CN215333648U - Rotation adjusting mechanism of gas compressor air inlet guide vane of gas turbine - Google Patents
Rotation adjusting mechanism of gas compressor air inlet guide vane of gas turbine Download PDFInfo
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- CN215333648U CN215333648U CN202122993216.0U CN202122993216U CN215333648U CN 215333648 U CN215333648 U CN 215333648U CN 202122993216 U CN202122993216 U CN 202122993216U CN 215333648 U CN215333648 U CN 215333648U
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- inlet guide
- guide vane
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Abstract
The utility model belongs to the technical field of gas turbines, and particularly relates to a rotation adjusting mechanism of a gas compressor inlet guide vane of a gas turbine, which comprises a telescopic pull rod, a transmission connecting arm, a transmission pull rod, a synchronous adjusting ring and a driven rocker arm; a plurality of air inlet guide vanes are annularly distributed on an air inlet section of the air compressor; the synchronous adjusting ring is sleeved outside a casing at the air inlet section of the air compressor; the transmission pull rod is rotationally connected between the transmission connecting arm and the synchronous adjusting ring; the telescopic pull rod is rotatably connected to the transmission connecting arm; the synchronous adjusting ring is connected with the air inlet guide vanes through the driven rocker arm and can drive all the air inlet guide vanes to rotate synchronously. The cooperative transmission effect of each structure in the scheme can stably control all the air inlet guide vanes to synchronously rotate, so that the angle of the air inlet guide vanes can be accurately controlled, and the control error of the angle can reach +/-0.1 degrees in the use process; the maximum rotation angle of the air inlet guide vane reaches 38.5 degrees, and the air inlet guide vane has the advantage of high regulation stability.
Description
Technical Field
The utility model belongs to the technical field of gas turbines, and particularly relates to a rotation adjusting mechanism for an air inlet guide vane of a gas compressor of a gas turbine.
Background
A gas turbine is an internal combustion type power machine that converts energy of gas into useful work, and is widely used in the field of civil power generation or as a power device for use in airplanes or large ships. The working process of the gas turbine is as follows: the air compressor continuously sucks air from the atmosphere and compresses the air; the compressed air enters a combustion chamber, is mixed with gas sprayed in the combustion chamber and then is combusted to form high-temperature gas, then the high-temperature gas flows into a gas turbine to expand and do work, and the high-temperature gas is used for pushing the turbine to drive a gas compressor to rotate together; the gas turbine is a device with good cleaning performance and high efficiency, and has the advantages of small volume, low weight and the like.
Since the advent of the gas turbine, the gas turbine has gained wide acceptance both at home and abroad due to its advantages of high power, small volume, fast start, stable operation and the use of various fuels, and a great deal of research work has been carried out by many scientific and technological workers both at home and abroad, and has been developed in a leap-over manner in a short time. The merits of the state of the art in gas turbines also reflect both the state of the art and the military strength.
Compressor surge often occurs in the operation process of the gas turbine, and the compressor surge phenomenon refers to the phenomenon that the whole compression system works unstably due to low-frequency and high-amplitude airflow oscillation generated by airflow in the axial direction of the gas turbine. Research shows that the root cause of surge is serious separation and unsmooth circulation of airflow in a blade channel of a compressor; when surging occurs, the gas compressor is easy to work unstably, so that the actual working state of the gas turbine is seriously deviated from the designed working state, the working characteristics of the gas turbine are influenced, the gas turbine is slightly flamed out and stopped, and the blade is seriously broken and even the whole gas turbine is seriously damaged.
Therefore, to prevent the occurrence of surge, an inlet guide is typically provided in the inlet section of the compressor, the inlet guide including a plurality of inlet guide vanes rotatable about respective vane axes. The air inlet guide vane can be properly adjusted at a certain angle according to different conditions of the operating rotating speed, the air flow, the air inlet parameters and the like of the gas turbine, so that the air flow entering the air compressor can be adjusted, and the surge degree of the air compressor is obviously reduced.
The existing angle adjusting mechanism of the air inlet guide vane has the defects of complex structural form, insufficient adjusting capability, poor adjusting angle and precision and the like; therefore, it is an urgent problem to design a new rotation adjusting structure for the inlet guide vane.
SUMMERY OF THE UTILITY MODEL
In order to solve the problem of angle adjustment of the air inlet guide vane at the air inlet section of the air compressor of the existing gas turbine, the scheme provides a rotation adjusting mechanism of the air inlet guide vane of the air compressor of the gas turbine.
