall surface 52 is s, and 0.1L≤s≤0.15L.

[0069] It can be understood that the expansion amplitude and length of the gradually expanding portion are designed to be within the above range, which can further ensure that the cooling air film forms a good cooling protection coverage at the trailing edge of the blade compared to the related art.

[0070] For example, the expansion amplitude of a single partition rib 4 may be 0.125 times the width of the inlet of the cold air flow channel 5 , and the length of the gradually expanding portion may be 0.15 times the length of the cold air flow channel 5 .

[0071] like Figures 3 to 5 As shown, in some embodiments, the cold air flow duct 5 also includes a third wall 53, which is opposite to the third direction and is located between the first wall 51 and the second wall 52, and the third wall 53 is connected to the inner wall surface of the cold air cavity 2 and the air outlet 32 ​​of the split, that is, the third wall 53 is the bottom wall of the groove of the cold air flow duct 5.

[0072] On the projection surface perpendicular to the first direction, the projection contour line of the third wall surface 53 is a second wave line extending along the second direction, and the amplitude of the second wave line is A2, 0.175B≤A2≤0.225B. In other words, the third wall surface 53 is a second wave-shaped (or concave-convex structure) wall surface extending along the flow direction of the cold air.

[0073] Furthermore, the wavelength of the second wave line is l2, 0.225B≤l2≤0.275B.

[0074] It can be understood that the third wall 53 is distributed between the first wall 51 and the second wall 52, and there are wavy recesses and protrusions arranged at intervals along the flow direction of the cold air, which increases the contact area between the cold air flow duct 5 and the cold air. Based on the structural design of the first wall 51 and the second wall 52, the heat dissipation effect of the cold air flow duct 5 can be further enhanced, while promoting the mixing performance between the cold air outflow and the mainstream of the fuel gas, thereby improving the uniformity of the airflow and temperature distribution at the downstream blade inlet.

[0075] For example, the amplitude of the second wavy wall surface may be 0.2 times the width of the inlet of the cold air flow channel 5 , and the wavelength may be 0.25 times the width of the inlet of the cold air flow channel 5 .

[0076] like Figures 1 to 5 As shown, in some embodiments, the pressure surface 11 and the suction surface 12 of the blade body 1 form a trailing edge 13 extending along the first direction at the connection of the trailing edge, the height of the blade body 1 is H, and on the projection surface perpendicular to the third direction, the projection contour line of the trailing edge 13 is a third wave line extending along the first direction, the amplitude of the third wave line is A3, 0.05H≤A3≤0.1H. In other words, the trailing edge 13 is a third wave-shaped (or concave and convex structure) wall extending along the blade height direction.

[0077] Furthermore, the wavelength of the third wave line is l3, 0.15H≤l3≤0.2H.

[0078] It can be understood that the trailing edge 13 is applied to the junction of the trailing edges of the pressure side 11 and the suction side 12 of the blade, and has wavy depressions and protrusions arranged at intervals along the blade height direction, which increases the heat exchange area of ​​the trailing edge of the blade and improves the heat exchange capacity of the weak point of the trailing edge of the blade.

[0079] For example, the amplitude of the third wavy wall surface may be 0.07 times the height of the blade body 1 , and the wavelength may be 0.17 times the height of the blade body 1 .

[0080] It should be noted that the optimal values ​​of all the above parameters can be obtained with the help of existing computational fluid dynamics software numerical simulation or related experiments.

[0081] Furthermore, a first wavy edge is formed at the connection between the second section of each of the first wall 51 and the second wall 52 and the air outlet 32 ​​of the slit on the pressure surface 11 of the blade body 1, and the first wavy edge extends along the blade profile direction of the pressure surface 11 of the blade body 1. A second wavy edge is formed at the connection between the third wall 53 and the inner wall of the cold air cavity 2, and at the connection between the third wall 53 and the air outlet 32 ​​of the slit on the pressure surface 11 of the blade body 1, and the second wavy edge extends along the first direction.

[0082] Therefore, when the first wall 51, the second wall 52, the third wall 53 and the trailing edge 13 all adopt the above-mentioned structural design, the partition rib 4, the third wall 53 and the trailing edge 13 can all be bionic structures (such as bionic bird flapping wing structures), which solves the technical problems such as large flow resistance of the cold air flow duct 5 inside the horizontal exhaust trailing edge slit 3, uneven distribution of the air film in the downstream area of ​​the slit 3, and uneven airflow on the downstream blades. It reduces the flow resistance in the cold air flow duct 5, improves the heat dissipation effect of the cold air flow duct 5, homogenizes the distribution of the cooling air film in the downstream area of ​​the blades, improves the turbine cooling performance, and improves the uniformity of the airflow entering the downstream blades.

[0083] An engine according to an embodiment of the present invention comprises the blade according to any one of the above embodiments.

