Turbine blade tenon sealing structure and aero-engine

Abstract

The utility model discloses a turbine blade tenon sealing structure and an aero-engine, the turbine blade tenon sealing structure comprises a turbine disc and a plurality of turbine blades arranged along the circumferential direction of the turbine disc, each turbine blade comprises a blade body and a blade root, and the blade root is arranged on the blade body. The turbine blade tenon sealing structure comprises a blade root and a blade body, a tenon used for being connected with a turbine disc is arranged on the side, away from the blade body, of the blade root, the blade roots of every two adjacent turbine blades are spliced with each other, the turbine blade tenon sealing structure is characterized in that the turbine blade tenon sealing structure further comprises a sealing piece arranged between every two adjacent turbine blades, an inserting groove is formed in each tenon, and the inserting grooves are formed in the sealing pieces. The sealing piece is inserted into the inserting grooves of the two adjacent turbine blades at the same time and blocks the gap between the blade roots of the two adjacent turbine blades. The turbine blade tenon sealing structure provided by the utility model can physically block high-temperature airflow from a gap between two adjacent turbine blades, effectively protect the tenon, improve the durability of the tenon, reduce the consumption of cooling gas and improve the use efficiency of a gas compressor.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engines, in particular to a turbine blade tenon sealing structure and an aviation engine adopting the turbine blade tenon sealing structure. Background Art

[0002] The working process of a gas turbine is as follows: the air compressed by the compressor is mixed with the aviation fuel and burned in the combustion chamber, thereby generating high-temperature and high-pressure gas, which drives the turbine blades to rotate and do work. Therefore, the high-speed rotating turbine blades in the gas turbine need to withstand very high-temperature airflow, and the turbine blades are connected to the turbine disk through the tenon at the root of the blade. Since there is a gap between two adjacent turbine blades, such as Figure 1 As shown, the high-temperature airflow will flow to the tenon through these gaps. The tenon will be eroded by the high-temperature airflow and the corrosive substances and foreign matter in the airflow for a long time, which will greatly reduce the life of the turbine disc tenon and is more likely to cause serious failures such as tenon breakage.

[0003] In this regard, Chinese invention patent CN117404139A provides a cold air flow path structure suitable for a double-spoke turbine disc, which guides the cold air provided by the compressor to the installation position of the tenon by setting a cavity inside the turbine disc, thereby cooling the tenon with cold air. However, cooling the tenon by drawing cooling air from the compressor will not only reduce the efficiency of the compressor and reduce the power of the engine, but also increase the temperature of the compressed air itself as the compression ratio of the engine continues to increase, and the cooling effect will also deteriorate, making it difficult to ensure the cooling effect. In addition, the gap between two adjacent turbine blades is not processed, and foreign matter in the hot air flow will enter the tenon through the gap. Utility Model Content

[0004] The utility model primarily provides a turbine blade tenon sealing structure to solve the technical problem that a gap between two adjacent turbine blades of an existing aircraft engine easily causes serious influence on the tenon.

[0005] The utility model also provides an aeroengine, which adopts the turbine blade tenon sealing structure.

[0006] According to a first aspect of the utility model, a turbine blade tenon sealing structure is provided, comprising a turbine disk and a plurality of turbine blades arranged circumferentially along the turbine disk, the turbine blade comprising a blade body and a blade root, the blade root being provided with a tenon for connecting to the turbine disk on a side away from the blade body, the blade roots of two adjacent turbine blades being spliced ​​with each other, the turbine blade tenon sealing structure also comprising a sealing sheet arranged between two adjacent turbine blades, the tenon being provided with a slot, the sealing sheet being simultaneously inserted into the slots of two adjacent turbine blades and sealing the gap between the blade roots of two adjacent turbine blades.

[0007] Preferably, the slots are respectively opened at both ends of the tenon along the circumference of the turbine disk, and the slot is provided with an opening on the side facing the adjacent turbine blade. The slots of two adjacent turbine blades are spliced ​​through the opening to form a splicing groove, and the sealing sheet is inserted into the splicing groove and connects the two adjacent turbine blades into a whole.

[0008] Preferably, the slot includes a fixed end and a positioning end extending along the length direction of the fixed end, and an insertion end arranged between the fixed end and the positioning end, an end of the fixed end away from the positioning end and an end of the positioning end away from the fixed end are both set as closed structures, the insertion end is inclined relative to the fixed end, and an insertion hole for inserting the sealing sheet is provided at the end of the insertion end away from the fixed end.