The technical scheme adopted by the utility model is as follows:
a rotation adjusting mechanism of a gas compressor air inlet guide vane of a gas turbine comprises a telescopic pull rod, a transmission connecting arm, a transmission pull rod, a synchronous adjusting ring and a driven rocker arm;
a plurality of air inlet guide vanes are annularly distributed on an air inlet section of the air compressor, and each air inlet guide vane can rotate; the synchronous adjusting ring is sleeved outside a casing at the air inlet section of the air compressor;
the transmission pull rod is rotationally connected between the transmission connecting arm and the synchronous adjusting ring; the telescopic pull rod is rotatably connected to the transmission connecting arm and can control the synchronous adjusting ring to move by taking one point on the transmission connecting arm as a lever fulcrum; the synchronous adjusting ring is connected with the air inlet guide vanes through the driven rocker arm and can drive all the air inlet guide vanes to rotate synchronously.
As a complement or alternative to the above-described rotation adjustment mechanism: a driving assembly is arranged on the outer side of a casing of the air inlet section of the air compressor, the driving assembly comprises a driving seat, a driving motor and the telescopic pull rod, and the driving seat is fixed on the outer wall of the casing; the driving motor is fixed on the driving seat and can control the telescopic action of the telescopic pull rod.
As a complement or alternative to the above-described rotation adjustment mechanism: one end of the transmission pull rod is rotatably connected with a transmission seat which is fixedly connected to the synchronous adjusting ring.
As a complement or alternative to the above-described rotation adjustment mechanism: the lever fulcrum is arranged in the middle of the transmission connecting arm, one end of the transmission connecting arm rotates with the transmission pull rod, and the other end of the transmission connecting arm is rotatably connected with the telescopic pull rod.
As a complement or alternative to the above-described rotation adjustment mechanism: guide vane end shafts are respectively arranged at the inner end and the outer end of the air inlet guide vane, and the air inlet guide vane can be controlled to rotate through the guide vane end shaft at the outer end; the guide vane end shaft at the outer end of the air inlet guide vane penetrates out of the casing and is connected with a driven rocker arm, and the driven rocker arm is vertically connected with the guide vane end shaft.
As a complement or alternative to the above-described rotation adjustment mechanism: one end of the driven rocker arm is fixedly connected with a driven ring sleeve, and the other end of the driven rocker arm is rotatably connected with a driven connecting sheet; the driven connecting sheet is fixedly connected to the synchronous adjusting ring; the driven ring sleeve is connected with the guide vane end shaft through a driven pin.
As a complement or alternative to the above-described rotation adjustment mechanism: the end face of one side, facing the driven rocker arm, of the synchronous adjusting ring is provided with a plurality of grooves, and the grooves are used for installing the driven connecting pieces in a one-to-one correspondence mode.
As a complement or alternative to the above-described rotation adjustment mechanism: the outer wall of the casing is provided with a guide fixing piece, one end of the guide fixing piece is forked and can limit, guide or fix the driven rocker arm.
As a complement or alternative to the above-described rotation adjustment mechanism: the synchronous adjusting ring is made of light alloy; the thickness of the synchronous adjusting ring is 18-20 mm.
As a complement or alternative to the above-described rotation adjustment mechanism: an inner support ring is arranged on the inner side of the casing and is rotationally connected with all the air inlet guide vanes
The utility model has the beneficial effects that:
1. according to the scheme, all the air inlet guide vanes can be stably controlled to rotate synchronously through the cooperative transmission action of the structures such as the telescopic pull rod, the transmission connecting arm, the transmission pull rod, the synchronous adjusting ring and the driven rocker arm, so that the angle of the air inlet guide vanes can be accurately controlled, and the control error of the angle can reach +/-0.1 degrees in the use process; the maximum rotation angle of the air inlet guide vane reaches 38.5 degrees, the air inlet guide vane adjusting device has the advantage of high adjusting stability, and after the air inlet guide vane adjusting device is connected into an automatic control system for gas operation, the air inlet guide vane adjusting device can realize quick control according to corresponding surge alarming and automatic adjusting instructions, so that the control requirements of a gas turbine on the angle of the air inlet guide vane under different working conditions are met;
2. the synchronous adjusting ring in the scheme can be made of light alloy such as aluminum alloy and the like, and the thickness of the synchronous adjusting ring is generally 18-20 mm; therefore, the rotation adjusting mechanism has the advantages of light weight, good manufacturability, low cost and the like;
3. the synchronous adjusting ring is provided with grooves, and the grooves and the air inlet guide vanes are in one-to-one correspondence, so that the constancy and the stability of the connecting position of the driven connecting sheet are ensured, and the rotation uniformity of the air inlet guide vanes is further ensured;
4. and the mounting that sets up outside the machine casket can play spacing, direction and fixed action to can fix whole rotation adjustment mechanism through this direction mounting in the transportation, thereby avoid causing collision and damage because of each spare part drunkenness.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below.
