Turbine blade and gas turbine

Abstract

This invention provides a turbine blade and a gas turbine. The turbine blade includes a blade body. The blade body includes a suction surface, a pressure surface, a suction side rib, and a pressure side rib; the suction side rib is disposed on the suction surface at the tip of the turbine blade, and the pressure side rib is disposed on the pressure surface at the tip of the turbine blade, forming a tip groove; the turbine blade also includes an outer blade tip surface disposed at the tip of the turbine blade; the bottom edge of the suction side rib and the tip edge of the suction surface are connected through the outer blade tip surface, and the bottom edge of the pressure side rib and the tip edge of the pressure surface are connected through the outer blade tip surface; the suction side rib is inclined from the outer blade tip surface to the suction surface, forming a first angle with the outer blade tip surface, and a suction side groove is formed between the outer surface of the suction side rib and the tip surface; the pressure side rib is inclined from the outer blade tip surface to the pressure surface, forming a second angle with the outer blade tip surface, and a pressure side groove is formed between the outer surface of the pressure side rib and the tip surface. The above-described turbine blade can reduce tip leakage flow.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more particularly to a turbine blade and a gas turbine. Background Technology

[0002] A gas turbine engine typically consists of an intake manifold, compressor, combustion chamber, turbine, and exhaust nozzle. Air enters the engine through the intake manifold, is compressed into high-pressure air by the compressor, and then mixes with fuel in the combustion chamber to produce high-temperature, high-pressure combustion gas. This gas drives the turbine to perform work and provide power, and is finally exhausted from the engine through the exhaust nozzle. The turbine blades, as a crucial component of the gas turbine engine, reflect the engine's performance level based on their efficiency.

[0003] A turbine typically consists of a rotating disk and multiple turbine blades extending from it, with the blades surrounded by a stationary casing. Due to the relative motion between the rotating turbine blades and the stationary casing, a gap inevitably exists between the turbine blade tips and the casing. Some of the high-temperature combustion gas flows through this gap under the influence of circumferential and axial pressure differences, forming a tip leakage flow. This leakage flow does almost no useful work, resulting in leakage losses. After exiting the gap, the leakage flow forms leakage vortices, mixing with the main flow and causing mixing losses. The leakage flow also generates friction losses as it flows through the blade tips and casing. All these losses contribute to a reduction in turbine aerodynamic efficiency.

[0004] Currently, the most widely used blade tip structures are the straight-rib double-rib structure and the pressure-side oblique-rib structure. The straight-rib double-rib structure includes pressure-side and suction-side straight ribs, forming a tip cavity between the pressure-side and suction-side ribs and the blade tip. The pressure-side oblique-rib structure is based on the straight-rib double-rib structure, with the pressure-side ribs angled while the suction-side straight ribs remain unchanged. Both the straight-rib double-rib and pressure-side oblique-rib structures reduce external mixing losses in the leakage flow by blocking the leakage flow through various vortex structures formed within the tip grooves.

[0005] However, the two structures mentioned above can only reduce the turbine tip leakage flow to a certain extent, and their obstruction effect on the tip leakage flow is limited. Summary of the Invention

[0006] The purpose of this invention is to provide a turbine blade and a gas turbine that can reduce tip leakage flow, improve aerodynamic performance, and increase turbine blade aerodynamic efficiency.

[0007] One aspect of the present invention provides a turbine blade including a blade body, the blade body including a suction surface, a pressure surface, a suction side rib, and a pressure side rib; the suction side rib is disposed on the suction surface at the tip of the turbine blade, the pressure side rib is disposed on the pressure surface at the tip of the turbine blade, the suction side rib and the pressure side rib form a tip groove; the turbine blade also includes an outer blade top surface disposed at the tip of the turbine blade; the bottom edge of the suction side rib and the tip edge of the suction surface are connected through the outer blade top surface, the bottom edge of the pressure side rib and the tip edge of the pressure surface are connected through the outer blade top surface; the suction side rib is inclined from the outer blade top surface to the suction surface and forms a suction side groove with the outer blade top surface; the pressure side rib is inclined from the outer blade top surface to the pressure surface and forms a pressure side groove with the outer blade top surface; the suction side groove and the pressure side groove provide a guiding function, thereby guiding at least a portion of the high-temperature combustion gas entering the suction side groove and the pressure side groove to the tip edge.