[0009] Preferably, the sealing sheet is made of elastic material, and an escape space for elastic bending of the sealing sheet is provided between the insertion end and the positioning end.

[0010] Preferably, the length of the sealing sheet is greater than the length of the fixed end, and the length of the sealing sheet is less than the sum of the lengths of the fixed end and the positioning end.

[0011] Preferably, the insertion end is arranged on a side of the positioning end away from the blade body.

[0012] Preferably, a first groove is provided at one end of the tenon along the axial direction of the turbine disk, and a second groove is provided on the axial end face of the turbine disk, and the second groove is arranged in a one-to-one correspondence with the first groove. The turbine blade tenon sealing structure also includes a limiting plate, and the two ends of the limiting plate are respectively clamped in the first groove and the second groove to limit the axial position of the tenon relative to the turbine disk.

[0013] Preferably, the limiting piece includes a telescopic portion and two limiting portions respectively arranged at opposite ends of the telescopic portion, and the telescopic portion is used to open the two limiting portions so that the two limiting portions are clamped in the first card slot and the second card slot in a one-to-one correspondence.

[0014] Preferably, the telescopic portion is configured as an arch-shaped structure protruding in a direction away from the turbine blade, and the arch-shaped structure is used to flatten in a direction toward the turbine blade so that the two limiting portions are away from each other and clamped in the first slot and the second slot one by one.

[0015] According to a second aspect of the utility model, there is also provided an aircraft engine, comprising a gas turbine, wherein the gas turbine comprises the above-mentioned turbine blade tenon sealing structure.

[0016] The utility model has the following beneficial effects:

[0017] In the turbine blade tenon sealing structure provided by the utility model, a slot is provided on the tenon of the turbine blade. By configuring a sealing sheet and inserting it into the slots of two adjacent turbine blades at the same time, the sealing sheet can be used to seal the gap between the blade roots of two adjacent turbine blades, physically blocking the high-temperature airflow from the gap between the two adjacent turbine blades, and blocking foreign matter from entering the tenon, avoiding long-term erosion by the high-temperature airflow and corrosive substances and foreign matter in the airflow to reduce the service life, effectively protecting the tenon and improving the durability of the tenon. Secondly, by sealing the gap between the blade roots of two adjacent turbine blades with a sealing sheet, the consumption of cooling gas can be reduced, and the use efficiency of the compressor can be improved. It is suitable for aircraft engines with high pressure ratios and high cooling gas temperatures.

[0018] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation on the present invention. In the drawings:

[0020] Figure 1 It is a schematic diagram of a local structure of an existing gas turbine, wherein the solid line with an arrow indicates the leakage direction of the gas;

[0021] Figure 2 An end surface structural diagram of a turbine blade in a turbine blade tenon sealing structure provided by an embodiment of the utility model;

[0022] Figure 3 A front view of a sealing sheet in a turbine blade tenon sealing structure provided by an embodiment of the utility model;

[0023] Figure 4 For application Figure 3 A schematic structural diagram of a sealing sheet installation tool shown;

[0024] Figure 5 For application Figure 3 A schematic structural diagram of a sealing sheet disassembly tool shown;

[0025] Figure 6 A cross-sectional structural diagram of a turbine blade in a turbine blade tenon sealing structure provided by an embodiment of the utility model;

[0026] Figure 7 A side view of a limiting piece in a turbine blade tenon sealing structure provided by an embodiment of the utility model;

[0027] Figure 8 for Figure 7 A front view of the limiting piece shown;

[0028] Fig. 9 for Figure 7 The installation structure diagram of the limit plate is shown.

[0029] Legend:

[0030] 1. turbine disc; 11. second slot; 2. turbine blade; 21. blade body; 22. blade root; 23. tenon; 24. slot; 241. fixed end; 242. positioning end; 243. insertion end; 25. first slot; 3. sealing sheet; 4. installation tool; 41. installation slot; 42. front retaining edge; 43. rear slot; 5. disassembly tool; 51. disassembly slot; 52. front slot; 53. rear retaining edge; 6. limit sheet; 61. telescopic part; 611. notch; 62. limit part. DETAILED DESCRIPTION

[0031] The embodiments of the present invention are described in detail below in conjunction with the accompanying drawings. However, the present invention can be implemented in a variety of different ways as defined and covered below.

[0032] Figures 1 to 9 The turbine blade tenon sealing structure and the aircraft engine provided by the embodiments of the utility model are jointly shown, wherein the turbine blade tenon sealing structure is used to seal the gap between the blade roots of two adjacent turbine blades, so as to prevent high-temperature combustion gas and foreign matter from entering the tenon of the turbine blade, thereby effectively protecting the tenon.