FIG. 1 is a structural diagram of a radial side view angle of a rotation adjusting mechanism of an air inlet guide vane of a gas turbine compressor in the scheme;
fig. 2 is a structural diagram of an axial side view angle of a rotation adjusting mechanism of an air inlet guide vane of a gas turbine compressor in the scheme.
In the figure: 1-a drive assembly; 11-a drive seat; 12-a drive motor; 13-a telescopic pull rod; 2-a transmission assembly; 21-a transmission seat; 22-a drive link; 23-a drive link arm; 3-a synchronous adjusting ring; 4-a driven assembly; 41-driven rocker arm; 42-a driven ring sleeve; 43-follower pin; 44-driven connecting piece; 5-air inlet guide vanes; 51-a vane end shaft; 6-mounting a base; 7-guiding fixing piece; 8-a casing; 9-inner support ring.
Detailed Description
The technical solutions in the embodiments will be described clearly and completely with reference to the accompanying drawings, and the described embodiments are only a part of the embodiments, but not all embodiments, and all other embodiments obtained by those skilled in the art without creative efforts will belong to the protection scope of the present solution based on the embodiments in the present solution.
Example 1
As shown in fig. 1 to 2, the present embodiment designs a rotation adjusting mechanism for an inlet guide vane of a compressor of a gas turbine.
The air inlet section of the gas turbine compressor is provided with a plurality of air inlet guide vanes 5, the air inlet guide vanes 5 are distributed annularly, each air inlet guide vane 5 can rotate around the respective blade shaft, the blade shaft of each air inlet guide vane 5 is a virtual shaft along the length direction of the air inlet guide vane 5, the inner end and the outer end of each air inlet guide vane 5 in the length direction are provided with a guide vane end shaft 51, and the guide vane end shaft 51 at the outer end of each air inlet guide vane 5 can control the rotation of the air inlet guide vane 5. An inner support ring 9 is arranged on the guide vane end shaft 51 at the inner end of the inlet guide vane 5, the inner support ring 9 is located inside the casing 8, and the inner support ring 9 is rotatably connected to all inlet guide vanes 5. The guide vane end shaft 51 positioned at the outer end of the air inlet guide vane 5 penetrates through the casing 8, and the guide vane end shaft 51 can be connected through a rotation adjusting mechanism, so that the rotation of the air inlet guide vane 5 is controlled.
The outer side wall of the casing 8 has an annular projection, and the annular projection can be used as the mounting seat 6 of the rotation adjusting mechanism.
The rotation adjusting mechanism comprises a driving assembly 1, a transmission assembly 2, a synchronous adjusting ring 3, a driven assembly 4 and other components.
The transmission assembly 2 comprises a transmission seat 21, a transmission pull rod 22, a transmission connecting arm 23 and other structures, when in use, the transmission connecting arm 23 plays a role of a lever, one point in the middle of the transmission connecting arm 23 serves as a fulcrum of the lever, the fulcrum of the lever can be connected to the mounting seat 6 through a pin, and the moment of the lever can be determined according to requirements. One end of the transmission connecting arm 23 rotates with the transmission pull rod 22, and the other end of the transmission connecting arm 23 rotates with the telescopic pull rod 13. When the telescopic pull rod 13 is telescopically operated, the transmission pull rod 22 can be moved along the length direction thereof. The end of the driving pull rod 22 far from the driving link arm 23 is connected to the driving seat 21 and is connected to the synchronization adjusting ring 3 through the driving seat 21, so that the synchronization adjusting ring 3 can be controlled to rotate around the center of the casing 8.