[0008] In one embodiment, a first angle is formed between the outer surface of the suction rib and the top surface of the outer blade, the first angle gradually increasing from the leading edge of the blade tip to the trailing edge of the blade tip; and / or

[0009] A second included angle is formed between the outer surface of the pressure side rib and the top surface of the outer leaf, and the second included angle gradually increases from the leading edge of the leaf tip to the trailing edge of the leaf tip.

[0010] In one embodiment, the value of the first included angle and / or the second included angle at the leading edge of the leaf tip is 30° to 80°.

[0011] In one embodiment, the width of the top surface of the outer blade forming the suction-side groove and / or the top surface of the outer blade forming the pressure-side groove gradually decreases from the leading edge of the blade tip to the trailing edge of the blade tip.

[0012] In one embodiment, the ratio of the width of the top surface of the outer blade forming the suction-side groove to the width of the top surface of the rib of the suction-side rib is 0.4 to 1.3; and / or the ratio of the width of the top surface of the outer blade forming the pressure-side groove to the width of the top surface of the rib of the pressure-side rib is 0.4 to 1.3.

[0013] In one embodiment, the suction-side groove extends from the leading edge of the blade tip to the region of maximum thickness of the blade body, and the pressure-side groove extends from the leading edge of the blade tip to the trailing edge of the blade tip.

[0014] In one embodiment, the suction-side groove extends from the leading edge of the blade tip by a distance of 10% to 50% of the chord length of the blade.

[0015] In one embodiment, the outer surface of the suction side rib is rounded between the top surface of the outer blade forming the suction side groove and between the top surface of the outer blade forming the suction side groove and the suction surface; and / or the outer surface of the pressure side rib is rounded between the top surface of the outer blade forming the pressure side groove and between the top surface of the outer blade forming the pressure side groove and the pressure surface.

[0016] In one embodiment, a trailing edge slit is provided at the trailing edge of the blade tip, and the trailing edge slit is located on the suction surface or the pressure surface.

[0017] Another aspect of the present invention provides a gas turbine comprising the turbine blades described in any of the preceding claims.

[0018] The turbine blades of this invention utilize inclined suction and pressure ribs. This allows a portion of the high-temperature combustion gas from the combustion chamber to pass over these ribs and enter the tip groove under the influence of circumferential and axial pressure differences. This increases the inlet turning angle of the leakage flow, resulting in a larger separation vortex range on the rib top surface. Consequently, the actual flow area between the rib top surface and the casing is reduced, thus decreasing the leakage flow rate. The suction and pressure side grooves also act as guides, partially directing the fluid entering the grooves towards the turbine blade trailing edge, further reducing the amount of high-temperature combustion gas entering. This reduces losses caused by turbine tip leakage, increases the amount of gas used for useful work, and improves turbine efficiency. Attached Figure Description

[0019] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein:

[0020] Figure 1 This is a schematic diagram of the typical leakage flow velocity vector at the tip clearance of a turbine blade;

[0021] Figure 2 This is a schematic diagram of a turbine blade before the improvement;

[0022] Figure 3 This is a schematic diagram of another turbine blade before the improvement;

[0023] Figure 4 This is a schematic diagram of an embodiment of a turbine blade according to the present invention;

[0024] Figure 5 yes Figure 4 A schematic diagram of the blade tip of a turbine blade is shown.

[0025] Figure 6 yes Figure 5 A schematic diagram showing another perspective of the leaf tip;

[0026] Figure 7 yes Figure 6 The cross-sectional view at the leading edge of the blade tip is shown below;

[0027] Figure 8 yes Figure 7 A cross-sectional view of the suction or pressure ribs at the blade tip is shown.

[0028] Figure 9 This is a schematic diagram of another embodiment of a turbine blade according to the present invention;

[0029] Figure 10 yes Figure 8 A schematic diagram of the planar streamlines of the suction side rib or the pressure side rib;

[0030] Figure 11 This is an embodiment of a turbine blade according to the present invention and Figure 3 The diagram shows a comparison of the radial distribution of total pressure loss at the turbine outlet before and after the improvement.

[0031] Figure 12a yes Figure 3 The diagram shows the limiting streamlines of the suction surface of the turbine blade before the improvement.

[0032] Figure 12b yes Figure 9 A schematic diagram of the limiting streamlines of the suction surface of the turbine blade is shown.