[0033] Please combine Figure 1 and Figure 2 The turbine blade tenon sealing structure includes a turbine disk 1 and a plurality of turbine blades 2 arranged along the circumference of the turbine disk 1. The turbine blade 2 includes a blade body 21 and a blade root 22. The blade root 22 is provided with a tenon 23 for connecting with the turbine disk 1 on a side away from the blade body 21. The blade roots 22 of two adjacent turbine blades 2 are spliced ​​with each other. Figure 1 FIG. 4 shows a partial structure of an existing gas turbine. Since there is a gap between the blade roots 22 of adjacent turbine blades 2, high-temperature combustion gas will enter the tenon along the gap.

[0034] Please combine Figure 3 The turbine blade tenon sealing structure also includes a sealing sheet 3 arranged between two adjacent turbine blades 2. The sealing sheet 3 is set as a long thin sheet structure. A slot 24 is provided on the tenon 23. The sealing sheet 3 is simultaneously inserted into the slots 24 of two adjacent turbine blades 2 and seals the gap between the blade roots 22 of two adjacent turbine blades 2.

[0035] Specifically, in the turbine blade tenon sealing structure, a slot 24 is provided on the tenon 23 of the turbine blade 2. By configuring the sealing sheet 3 to be simultaneously inserted into the slots 24 of two adjacent turbine blades 2, the sealing sheet 3 can be used to block the gap between the blade roots 22 of two adjacent turbine blades 2, physically blocking the high-temperature airflow from the gap between the two adjacent turbine blades 2, and blocking foreign matter from entering the tenon 24, avoiding long-term erosion by the high-temperature airflow and corrosive substances and foreign matter in the airflow to reduce the service life, effectively protecting the tenon 24, and improving the durability of the tenon 24. Secondly, by blocking the gap between the blade roots 22 of two adjacent turbine blades 2 with the sealing sheet 3, the consumption of cooling gas can be reduced, and the use efficiency of the compressor can be improved, which is suitable for aircraft engines with high pressure ratio and high cooling gas temperature.

[0036] Preferably, the slots 24 are respectively opened at both ends of the tenon 23 along the circumference of the turbine disk 1, and the slots 24 are provided with an opening on one side facing the adjacent turbine blade 2. The slots 24 of two adjacent turbine blades 2 are spliced ​​through the opening to form a splicing groove, and the sealing sheet 3 is inserted into the splicing groove and connects the two adjacent turbine blades 2 into a whole. That is, the sealing sheet 3 extends transversely through the opening into the slots 24 of the two adjacent turbine blades 2, and is inserted into the two slots 24 at the same time, so as to achieve sealing between the blade roots 22 of the two adjacent turbine blades 2, and can also connect the two adjacent turbine blades 2 into a whole, strengthen the fixation of the turbine blades 2, and improve the installation strength and stability of the turbine blades 2.

[0037] like Figure 2 As shown, the slot 24 includes a fixed end 241 and a positioning end 242 extending along the length direction of the fixed end 241, and an insertion end 243 arranged between the fixed end 241 and the positioning end 242, and the end of the fixed end 241 away from the positioning end 242 and the end of the positioning end 242 away from the fixed end 241 are both set as closed structures, and the insertion end 243 is inclined relative to the fixed end 241, and the end of the insertion end 243 away from the fixed end 241 is provided with an insertion hole for inserting the sealing sheet 3.

[0038] Specifically, the fixed end 241 and the positioning end 242 are arranged along a straight line, and the insertion end 243 is arranged obliquely relative to the fixed end 241, so that the fixed end 241, the positioning end 242 and the insertion end 243 together form a "Y"-shaped structure. When the length of the sealing sheet 3 is less than the length of the fixed end 241, the sealing sheet 3 can be fully inserted into the fixed end 241 along the insertion hole, and then the sealing sheet 3 can be pulled back in the direction toward the positioning end 242, so that part of the structure of the sealing sheet 3 enters the positioning end 242. By clamping the sealing sheet 3 together by the fixed end 241 and the positioning end 242, the sealing sheet 3 can be fastened in the slot 24 and will not fall off actively. The limiting structure is simple and efficient.

[0039] Preferably, the sealing sheet 3 is made of elastic material, specifically GH3030 material, and an escape space is provided between the insertion end 241 and the positioning end 242 for elastic bending of the sealing sheet 3, so as to drive the tail end of the sealing sheet 3 to enter the positioning end 242 after elastic bending in the escape space.

