High-load turbine blade tip clearance adjusting structure

Abstract

The invention provides a high-load turbine blade top clearance adjusting structure which comprises a casing, a turbine, a sealing stop block and a pushing mechanism, the turbine, the sealing stop block and the pushing mechanism are arranged in the casing, the sealing stop block is arranged at the position, corresponding to the turbine, of the inner wall of the casing, and a blade top clearance is formed between an inclined face structure of the sealing stop block and a blade top of the turbine. And a pushing mechanism for pushing the sealing baffle block to axially move in the casing is arranged on the inner wall of the casing. According to the high-load turbine blade top clearance adjusting structure, by arranging the inclined plane structure, the sliding mechanism and other components, the size of the blade top clearance can be adjusted in the axial moving process of the sealing check block, and the good sealing effect is guaranteed.

Description

Technical Field

[0001] The invention belongs to the technical field of impeller rotating machinery, and in particular relates to a high-load turbine blade tip clearance adjustment structure. Background Art

[0002] In order to improve the efficiency of the turbine, it is necessary to reduce the turbine blade tip clearance. However, the blade tip clearance is affected by temperature and operating conditions. Too large a blade tip clearance will reduce the turbine efficiency, while too small a blade tip clearance may cause scraping and collision between the blades and the casing, causing equipment damage. Therefore, how to control the leakage of high-load turbine blade tip clearance is a difficult problem that needs to be solved urgently. Summary of the invention

[0003] In view of this, the present invention aims to provide a high-load turbine blade tip clearance adjustment structure to solve the problem that the turbine blade tip clearance cannot be adjusted.

[0004] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0005] A high-load turbine blade tip clearance adjustment structure comprises a casing and a turbine arranged inside the casing, a sealing block and a driving mechanism, wherein a sealing block is provided at a position of the inner wall of the casing corresponding to the turbine, a blade tip clearance is formed between the inclined surface structure of the sealing block and the blade tip of the turbine, and a driving mechanism is provided on the inner wall of the casing for driving the sealing block to move axially in the casing.

[0006] Furthermore, a slide groove is provided on the inner wall of the casing, and a sealing block is provided on the inner wall of the casing at an outer position corresponding to the turbine, and the sealing block is installed in the slide groove.

[0007] Furthermore, a sealing belt is provided on the inclined surface of the sealing stopper, and the sealing belt is a circular ring body with a taper, and a blade tip gap is formed between the sealing belt and the blade tip of the turbine.

[0008] Furthermore, the sealing block is located on the high-pressure side of the turbine, and the driving mechanism is located on the low-pressure side of the turbine.

[0009] Furthermore, when the sealing stopper moves to the right through the pushing mechanism, the distance between the conical surface of the sealing belt and the blade top decreases.

[0010] Furthermore, a baffle is installed inside the casing, a spring is installed between the baffle and the sealing block, and the telescopic rod of the pushing mechanism passes through the through hole in the middle of the baffle and is fixedly connected to the spring.

[0011] Furthermore, a sealing block is provided between the sealing stopper and the casing.

[0012] Furthermore, the casing is provided with a stopper on the outer side of the sealing stopper.

[0013] Furthermore, the pushing mechanism is a telescopic cylinder.

[0014] Compared with the prior art, the high-load turbine blade tip clearance adjustment structure of the present invention has the following advantages:

[0015] (1) The high-load turbine blade tip clearance adjustment structure described in the present invention realizes the adjustment of the blade tip clearance size during the axial movement of the sealing block by providing components such as an inclined surface structure and a sliding mechanism, thereby ensuring a good sealing effect.

[0016] (2) In the high-load turbine blade tip clearance adjustment structure described in the present invention, a spring is provided between the pushing mechanism and the sealing block to facilitate resetting the pushing mechanism.

[0017] (3) In the high-load turbine blade tip clearance adjustment structure described in the present invention, a stopper is provided on the inner wall of the casing, which can reduce the lateral force of the gas working medium on the sealing stopper. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0019] Figure 1 It is a schematic diagram of a high-load turbine blade tip clearance adjustment structure according to an embodiment of the present invention.

[0020] Description of reference numerals:

[0021] 10. Casing; 11. Slide; 20. Turbine; 21. Blade; 22. Blade tip; 30. Sealing block; 32. Stop platform; 33. Sealing block; 40. Pushing mechanism; 50. Sealing belt; 55. Blade tip clearance; 60. Spring; 70. Baffle; 80. Downstream pipeline. DETAILED DESCRIPTION

[0022] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0023] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0024] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0025] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0026] A high-load turbine blade tip clearance adjustment structure, such as Figure 1 As shown, it includes a casing 10 and a turbine 20, a sealing block 30, a sealing block 33 and a driving mechanism 40 arranged inside the casing 10. The sealing block 30 is provided on the inner wall of the casing 10 at a position corresponding to the turbine 20. The sealing block 30 is provided with an inclined surface structure. A blade tip gap 55 is formed between the inclined surface structure and the blade tip 22 of the turbine 20. The inner wall of the casing 10 is provided with a driving mechanism 40 for driving the sealing block 30 to move axially in the casing 10.