[0033] Figure 13 This is a schematic diagram of the turbine rotor assembly. Detailed Implementation

[0034] A gas turbine engine (also known as a gas turbine) is an internal combustion engine that uses a continuously flowing gas as its working fluid to drive a high-speed rotating impeller, converting the energy of the fuel into useful work. It can be used in aviation, marine, or power generation, and typically consists of an intake, compressor, combustion chamber, turbine, and exhaust nozzle. Air enters the engine through the intake, is compressed into high-pressure air by the compressor, and then mixes and burns with fuel in the combustion chamber to produce high-temperature, high-pressure gas. This gas drives the turbine to perform work and provide power, and is finally exhausted from the engine through the exhaust nozzle. The turbine blades are a crucial component of the gas turbine engine, and their efficiency reflects the engine's performance level.

[0035] A turbine typically consists of a rotating disk and multiple turbine blades extending from it, with the blades surrounded by a stationary casing. Due to the relative motion between the rotating turbine blades and the stationary casing, a gap inevitably exists between the turbine blade tip and the casing. Some of the high-temperature combustion gas flows through this gap under the influence of circumferential and axial pressure differences, forming a tip leakage flow. This leakage flow does almost no useful work, resulting in leakage losses. After exiting the gap, the leakage flow forms leakage vortices, mixing with the main flow and causing mixing losses. The leakage flow also generates friction losses as it flows through the blade tip and casing. All these losses contribute to a decrease in turbine aerodynamic efficiency. Under different operating conditions of a gas turbine engine, the temperature and rotational speed of the turbine blades vary greatly, resulting in significant variations in blade elongation and consequently, changes in the clearance size. Typically, the clearance between the tip and casing of an axial turbine is on the order of 1% to 2% of the blade height. Studies have shown that a 1 mm increase in tip clearance leads to a decrease in turbine efficiency of approximately 2.5% and an increase in fuel consumption of the gas turbine engine of approximately 2.6%.

[0036] Figure 1 A typical velocity vector diagram of the blade tip leakage flow is shown. The blade tip 4 includes the leading edge 40, pressure surface 4-1, suction surface 4-2, trailing edge 43, and tip surface 44. Under the influence of circumferential and axial pressure differences, high-temperature, high-pressure combustion gases enter the gap from the portion of the suction surface 4-2 near the leading edge 43 and the portion of the pressure surface 4-1, and flow out of the gap from the middle of the suction surface 4-2 to the trailing edge 43, forming a leakage flow.

[0037] Currently, the most widely used blade tip 4 structures are the straight rib double rib structure and the pressure side oblique rib structure.

[0038] like Figure 2 As shown, the blade tip 4 of the straight-rib double-rib structure includes a pressure-side straight rib 41a and a suction-side straight rib 41b. A blade tip groove is formed between the pressure-side straight rib 41a, the suction-side straight rib 41b, and the blade tip surface 44. This structure can reduce the turbine blade tip leakage flow to a certain extent.

[0039] like Figure 3 As shown, the blade tip 4 of the pressure-side inclined rib structure is based on the straight rib double rib structure, with the pressure-side ribs inclined to form pressure-side inclined ribs 41c, while the suction-side straight ribs 41b remain unchanged. The blade tip 4 of both the straight rib double rib structure and the pressure-side inclined rib structure reduces the external mixing loss of the leakage flow by blocking the leakage flow through various vortex structures formed in the blade tip groove.

[0040] However, the two structures mentioned above can only reduce the turbine tip leakage flow to a certain extent, and their obstruction effect on the tip leakage flow is limited.

[0041] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Each example is provided to explain the invention and not to limit it. In fact, it will be apparent to those skilled in the art that various modifications and variations may be made to the invention without departing from the scope or spirit thereof. For example, a feature shown or described as part of one embodiment may be used with another embodiment to produce yet another embodiment. Therefore, the invention is intended to cover these modifications and variations that fall within the scope of the appended claims and their equivalents.