[0040] Preferably, the length of the sealing sheet 3 is greater than the length of the fixed end 241, and the length of the sealing sheet 3 is less than the sum of the lengths of the fixed end 241 and the positioning end 242. Since the sealing sheet 3 is made of elastic material and can be elastically bent and deformed during the assembly process, adjusting the length of the sealing sheet 3 to be greater than the length of the fixed end 241 can not only enable the tail end of the sealing sheet 3 to enter the positioning end 242 after elastic bending along the avoidance space to complete the assembly operation, but also enable at least a portion of the sealing sheet 3 to remain inserted in the positioning end 242 after being assembled in place, thereby improving the limiting effect.

[0041] Preferably, the insertion end 243 is arranged on a side of the positioning end 242 away from the blade body 21, that is, the insertion end 243 is arranged toward the end of the tenon 23, and the sealing sheet 3 is inserted from the bottom of the tenon 23 to avoid interference with the assembly of the sealing sheet 3 due to the wider position of the blade root 22, thereby improving the assembly convenience of the sealing sheet 3.

[0042] like Figure 4As shown, an embodiment of the utility model further provides an installation tool 4, which includes a thin sheet structure for passing through the gap between the blade roots 22 of two adjacent turbine blades 2, and an installation groove 41 is opened on the thin sheet structure of the installation tool 4, the front end of the installation groove 41 is set as a front guard edge 42, and the rear end of the installation groove 41 is set as a rear card groove 43 adapted to the inclination angle of the insertion end 243. The thin sheet structure of the installation tool 4 can penetrate into the splicing groove along the gap between the blade roots 22 of two adjacent turbine blades 2, thereby clamping the sealing sheet 3 through the installation groove 41, so that the front end of the sealing sheet 3 abuts the front guard edge 42, and the rear end of the sealing sheet 3 abuts the rear clamping groove 43, and the sealing sheet 3 is pulled backward by the installation tool 4, so that the sealing sheet 3 is deformed and bent (the length becomes shorter), and the rear end of the sealing sheet 3 is pressed downward by the rear clamping groove 43. At this time, the front end of the sealing sheet 3 will bend upward, and then the sealing sheet 3 is pushed forward by the installation tool 4 to position the sealing sheet 3 at the positioning end 242, and then the installation tool 4 is taken out. At this time, since the sealing sheet 3 is no longer subjected to the squeezing force of the installation tool 4, the sealing sheet 3 automatically rebounds and resets (the length becomes longer), thereby being clamped in the positioning end 242.

[0043] like Figure 5 As shown, the embodiment of the utility model further provides a disassembly tool 5, the disassembly tool 5 includes a thin sheet structure for passing through the gap between the blade roots 22 of two adjacent turbine blades 2, the thin sheet structure of the disassembly tool 5 is provided with a disassembly groove 51, the front end of the disassembly groove 51 is set as an inclined front clamping groove 52, and the rear end of the disassembly groove 51 is set as a rear guard 53. Similarly, the thin sheet structure of the disassembly tool 5 can penetrate into the splicing groove along the gap between the blade roots 22 of two adjacent turbine blades 2, so as to clamp the sealing sheet 3 through the disassembly groove 51, so that the front end of the sealing sheet 3 abuts the front clamping groove 52, and the rear end of the sealing sheet 3 abuts the rear guard 53, and the sealing sheet 3 is pulled back by the disassembly tool 5 to deform and bend the sealing sheet 3, and the rear end of the sealing sheet 3 is pressed downward by the front clamping groove 52, and then the sealing sheet 3 is pushed back by the installation tool 4, so that the sealing sheet 3 can be taken out along the insertion end 243.

[0044] Please combine Figure 6 and Fig. 9Preferably, a first groove 25 is provided at one end of the tenon 23 along the axial direction of the turbine disk 1, and a second groove 11 is provided on the axial end surface of the turbine disk 1, and the second groove 11 is arranged in a one-to-one correspondence with the first groove 25. The turbine blade tenon sealing structure also includes a limiting plate 6, and the two ends of the limiting plate 6 are respectively clamped in the first groove 25 and the second groove 11, so that the tenon 23 is axially limited relative to the turbine disk 1.