[0027] The turbine 20 is rotatably connected to the casing 10 . A plurality of blades 21 are disposed on the turbine 20 . One side of the casing 10 is connected to a downstream pipeline 80 .

[0028] The inner wall of the casing 10 is provided with a slide groove 11, and a sealing block 30 is provided at the inner wall of the casing 10 corresponding to the outer position of the turbine 20, and the sealing block 30 is installed in the slide groove 11. The inner wall of the casing 10 is also provided with a pushing mechanism 40 for pushing the sealing block 30 to move axially in the slide groove 11. It can be understood that due to the inclined structure of the sealing block 30, when the sealing block 30 moves axially through the pushing mechanism 40, the minimum distance between it and the blade tip is constantly changing, so as to facilitate the adjustment of the size of the blade tip clearance.

[0029] In one or more embodiments, a sealing belt 50 is fixed to the surface of the inclined structure. The sealing belt 50 is a circular ring structure with a taper. On the one hand, it is to fit the inclined structure. On the other hand, the side close to the turbine 20 is still an inclined surface, which is convenient for adjusting the blade tip clearance. A blade tip clearance 55 is formed between the sealing belt 50 and the blade tip of the turbine 20. Through the setting of the blade tip clearance 55, direct contact between the blade tip 22 and the sealing belt 50 is avoided.

[0030] The sealing block 30 is installed on the high-pressure side of the turbine 20 , and the pushing mechanism 40 is a telescopic cylinder, and the pushing mechanism 40 is arranged on the low-pressure side of the turbine 20 .

[0031] When the sealing stopper 30 is moved to the right by the pushing mechanism 40 , the minimum distance between the conical surface of the sealing band 50 and the blade tip is reduced.

[0032] In one or more embodiments, a baffle 70 is fixedly installed inside the receiver 10, a spring 60 is installed between the baffle 70 and the sealing block 30, and the telescopic rod of the telescopic lever passes through the through hole in the middle of the baffle 70 and is fixedly connected to the spring 60. The spring 60 is provided to facilitate the reset of the pushing mechanism 40.

[0033] Furthermore, a sealing block 33 is provided between the sealing block 30 and the casing 10 to reduce leakage of the working fluid between the sealing block 30 and the casing 10 .

[0034] In one or more embodiments, a stopper 32 is fixed to the casing 10 on the outer side of the sealing stopper 30 . The setting of the stopper 32 can reduce the lateral force of the flow of the gas working medium on the sealing stopper 30 .

[0035] The structure of the high-load turbine blade tip clearance leakage control can adjust the blade tip clearance size during the axial movement of the sealing block by setting the pushing mechanism and the inclined surface structure. In addition, a spring is provided between the pushing mechanism and the sealing block to facilitate the reset of the pushing mechanism. In addition, a stop is also provided on the inner wall of the casing to reduce the lateral force of the gas working medium on the sealing block.

[0036] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A high-load turbine blade tip clearance adjustment structure, characterized in that: The invention comprises a casing and a turbine, a sealing block and a driving mechanism arranged inside the casing. A sealing block is arranged on the inner wall of the casing at a position corresponding to the turbine, a blade tip gap is formed between the inclined surface structure of the sealing block and the blade tip of the turbine, and a driving mechanism is arranged on the inner wall of the casing for driving the sealing block to move axially in the casing.

2. A high-load turbine blade tip clearance adjustment structure according to claim 1, characterized in that: The inner wall of the casing is provided with a slide groove, and a sealing block is provided at an outer position of the inner wall of the casing corresponding to the turbine, and the sealing block is installed in the slide groove.

3. The high-load turbine blade tip clearance adjustment structure according to claim 1, characterized in that: A sealing belt is arranged on the inclined surface of the sealing stopper. The sealing belt is a circular ring body with a taper. A blade tip gap is formed between the sealing belt and the blade tip of the turbine.

4. The high-load turbine blade tip clearance adjustment structure according to claim 1, characterized in that: The sealing block is located on the high-pressure side of the turbine and the driving mechanism is located on the low-pressure side of the turbine.

5. The high-load turbine blade tip clearance adjustment structure according to claim 3, characterized in that: When the sealing stopper moves to the right through the pushing mechanism, the distance between the conical surface of the sealing belt and the blade top decreases.

6. The high-load turbine blade tip clearance adjustment structure according to claim 1, characterized in that: A baffle is installed inside the receiver, a spring is installed between the baffle and the sealing block, and the telescopic rod of the pushing mechanism passes through the through hole in the middle of the baffle and is fixedly connected to the spring.

7. The high-load turbine blade tip clearance adjustment structure according to claim 1, characterized in that: A sealing block is arranged between the sealing stopper and the casing.

8. The high-load turbine blade tip clearance adjustment structure according to claim 1, characterized in that: The casing is provided with a stopper on the outer side of the sealing stopper.

9. The high-load turbine blade tip clearance adjustment structure according to claim 1, characterized in that: The driving mechanism is a telescopic cylinder.

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