[0042] The embodiments described later are in Figures 2 to 3 Improvements were made based on the turbine blades shown. Figure 4 and Figure 5 The structure of the turbine blade of the present invention is shown. A turbine typically consists of a rotating disk and multiple turbine blades extending from the disk. The turbine blades are surrounded by a stationary casing, and there is relative motion between the turbine blades and the stationary casing when the turbine blades rotate. Figure 4 The turbine blade of the present invention shown includes a tenon 1, a flange 2, and a blade body 3 connected to the flange 2. The blade body 3 includes a suction surface 4-2, a pressure surface 4-1, a suction side rib, and a pressure side rib. A suction side rib 42 is provided on the suction surface 4-2 at the blade tip 4 of the turbine blade, and a pressure side rib 41 is provided on the pressure surface 4-1 at the blade tip 4 of the turbine blade. The suction side rib 42 and the pressure side rib 41 form a blade tip groove 5. The turbine blade also includes an outer blade top surface 404 provided at the blade tip 4 of the turbine blade. The bottom edge of the suction side rib 42 and the blade tip edge of the suction surface 4-2 are connected through the outer blade top surface 404, and the bottom edge of the pressure side rib 41 and the blade tip edge of the pressure surface 4-1 are connected through the outer blade top surface 404. The suction side rib 42 is inclined from the outer blade top surface 404 toward the suction surface 4-2 and forms a suction side groove 7 with the outer blade top surface 404. The pressure-side rib 41 has its outer blade top surface 404 inclined toward the pressure surface 4-1, forming a pressure-side groove 6 with the outer blade top surface 404. The suction-side groove 7 and the pressure-side groove 6 provide a guiding function, thereby guiding at least a portion of the high-temperature combustion gas entering the suction-side groove 7 and the pressure-side groove 6 to the blade tip trailing edge 43.

[0043] The turbine blade of this invention, through the inclined suction side ribs 42 and pressure side ribs 41, allows a portion of the high-temperature combustion gas from the combustion chamber to pass over the inclined suction side ribs 42 and pressure side ribs 41 under the action of circumferential and axial pressure differences and enter the blade tip groove 5. This increases the leakage flow inlet turning angle, resulting in a larger separation vortex range on the rib top surface, thereby reducing the actual flow area between the rib top surface and the casing, and reducing the leakage flow rate. The suction side groove 7 and pressure side groove 6 have a guiding function, which can partially guide the fluid entering the grooves towards the turbine blade trailing edge, further reducing the amount of high-temperature combustion gas entering, thereby reducing the losses caused by turbine blade tip leakage, increasing the amount of combustion gas that performs useful work, and improving turbine efficiency.

[0044] like Figure 6 In one embodiment, the pressure surface 4-1 of the blade tip 4 has a trailing edge slit 43 located at the trailing edge of the blade tip, which is situated on the pressure surface 4-1. In another embodiment, the trailing edge slit is located on the suction surface 4-2. High-temperature combustion gases passing through the gap in the blade tip 4 can flow out of the blade tip groove 5 through the trailing edge slit, effectively reducing the leakage flow rate across the suction side rib 42, minimizing losses caused by leakage vortices in the blade tip 4, and to some extent reducing the trailing edge loss of the blade tip 4. The ratio of the width of the trailing edge slit to the height of the suction side rib 42 or the pressure side rib 41 can be selected between 0.5 and 2.5.

[0045] Figure 7 and Figure 8 A cross-section at the leading edge of the blade tip (40°) is shown. Figure 7 As shown, the suction-side rib 42 includes an inner surface 421, a rib top surface 422, and an outer surface 423 opposite to the inner surface 421. The pressure-side rib 41 includes an inner surface 411, a rib top surface 412, and an outer surface 413 opposite to the inner surface 411. The outer blade top surface 404 includes an outer blade top surface 414 forming the suction-side groove 6 and an outer blade top surface 424 forming the pressure-side groove 7.

[0046] In one embodiment, the width of the rib top surface 412 of the pressure side rib 41 and the rib top surface 422 of the suction side rib 42 can be selected as 0.4 to 1.6 times the blade trailing edge diameter, and the depth of the blade tip groove 5 can be selected as 1% to 5% of the blade tip airfoil chord length. The chord length refers to the distance between the leading edge and trailing edge of the turbine blade.