[0045] Specifically, in the turbine blade tenon sealing structure, by setting a first slot 25 on the tenon 23 of the turbine blade 2, setting a second slot 11 on the turbine disk 1, and respectively inserting the two ends of the limiting plate 6 into the first slot 25 and the second slot 11, the tenon 23 can be axially limited relative to the turbine disk 1. The limiting structure is simple and efficient, and the limiting effect is good. Moreover, since the second slot 11 is arranged in a one-to-one correspondence with the first slot 25, each turbine blade 2 is limited by a limiting plate 6, which is convenient and flexible to adjust the limiting accuracy and limiting strength, effectively improves the stability of the turbine blade 2, and is also convenient to disassemble and assemble any turbine blade 2 separately, which is convenient for later repair and maintenance operations.

[0046] Preferably, the corresponding first card slot 25 and the second card slot 11 are extended in the same straight line direction. Since the first card slot 25 and the second card slot 11 are extended in the same straight line direction, the limiting piece 6 can be fixed on the same plane, thereby improving the installation strength and stability, avoiding falling off, and enabling the limiting piece 6 to closely contact the turbine blade 2 and the turbine disk 1, further improving the limiting effect.

[0047] Further, the tenon 23 is provided with a first protruding block protruding outward, and the first slot 25 is provided on the first protruding block, so that the first slot 25 is provided outside the main structure of the tenon 23, avoiding reducing the structural strength of the tenon 23, and the limiting piece 6 can fully abut the side wall of the tenon 23 to improve the limiting strength. The turbine disk 1 is provided with a second protruding block protruding outward, and the second slot 11 is provided on the second protruding block, which can also enable the second slot 11 to be provided outside the main structure of the turbine disk 1, avoiding reducing the structural strength of the turbine disk 1, and the limiting piece 6 can fully abut the side wall of the turbine disk 1.

[0048] like Figure 7As shown, the limiting piece 6 includes a telescopic portion 61 and two limiting portions 62 disposed at opposite ends of the telescopic portion 61, and the telescopic portion 61 is used to open the two limiting portions 62 so that the two limiting portions 62 are clamped in the first clamping slot 25 and the second clamping slot 11 in a one-to-one correspondence. The distance between the two limiting portions 62 can be adjusted by the telescopic portion 61, so that the two limiting portions 62 can be mutually opened and clamped in place, or the two limiting portions 62 can be mutually retracted for removal, and the disassembly structure is simple and efficient.

[0049] Please combine Figure 7 and Fig. 9 The telescopic portion 61 is configured as an arch-shaped structure protruding in a direction away from the turbine blade 2, and the arch-shaped structure is used to flatten in a direction toward the turbine blade 2, so that the two limiting portions 62 are separated from each other and clamped in the first clamping groove 25 and the second clamping groove 11 one by one. The telescopic portion 61 is configured as an arch-shaped structure, so that the telescopic portion 61 and the two limiting portions 62 are integrally formed, the structural strength is higher, and the limiting effect is better. In other embodiments, the telescopic portion 61 can also be formed by splicing two telescopic plates, and the spacing between the two limiting portions 62 can also be adjusted by adjusting the splicing position of the two telescopic plates.

[0050] like Figure 8 As shown, notches 611 are provided on opposite sides of the telescopic portion 61, and the notches 611 are used to insert a hook and to hook and pull the telescopic portion 61 in a flattened state in a direction away from the turbine blade 2 to reset it into the arch structure, so that the two limiting portions 62 are separated from each other and respectively detach from the first slot 25 and the second slot 11, making it convenient to remove the limiting plate 6.

[0051] like Fig. 9 As shown, one end of the limiting portion 62 away from the telescopic portion 61 is tilted outward along the axial direction of the turbine disk 1, so that the limiting portion 62 can reversely press against the first slot 25 or the second slot 11 after being snapped into place, thereby preventing the limiting plate 6 from loosening.

[0052] Preferably, there are multiple limit plates 6, and the multiple limit plates 6 are arranged in a one-to-one correspondence with the multiple turbine blades 2, that is, each turbine blade 2 is axially limited by a limit plate 6, which is convenient and flexible to adjust the limiting accuracy and limiting strength of each turbine blade 2, effectively improves the stability of the turbine blade 2, and is also convenient for disassembly and assembly of any turbine blade 2, which is convenient for later repair and maintenance operations.

