Blade structure of gas compressor of gas turbine

Abstract

Relates to the field of gas turbines, and discloses a blade structure of a gas compressor of a gas turbine, which is arranged on a power shaft of the gas turbine and comprises a mounting disc, a blade and a blade, the blade body is inserted and fixed on the mounting disc; the fixing device is arranged on the mounting disc, is connected with the blade body and is used for fixing the blade body; the abutting plate is arranged on the mounting disc; the second elastic piece is fixedly arranged on the abutting plate, the fixing device comprises a mounting plate fixed to the mounting disc, an adjusting rod arranged on the mounting plate in a penetrating mode and a fixing block fixed to the side, close to the blade body, of the adjusting rod, and the fixing block is clamped and fixed to the blade body. Through the arrangement of the fixing device, the operation is simpler, more convenient and quicker when the blade body is replaced or maintained, and the maintenance cost and the time cost are reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, in particular to a blade structure of a gas turbine compressor. Background Art

[0002] In the working process of the gas turbine, the compressor is a key component. Its main function is to compress the air entering the gas turbine through the high-speed rotation of the blades, thereby increasing the pressure and temperature of the air and providing the necessary conditions for the subsequent combustion process. The performance of the compressor directly affects the overall efficiency and stability of the gas turbine.

[0003] During the operation of the gas turbine, the air flow will inevitably contain solid particles, which will cause scouring and cutting of the components and cause wear. Especially when the air filter is damaged, large particles will enter the gas turbine and continuously scour the blades, increasing the roughness of the blades, so the damaged blades need to be replaced.

[0004] The existing equipment has the following disadvantages: the traditional gas turbine compressor blade body is directly mounted on the power shaft by welding, bolting or other fixing methods, or indirectly mounted through a mounting plate. However, this structure has some problems. The integrally fixed blades will cause the entire blade to be replaced when damaged, which is costly. In addition, the blade fixing method is complicated and time-consuming when replacing or repairing the blades, which increases the maintenance cost.

[0005] Therefore, the present application proposes a blade structure for a gas turbine compressor to solve the above-mentioned problems. Summary of the invention

[0006] The object of the present invention is to provide a blade structure for a gas turbine compressor to solve the problem that the above-mentioned integrally fixed blades will cause the entire blade to be replaced when damaged, which is costly, and the blade fixing method is complicated and time-consuming when replacing or repairing the blades, thereby increasing maintenance costs.

[0007] To achieve the above object, the present invention provides the following technical solution: a blade structure of a gas turbine compressor, arranged on a power shaft of the gas turbine, comprises:

[0008] A mounting plate, fixedly sleeved on the power shaft;

[0009] The blade body is plugged and fixed on the mounting plate;

[0010] A fixing device, arranged on the mounting plate and connected to the blade body, for fixing the blade body;

[0011] An abutment plate, disposed on the mounting plate;

[0012] The second elastic member is fixedly arranged on the abutting plate.

[0013] Wherein, the fixing device includes a mounting plate fixed on the mounting plate, an adjusting rod passing through the mounting plate and a fixing block fixed on the adjusting rod on the side close to the blade body, the fixing block is clamped and fixed on the blade body, and a fixing groove for fixing the fixing block is opened at the position of the blade body corresponding to the fixing block.

[0014] Wherein, the adjusting rod is located between the fixing block and the mounting plate and is sleeved with a first elastic member.

[0015] Wherein, a threaded section is arranged between the adjusting rod and the mounting plate, the adjusting rod is slidably sleeved inside the threaded section, and the threaded section is penetrated through the mounting plate.

[0016] Wherein, an adjusting nut is rotatably provided on a side of the mounting plate away from the fixing block, and the adjusting nut is threadedly connected with the threaded section.

[0017] Wherein, a rotating rod is arranged on the adjusting nut.

[0018] Wherein, a limiting block is arranged on the outer side of the adjusting rod, and the limiting block is slidably arranged inside the threaded section, and a limiting groove for the limiting block to move is opened at the position of the threaded section corresponding to the limiting block.