[0047] In one embodiment, a first angle is formed between the outer surface 423 of the suction-side rib 42 and the top surface 414 of the outer blade, the first angle gradually increasing from the leading edge 40 of the blade tip to the trailing edge 43 of the blade tip; and / or a second angle is formed between the outer surface 413 of the pressure-side rib 41 and the top surface 424 of the outer blade, the second angle gradually increasing from the leading edge 40 of the blade tip to the trailing edge 43 of the blade tip. The width of the top surface 424 of the outer blade forming the suction-side groove 7 and / or the top surface 414 of the outer blade forming the pressure-side groove 6 gradually decreases from the leading edge 40 of the blade tip to the trailing edge 43 of the blade tip. Figure 8 As shown, the first included angle and the second included angle are both α; the distance between the bottom edge of the suction side rib 42 and the blade tip edge of the suction surface 4-2, and the distance between the bottom edge of the pressure side rib 41 and the blade tip edge of the pressure surface 4-1 are the width W (i.e. the width of the outer blade top surface 424 and the outer blade top surface 414).

[0048] At the leading edge of the leaf tip, 40 points, such as Figure 5 and Figure 6 As shown, the first included angle or the second included angle α is the smallest, and the width W is the largest. In one embodiment, the value of the first included angle and / or the second included angle at the leading edge 40 of the blade tip is 30° to 80°. The ratio of the width of the outer blade top surface 424 to the width of the rib top surface 422 of the suction side rib 42 is 0.4 to 1.3, and the ratio of the width of the outer blade top surface 414 to the width of the rib top surface 412 of the pressure side rib 41 is 0.4 to 1.3. The first included angle or the second included angle α gradually increases to 90° along the chord of the turbine blade towards the trailing edge, and the width W of the outer blade top surface 414 and the outer blade top surface 424 gradually decreases to 0, so that the suction side rib 42 and the pressure side rib 41 gradually merge with the blade body region 3, as shown. Figure 5 and Figure 6 As shown.

[0049] For a turbine blade with a tip groove 5, under the influence of circumferential and axial pressure differences, high-temperature combustion gas will enter the gap from the portion of the suction surface 4-2 near the leading edge and the portion of the pressure surface 4-1. Therefore, in one embodiment, the suction side rib 42 can be provided at the tip leading edge 40. Figure 6 As shown, in one embodiment, the suction-side groove 7 extends from the leading edge 40 of the blade tip to the region of maximum thickness of the blade body 3, i.e., the termination position of the outer blade top surface 424 is located near the region of maximum thickness of the blade body 3. The extension distance of the suction-side groove 7 from the leading edge 40 of the blade tip can be selected as 10% to 50% of the blade chord length. Figure 5 As shown, in one embodiment, the pressure-side groove 6 extends from the leading edge 40 of the blade tip to the trailing edge 43 of the blade tip, meaning that the termination position of the outer blade top surface 414 can be located near the region of the trailing edge 43 of the blade tip. The distance between the termination position of the outer blade top surface 414 and the trailing edge 43 of the blade tip can be selected as 0 to 30% of the chord length of the turbine blade.

[0050] Figure 9Another embodiment of the turbine blade of the present invention is shown. In such a way... Figure 9 In the embodiment shown, the outer surface 423 of the suction side rib 42 is rounded between the outer blade top surface 424 forming the suction side groove 7 and between the outer blade top surface 424 and the suction surface 4-2. The outer surface 413 of the pressure side rib 41 is rounded between the outer blade top surface 414 forming the pressure side groove 6 and between the outer blade top surface 414 forming the pressure side groove and the pressure surface 4-1.

[0051] Figure 10 The flow direction of the high-temperature combustion gas at the blade tip 4 is schematically shown. A portion of the high-temperature combustion gas from the combustion chamber, under the influence of circumferential and axial pressure differences, passes over the suction side rib 42 and the pressure side rib 41 and enters the blade tip groove 5. (As shown in the diagram...) Figure 2 Compared to the original straight-ribbed double-ribbed blade tip, the inclined suction-side rib 42 and pressure-side rib 41 increase the inlet turning angle of the leakage flow, resulting in a larger separation vortex range on the rib top surfaces 412 and 422, thereby reducing the actual flow area between the rib top surfaces and the casing 8. On the other hand, the suction-side groove 7 and pressure-side groove 6 have a guiding function, partially directing the fluid entering the blade tip groove 5 towards the turbine blade trailing edge, further reducing the amount of high-temperature combustion gas entering the blade tip groove 5, thereby reducing the losses caused by turbine blade tip leakage.