[0053] As a second aspect, the embodiment of the utility model also provides an aircraft engine, including a gas turbine, and the gas turbine includes the above-mentioned turbine blade tenon sealing structure. Since the turbine blade tenon sealing structure is provided with the sealing sheet 3, the gap between the blade roots 22 of two adjacent turbine blades 2 can be effectively blocked, and the tenon 23 is prevented from being eroded by the high-temperature airflow and the corrosive substances and foreign matter in the airflow for a long time, thereby reducing the service life, thereby improving the stability and durability of the aircraft engine, and reducing the consumption of cooling gas, improving the use efficiency of the compressor, and is suitable for aircraft engines with high pressure ratio and high cooling gas temperature.

[0054] The above description is only the preferred embodiment of the utility model, and is not intended to limit the utility model. For those skilled in the art, the utility model can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. A turbine blade tenon sealing structure, comprising a turbine disk (1) and a plurality of turbine blades (2) arranged along the circumference of the turbine disk (1), wherein the turbine blade (2) comprises a blade body (21) and a blade root (22), wherein a tenon (23) for connecting to the turbine disk (1) is provided on a side of the blade root (22) away from the blade body (21), and the blade roots (22) of two adjacent turbine blades (2) are spliced ​​with each other, characterized in that: The turbine blade tenon sealing structure also includes a sealing sheet (3) arranged between two adjacent turbine blades (2), the tenon (23) being provided with a slot (24), the sealing sheet (3) being simultaneously inserted into the slots (24) of the two adjacent turbine blades (2) and sealing the gap between the blade roots (22) of the two adjacent turbine blades (2).

2. The turbine blade tenon sealing structure according to claim 1, characterized in that: The slots (24) are respectively opened at two ends of the tenon (23) along the circumference of the turbine disk (1); the slots (24) are provided with an opening on one side facing the adjacent turbine blade (2); the slots (24) of two adjacent turbine blades (2) are spliced ​​through the opening to form a splicing groove; the sealing sheet (3) is inserted into the splicing groove and connects the two adjacent turbine blades (2) into a whole.

3. The turbine blade tenon sealing structure according to claim 1, characterized in that: The slot (24) comprises a fixed end (241) and a positioning end (242) extending along the length direction of the fixed end (241), and an insertion end (243) arranged between the fixed end (241) and the positioning end (242); an end of the fixed end (241) away from the positioning end (242) and an end of the positioning end (242) away from the fixed end (241) are both arranged as closed structures; the insertion end (243) is arranged obliquely relative to the fixed end (241); and an insertion hole for inserting the sealing sheet (3) is arranged at an end of the insertion end (243) away from the fixed end (241).

4. The turbine blade tenon sealing structure according to claim 3, characterized in that: The sealing sheet (3) is made of elastic material, and an escape space for elastic bending of the sealing sheet (3) is provided between the insertion end (243) and the positioning end (242).

5. The turbine blade tenon sealing structure according to claim 4, characterized in that: The length of the sealing sheet (3) is greater than the length of the fixed end (241), and the length of the sealing sheet (3) is less than the sum of the lengths of the fixed end (241) and the positioning end (242).

6. The turbine blade tenon sealing structure according to claim 3, characterized in that: The insertion end (243) is arranged on a side of the positioning end (242) away from the blade body (21).

7. The turbine blade tenon sealing structure according to claim 1, characterized in that: A first clamping groove (25) is provided at one end of the tenon (23) along the axial direction of the turbine disk (1), and a second clamping groove (11) is provided on the axial end surface of the turbine disk (1), wherein the second clamping groove (11) is arranged in a one-to-one correspondence with the first clamping groove (25), and the turbine blade tenon sealing structure also includes a limiting plate (6), wherein two ends of the limiting plate (6) are respectively clamped in the first clamping groove (25) and the second clamping groove (11), so that the tenon (23) is axially limited relative to the turbine disk (1).

8. The turbine blade tenon sealing structure according to claim 7, characterized in that: The limiting piece (6) comprises a telescopic portion (61) and two limiting portions (62) arranged at opposite ends of the telescopic portion (61); the telescopic portion (61) is used to open the two limiting portions (62) so that the two limiting portions (62) are clamped in the first clamping slot (25) and the second clamping slot (11) in a one-to-one correspondence.

9. The turbine blade tenon sealing structure according to claim 8, characterized in that: The telescopic portion (61) is configured as an arch-shaped structure protruding in a direction away from the turbine blade (2), and the arch-shaped structure is used to be flattened in a direction toward the turbine blade (2), so that the two limiting portions (62) are separated from each other and clamped in the first clamping groove (25) and the second clamping groove (11) in a one-to-one correspondence.

10. An aircraft engine comprising a gas turbine, characterized in that: The gas turbine comprises the turbine blade tenon sealing structure according to any one of claims 1 to 9.

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