[0019] Wherein, the fixing block is arranged in a wedge shape.

[0020] Wherein, a clamping block is arranged at the lower end of the blade body, and the clamping block is inserted and fixed in the mounting plate, and a clamping groove for fixing the clamping block is opened on the mounting plate.

[0021] Among them, a plug-in block is fixed at the lower end of the clamping block, and a low joint is provided on the side of the plug-in block close to the abutment plate. The width of the plug-in block gradually decreases towards the low joint. The shape of the clamping groove is arranged corresponding to the shape of the plug-in block. The low joint abuts against the second elastic member, and an installation groove is provided at the position of the installation plate corresponding to the fixing device.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] When the damaged blade body needs to be replaced, the present invention releases the restriction of the fixing device on the blade body, and then the second elastic member pushes the blade body to move to the side away from the abutment plate, and then pushes it out from the inside of the mounting plate. By setting up this device, the blade body can be effectively fixed to prevent it from loosening or falling off due to vibration or external force during high-speed rotation, thereby improving the stability and safety of the gas turbine. Through the setting of the fixing device, the operation is simpler and faster when replacing or repairing the blade body, reducing maintenance costs and time costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of the main structure in one embodiment of the present invention;

[0025] Figure 2 A schematic diagram of the internal structure of a gas turbine according to an embodiment of the present invention;

[0026] Figure 3 It is a schematic structural diagram of a blade device in one embodiment of the present invention;

[0027] Figure 4 It is a schematic structural diagram of a blade device in front view in one embodiment of the present invention;

[0028] Figure 5 It is a schematic diagram of the structure of the connection between the blade body and the mounting plate in one embodiment of the present invention;

[0029] Figure 6 It is a schematic diagram of the structure of the plug-in block at the lower end of the blade body in one embodiment of the present invention;

[0030] Figure 7 It is a structural schematic diagram of the connection between the plug-in block and the fixing device in one embodiment of the present invention;

[0031] Figure 8 It is a structural schematic diagram of the connection between the fixing device and the mounting plate in one embodiment of the present invention;

[0032] Fig. 9 It is a structural schematic diagram of a fixing device in one embodiment of the present invention;

[0033] Fig.10 It is a schematic structural diagram of the explosion of the fixing device in one embodiment of the present invention.

[0034] In the figure: 1. gas turbine; 11. power shaft; 21. mounting plate; 211. abutment plate; 2101. snap-in groove; 2102. mounting groove; 22. blade body; 221. snap-in block; 222. plug-in block; 2221. low joint; 22201. fixing groove; 3. fixing device; 31. mounting plate; 32. adjusting rod; 321. limiting block; 33. fixing block; 34. first elastic member; 35. threaded section; 3501. limiting groove; 36. adjusting nut; 361. rotating rod; 37. second elastic member. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] See also Figure 1-10 The present invention provides a blade structure applicable to the field of gas turbine compressors, specifically a gas turbine compressor blade mechanism, which is arranged on a power shaft 11 of a gas turbine 1, and includes:

[0037] The mounting plate 21 is fixedly sleeved on the power shaft 11;

[0038] The blade body 22 is plugged and fixed on the mounting plate 21;

[0039] A fixing device 3, which is arranged on the mounting plate 21 and connected to the blade body 22, and is used to fix the blade body 22;

[0040] Abutment plate 211, disposed on the mounting plate 21;

[0041] The second elastic member 37 is fixedly disposed on the abutting plate 211 , and is made of a damped spring or elastic pad.