[0084] The technical advantages of the engine according to the embodiment of the present invention are the same as the technical advantages of the above-mentioned blades, which will not be repeated here.

[0085] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0086] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0087] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0088] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0089] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0090] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A blade with a half-slit cooling structure, characterized in that: The blade body comprises a blade body, wherein the blade body is provided with a cold air cavity and a slit, an air inlet of the slit is connected with the cold air cavity, an air outlet of the slit is formed on the pressure surface of the blade body and is connected with the outside, the slit is adjacent to the trailing edge of the blade body and is provided with a partition rib, the partition rib is at least one and divides the slit into at least two cold air flow channels, all the cold air flow channels are arranged at intervals along a first direction, the first direction is the height direction of the blade body, the cold air flow channels extend along a second direction, and the second direction forms an angle with the first direction; A cross-sectional area of ​​a portion of the cold air flow channel adjacent to the air inlet of the slit gradually decreases in a direction from the air inlet of the slit toward the air outlet.

2. The blade with a half-slit cooling structure according to claim 1, characterized in that: The cold air flow channel comprises a first wall surface and a second wall surface arranged opposite to each other along the first direction, wherein the first wall surface and the second wall surface both comprise a first section, a middle section and a second section sequentially connected along the second direction; The end of the first section of each of the first wall and the second wall facing away from the middle section is connected to the inner wall of the cold air cavity, and the distance between the first section of the first wall and the first section of the second wall gradually decreases in the direction from the air inlet of the slit toward the air outlet.

3. The blade with a half-slit cooling structure according to claim 1 or 2, characterized in that: The first wall surface and the second wall surface are mirror-symmetrical with respect to a reference plane, and the reference plane is perpendicular to the first direction.

4. The blade with a half-slit cooling structure according to claim 3, characterized in that: On the projection plane perpendicular to the third direction, the width of the projection contour line of the inlet of the cold air flow channel is B, and the contraction amplitude of the first segment of each of the first wall surface and the second wall surface is defined as α, and the contraction amplitude is the difference between the projection of the corresponding first segment and the projection of the reference plane at the longest spacing and the shortest spacing, 0.075B≤α≤0.125B, wherein the third direction is perpendicular to both the first direction and the second direction; And / or, the length of the cold air flow channel is L, the length of the projection contour line of the first section of each of the first wall surface and the second wall surface on the reference plane is the span length β, and 0.3L≤β≤0.4L.

5. The blade with a half-slit cooling structure according to claim 4, characterized in that: On a projection surface perpendicular to the third direction, a projection contour line of a middle section of each of the first wall surface and the second wall surface is a first wave line extending along the second direction, and an amplitude of the first wave line is A1, 0.1B≤A1≤0.15B; And / or, the wavelength of the first wave line is l1, 0.2L≤l1≤0.25L. And / or, the length of the projection contour line of the middle section of each of the first wall surface and the second wall surface on the reference plane is the span length γ, and 0.45L≤γ≤0.55L.

6. The blade with a half-slit cooling structure according to claim 4, characterized in that: The end of the second section of each of the first wall and the second wall facing away from the middle section is connected to the air outlet of the slit, and the distance between the second section of the first wall and the second section of the second wall gradually increases in the direction from the air inlet of the slit toward the air outlet.

7. The blade with a half-slit cooling structure according to claim 6, characterized in that: On a projection plane perpendicular to the third direction, define the expansion amplitude of the second segment of each of the first wall surface and the second wall surface as λ, wherein the expansion amplitude is the difference between the projection of the corresponding second segment and the projection of the reference plane at the longest spacing and the shortest spacing, 0.1B≤λ≤0.15B; And / or, the length of the second segment of each of the first wall surface and the second wall surface is s, 0.1L≤s≤0.15L.

8. The blade with a half-slit cooling structure according to any one of claims 4 to 7, characterized in that: The cold air flow channel further includes a third wall surface, the third wall surface is opposite to the third direction and is located between the first wall surface and the second wall surface, and the third wall surface is connected to the inner wall surface of the cold air cavity and the air outlet of the split slit; On a projection surface perpendicular to the first direction, a projection contour line of the third wall surface is a second wave line extending along the second direction, and an amplitude of the second wave line is A2, 0.175B≤A2≤0.225B; And / or, the wavelength of the second wave line is l2, 0.225B≤l2≤0.275B.

9. The blade with a half-slit cooling structure according to claim 8, characterized in that: The pressure surface and the suction surface of the blade body form a trailing edge extending along the first direction at the connection of the trailing edge, the height of the blade body is H, and on the projection surface perpendicular to the third direction, the projection contour line of the trailing edge is a third wave line extending along the first direction, the amplitude of the third wave line is A3, 0.05H≤A3≤0.1H; And / or, the wavelength of the third wave line is l3, 0.15H≤l3≤0.2H.

10. An engine, characterized in that: The engine comprises the blade according to any one of claims 1-9.

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