[0052] Figure 11 This is the radial distribution curve of the total pressure loss at the turbine blade exit. Wherein, Figure 11 The middle dashed line is Figure 3 The total pressure loss at the blade tip exit shown is radially distributed, with the solid line representing the total pressure loss at the blade tip exit. Figure 9 The total pressure loss at the blade outlet is distributed radially. It can be seen that... Figure 9 The total pressure loss caused by tip leakage vortices in the turbine blades shown is relatively high. Figure 3 The blade tip structure shown is smaller, and the position of the upper channel vortex moves towards the casing 8, reducing the secondary flow influence area.

[0053] Figure 12a for Figure 3 The suction surface 4-2 of the turbine blade is shown as the limiting streamline. Figure 12b for Figure 9 The diagram shows the limiting streamlines of the suction surface of the turbine blade (4-2). (Using...) Figure 9 The turbine blades of the structure shown have a smaller secondary flow range in the upper channel.

[0054] The turbine engine of the present invention includes a turbine disk body (not shown) and a turbine rotor assembly 9, the turbine rotor assembly 9 including a plurality of turbine blades 3. Figure 13The turbine rotor assembly 9 of the present invention is shown. A plurality of turbine blades are mounted circumferentially to the turbine disk body via tenons 1.

[0055] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A turbine blade, comprising a blade body, The blade includes a suction surface, a pressure surface, suction side ribs, and pressure side ribs; The suction side rib is provided on the suction surface at the tip of the turbine blade, and the pressure side rib is provided on the pressure surface at the tip of the turbine blade. The suction side rib and the pressure side rib form a tip groove. Its features are, The turbine blade also includes an outer blade tip surface disposed at the blade tip; The bottom edge of the suction side rib and the tip edge of the suction surface are connected through the top surface of the outer blade, and the bottom edge of the pressure side rib and the tip edge of the pressure surface are connected through the top surface of the outer blade. The suction side rib is inclined from the top surface of the outer blade to the suction surface and forms a suction side groove with the top surface of the outer blade; The pressure-side rib is inclined from the top surface of the outer blade to the pressure surface and forms a pressure-side groove with the top surface of the outer blade; The suction-side groove and the pressure-side groove provide a guiding function, thereby directing at least a portion of the high-temperature combustion gas entering the suction-side groove and the pressure-side groove to the blade tip trailing edge.

2. The turbine blade as described in claim 1, characterized in that, The outer surface of the suction rib and the top surface of the outer blade form a first included angle, which gradually increases from the leading edge of the blade tip to the trailing edge of the blade tip; and / or A second included angle is formed between the outer surface of the pressure side rib and the top surface of the outer leaf, and the second included angle gradually increases from the leading edge of the leaf tip to the trailing edge of the leaf tip.

3. The turbine blade as described in claim 2, characterized in that, The value of the first included angle and / or the second included angle at the leading edge of the leaf tip is 30° to 80°.

4. The turbine blade as described in any one of claims 1 to 3, characterized in that, The width of the top surface of the outer blade forming the suction-side groove and / or the top surface of the outer blade forming the pressure-side groove gradually decreases from the leading edge of the blade tip to the trailing edge of the blade tip.

5. The turbine blade as described in claim 4, characterized in that, The ratio of the width of the top surface of the outer blade forming the suction-side groove to the width of the top surface of the suction-side rib is 0.4 to 1.3; and / or The ratio of the width of the top surface of the outer blade forming the pressure-side groove to the width of the top surface of the pressure-side rib is 0.4 to 1.

3.

6. The turbine blade as described in any one of claims 1 to 3, characterized in that, The suction-side groove extends from the leading edge of the blade tip to the area of ​​maximum thickness of the blade body, and the pressure-side groove extends from the leading edge of the blade tip to the trailing edge of the blade tip.

7. The turbine blade as claimed in claim 6, characterized in that, The suction-side groove extends from the leading edge of the blade tip by a distance of 10% to 50% of the chord length of the blade.

8. The turbine blade as claimed in claim 1, characterized in that, The outer surface of the suction side rib is rounded between the outer surface of the outer blade forming the suction side groove and the outer surface of the outer blade forming the suction side groove and the suction surface; and / or The outer surface of the pressure side rib is rounded between the top surface of the outer blade forming the pressure side groove and between the top surface of the outer blade forming the pressure side groove and the pressure surface.

9. The turbine blade as claimed in claim 1, characterized in that, A trailing edge slit is provided at the tip of the blade, and the trailing edge slit is located on the suction surface or the pressure surface.

10. A gas turbine, characterized in that, Includes turbine blades as described in any one of claims 1-9.

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