[0042] It should be noted that, when working, the blade body 22 is made of martensitic stainless steel as a whole, and the surface is evenly sprayed with a copper-nickel-indium alloy powder coating, which has good strength, anti-oxidation and corrosion resistance, and anti-vibration performance. When installing the blade body 22, the blade body 22 is inserted into the mounting plate 21, and then when the blade body 22 contacts the abutment plate 211, the second elastic member 37 is squeezed, and when installed to the set position, the fixing device 3 is clamped and fixed in the blade body 22, and the blade body 22 is fixed in the mounting plate 21. When the damaged blade needs to be repaired, When the main body 22 is replaced, the restriction of the fixing device 3 on the blade body 22 is released, and then the second elastic member 37 pushes the blade body 22 to move to the side away from the abutment plate 211, and then is pushed out from the inside of the mounting plate 21. By setting up this device, the blade body 22 can be effectively fixed to prevent it from loosening or falling off due to vibration or external force during high-speed rotation, thereby improving the stability and safety of the gas turbine 1. Through the setting of the fixing device 3, the operation is simpler and faster when replacing or repairing the blade body 22, reducing maintenance costs and time costs.

[0043] In one embodiment, the fixing device 3 includes a mounting plate 31 fixed on the mounting plate 21, an adjusting rod 32 passing through the mounting plate 31, and a fixing block 33 fixed on the side of the adjusting rod 32 close to the blade body 22. The fixing block 33 is clamped and fixed on the blade body 22, and a fixing groove 22201 for fixing the fixing block 33 is opened at the position of the blade body 22 corresponding to the fixing block 33.

[0044] This design, see Figure 7 When the blade body 22 contacts the fixing block 33, the fixing block 33 will be squeezed and then pushed to move to the side away from the blade body 22. When the blade body 22 is inserted into the set position, the fixing block 33 moves to the side close to the blade body 22 under the action of the adjusting rod 32, and then is clamped and fixed on the blade body 22, and closely cooperates with the fixing groove 22201 on the blade body 22, effectively preventing the blade from loosening or falling off during high-speed rotation, and significantly enhancing the fixing stability of the blade. The design of the adjusting rod 32 makes the fixing device 3 have a certain degree of adjustability. When the blade body 22 needs to be replaced or repaired, only the adjusting rod 32 needs to be loosened to easily remove the fixing block 33 from the blade body 22, thereby realizing the quick disassembly and installation of the blade.

[0045] In one embodiment, the adjusting rod 32 is located between the fixing block 33 and the mounting plate 31 and is sleeved with a first elastic member 34 . The first elastic member 34 is made of a damped spring or an elastic pad.

[0046] This design, see Figure 8 ,as well as Fig. 9When the fixing block 33 squeezes the blade body 22, the fixing block 33 squeezes the first elastic member 34. When the fixing groove 22201 on the blade body 22 is aligned with the fixing block 33, the fixing block 33 moves toward the inside of the fixing groove 22201 under the push of the first elastic member 34, and then is clamped and fixed in the inside of the fixing groove 22201, completing the fixing work of the fixing block 33 on the blade body 22.

[0047] In one embodiment, a threaded section 35 is provided between the adjusting rod 32 and the mounting plate 31 , the adjusting rod 32 is slidably sleeved inside the threaded section 35 , and the threaded section 35 is penetrated on the mounting plate 31 .

[0048] This design, see Fig. 9 By adjusting the installation position of the threaded section 35 on the mounting plate 31, the position of the adjusting rod 32 can be accurately adjusted to achieve fine-tuning of the tightness of the blade body 22, so that the fixing block 33 fits tightly with the blade body 22, making the connection between the fixing block 33 and the blade body 22 more stable.

[0049] In one embodiment, an adjusting nut 36 is rotatably provided on a side of the mounting plate 31 away from the fixing block 33 , and the adjusting nut 36 is threadedly connected to the threaded section 35 .

[0050] This design, see Figure 8-10 When the blade body 22 needs to be disassembled, the adjusting nut 36 is rotated so that the adjusting nut 36 rotates inside the mounting plate 31, and then the adjusting nut 36 is threadedly connected with the threaded section 35, driving the threaded section 35 to move to the side away from the blade body 22, and then the adjusting rod 32 drives the fixing block 33 to be pulled out from the inside of the fixing groove 22201, and when the fixing block 33 is pulled out from the inside of the blade body 22, the second elastic member 37 drives the blade body 22 to be pushed out from the inside of the mounting plate 21, so that the blade body 22 can be easily removed from the mounting plate 21.

[0051] In one embodiment, a rotating rod 361 is disposed on the adjusting nut 36 .

[0052] This design, see Figure 7-10 The design of the rotating rod 361 makes the rotation operation of the adjusting nut 36 more convenient. The adjusting nut 36 can be easily rotated by holding the rotating rod 361, which further facilitates the disassembly and replacement of the blade body 22.

[0053] In one embodiment, a limit block 321 is disposed on the outer side of the adjusting rod 32 , and the limit block 321 is slidably disposed inside the threaded section 35 . A limit groove 3501 for the limit block 321 to move is opened at the position of the threaded section 35 corresponding to the limit block 321 .

[0054] This design, see Fig. 9 ,as well as Fig.10 The cooperation between the limit block 321 and the limit groove 3501 can effectively limit the moving range of the adjustment rod 32 inside the threaded section 35. When the fixed block 33 is squeezed by the blade body 22, the adjustment rod 32 moves inside the threaded section 35, and the limit block 321 slides inside the limit groove 3501, which ensures that the adjustment rod 32 will not exceed the predetermined stroke during the adjustment process, thereby ensuring the stability and safety of the entire structure. The sliding of the limit block 321 in the limit groove 3501 provides a clear moving path for the adjustment rod 32. This enables the user to more accurately control the moving distance and direction of the adjustment rod 32 during the adjustment process, thereby improving the accuracy and reliability of the adjustment. The close cooperation between the limit block 321 and the limit groove 3501 can, to a certain extent, prevent the adjustment rod 32 from loosening or displacement when subjected to external force. This helps to maintain the stability and tightness of the entire structure and extend its service life.

[0055] In one embodiment, the fixing block 33 is configured in a wedge shape.

[0056] This design, see Figure 7-10 The wedge-shaped setting of the fixing block 33 can be squeezed by the blade body 22 and gradually move to the side away from the blade body 22 when it contacts the blade body 22, and the fixing groove 22201 is set corresponding to the shape of the wedge-shaped fixing block 33, so that the fixing block 33 can be stably fixed inside the blade body 22.

[0057] In one embodiment, a clamping block 221 is disposed at the lower end of the blade body 22 . The clamping block 221 is inserted and fixed in the mounting plate 21 . The mounting plate 21 is provided with a clamping groove 2101 for fixing the clamping block 221 .

[0058] This design, see Figure 5-7 The side of the clamping block 221 is serrated and tightly matched with the clamping groove 2101, which can significantly increase the connection stability between the blade body 22 and the mounting plate 21. This mechanical connection method can effectively prevent the blade body 22 from falling off or loosening due to vibration or external force during operation. The plug-in design of the clamping block 221 and the clamping groove 2101 can simplify the installation process between the blade body 22 and the mounting plate 21. No complicated tools or skills are required. Only the clamping block 221 needs to be aligned with the clamping groove 2101 and inserted, which improves the installation efficiency. When the blade body 22 needs to be disassembled for cleaning, repair or replacement, it can be easily achieved by simply pulling out the clamping block 221.

[0059] In one embodiment, a plug-in block 222 is fixed to the lower end of the clamping block 221, and a low joint 2221 is provided on the side of the plug-in block 222 close to the abutment plate 211. The width of the plug-in block 222 gradually decreases toward the low joint 2221. The shape of the clamping groove 2101 is set corresponding to the shape of the plug-in block 222. The low joint 2221 abuts against the second elastic member 37, and an installation groove 2102 is opened at the position of the corresponding fixing device 3 of the installation disk 21.

[0060] This design, see Figure 5-7 The corresponding shape design of the plug-in block 222 and the card slot 2101, as well as the gradual reduction of the width of the plug-in block 222, enable the plug-in block 222 to gradually and tightly fit in the card slot 2101 during the plug-in process, thereby improving the tightness and stability of the connection. The design of the low joint 2221 enables the plug-in block 222 to be more easily positioned when inserted into the card slot 2101, thereby ensuring the accuracy and efficiency of the plug-in. The abutment design of the low joint 2221 and the second elastic member 37 allows the second elastic member 37 to push the plug-in block 222 out of the inside of the card slot 2101 after the fixing device 3 releases the restriction on the plug-in block 222, thereby facilitating subsequent replacement of the blade body 22 by the staff.

[0061] In addition, if there are descriptions involving "first", "second", etc. in the embodiments, the descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or implying the importance of the relative description or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features.

Claims

1. A blade structure for a gas turbine compressor, arranged on a power shaft (11) of a gas turbine (1), characterized in that: include: A mounting plate (21) fixedly sleeved on the power shaft (11); A blade body (22) is plugged and fixed on the mounting plate (21); A fixing device (3), arranged on the mounting plate (21) and connected to the blade body (22), and used for fixing the blade body (22); An abutment plate (211) is arranged on the mounting plate (21); The second elastic member (37) is fixedly arranged on the abutting plate (211).

2. The blade structure of the gas turbine compressor according to claim 1, characterized in that: The fixing device (3) comprises a mounting plate (31) fixed on the mounting plate (21), an adjusting rod (32) passing through the mounting plate (31), and a fixing block (33) fixed on the side of the adjusting rod (32) close to the blade body (22); the fixing block (33) is snap-fitted and fixed on the blade body (22); and a fixing groove (22201) for fixing the fixing block (33) is provided at a position of the blade body (22) corresponding to the fixing block (33).

3. The blade structure of the gas turbine compressor according to claim 2, characterized in that: The adjusting rod (32) is located between the fixing block (33) and the mounting plate (31) and is sleeved with a first elastic member (34).

4. The blade structure of a gas turbine compressor according to claim 2, characterized in that: A threaded section (35) is provided between the adjusting rod (32) and the mounting plate (31); the adjusting rod (32) is slidably sleeved inside the threaded section (35); and the threaded section (35) is penetrated on the mounting plate (31).

5. The blade structure of the gas turbine compressor according to claim 4, characterized in that: An adjusting nut (36) is rotatably provided on a side of the mounting plate (31) away from the fixing block (33), and the adjusting nut (36) is threadedly connected to the threaded section (35).

6. The blade structure of a gas turbine compressor according to claim 5, characterized in that: The adjusting nut (36) is provided with a rotating rod (361).

7. The blade structure of a gas turbine compressor according to claim 4, characterized in that: A limit block (321) is arranged on the outer side of the adjusting rod (32), and the limit block (321) is slidably arranged inside the threaded section (35). A limit groove (3501) for the limit block (321) to move is opened at a position of the threaded section (35) corresponding to the limit block (321).

8. The blade structure of a gas turbine compressor according to claim 2, characterized in that: The fixing block (33) is arranged in a wedge shape.

9. The blade structure of a gas turbine compressor according to claim 1, characterized in that: A clamping block (221) is provided at the lower end of the blade body (22); the clamping block (221) is plugged and fixed in the mounting plate (21); and a clamping groove (2101) for fixing the clamping block (221) is provided on the mounting plate (21).

10. The blade structure of the gas turbine compressor according to claim 9, characterized in that: A plug-in block (222) is fixed at the lower end of the clamping block (221); a low joint (2221) is provided on a side of the plug-in block (222) close to the abutment plate (211); the width of the plug-in block (222) gradually decreases in a direction close to the low joint (2221); the shape of the clamping groove (2101) is arranged corresponding to the shape of the plug-in block (222); the low joint (2221) abuts against the second elastic member (37); and a mounting groove (2102) is provided on the mounting plate (21) at a position corresponding to the fixing device (3).

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