The synchronous adjusting ring 3 is a metal ring made of light alloy, and the synchronous adjusting ring 3 is sleeved outside a casing 8 at an air inlet section of the compressor when in use; and the thickness of the synchronization regulation ring 3 is 18-20 mm; a groove is formed in the position, corresponding to each air inlet guide vane 5, of the synchronous adjusting ring 3, so that after the synchronous adjusting ring 3 is connected with the air inlet guide vanes 5 through the driven assembly 4, the rotation angles of the air inlet guide vanes 5 can be the same.
The driven assembly 4 comprises a driven rocker arm 41, a driven ring sleeve 42, a driven pin 43, a driven connecting piece 44 and the like, wherein one end of the driven rocker arm 41 is fixedly connected with the driven ring sleeve 42, and the other end of the driven rocker arm 41 is rotatably connected with the driven connecting piece 44; the driven connecting pieces 44 are fixedly connected to the synchronous adjusting ring 3, grooves are formed in the end face of one side of the driven rocker arm 41 of the synchronous adjusting ring 3, the number of the grooves corresponds to the number of the driven connecting pieces 44 one by one, and the driven connecting pieces 44 can be connected into the corresponding grooves for fixing, so that the connection stability and the stability of the driven connecting pieces 44 are improved, the same connecting position of all the driven rocker arms 41 can be ensured, and the same rotation angle of all the air inlet guide vanes 5 is ensured; the driven ring 42 is connected to the vane end shaft 51 by a driven pin 43, and the driven pin 43 can fix the driven ring 42 to the vane end shaft 51. When in use, the length direction of the driven rocker arm 41 is perpendicular to the axial direction of the guide vane end shaft 51, and when the synchronous adjusting ring 3 rotates, the driven rocker arm 41 can control the rotation of the air inlet guide vane 5.
In the embodiment, when the synchronous adjusting ring is used, the driving motor 12 directly controls the telescopic pull rod 13 to perform telescopic action, and the telescopic pull rod 13 is rotatably connected with the transmission connecting arm 23, so that the transmission connecting arm 23 can drive the transmission pull rod 22 to perform telescopic movement by taking one point in the middle of the transmission connecting arm as a lever fulcrum, and at the moment, the synchronous adjusting ring 3 can be controlled to rotate by taking the center of the casing 8 as an axis. The synchronous adjusting ring 3 is connected with the corresponding air inlet guide vanes 5 through each driven rocker arm 41 so as to drive all the air inlet guide vanes 5 to synchronously rotate, thereby adjusting the air input of the air inlet section of the air compressor. Through the control of the rotation adjusting mechanism with the structure, all the air inlet guide vanes 5 can synchronously and stably rotate, the accurate control of the angles of the air inlet guide vanes 5 is ensured, and the control error of the angles can be controlled within +/-0.1 degrees; the maximum angle of rotation of the inlet guide vanes 5 can reach 38.5 °.
In addition, be provided with direction fixing part 7 on the outer wall of casket 8, the one end of direction fixing part 7 is the forked form of U-shaped, and this direction fixing part 7 is fixed on mount pad 6, and during the use, places driven rocker 41 of driven subassembly 4 in this forked structure to can realize spacing and the direction of driven rocker 41, can utilize the screw to carry out fixed connection with direction fixing part 7 driven rocker 41 in addition, thereby avoid whole gas turbine to arouse collision and damage because of spare parts such as synchro-adjusting ring 3 play in handling.
The above examples are merely for clearly illustrating the examples and are not intended to limit the embodiments; and are neither required nor exhaustive of all embodiments. And obvious variations or modifications of this technology may be resorted to while remaining within the scope of the technology.
Claims (10)
1. The utility model provides a rotation adjustment mechanism of gas turbine compressor inlet guide vane which characterized in that: comprises a telescopic pull rod (13), a transmission connecting arm (23), a transmission pull rod (22), a synchronous adjusting ring (3) and a driven rocker arm (41);
a plurality of air inlet guide vanes (5) are annularly distributed on the air inlet section of the air compressor, and each air inlet guide vane (5) can rotate; the synchronous adjusting ring (3) is sleeved outside a casing (8) at the air inlet section of the air compressor;
the transmission pull rod (22) is rotationally connected between the transmission connecting arm (23) and the synchronous adjusting ring (3); the telescopic pull rod (13) is rotationally connected to the transmission connecting arm (23) and can control the synchronous adjusting ring (3) to move by taking one point on the transmission connecting arm (23) as a lever fulcrum; the synchronous adjusting ring (3) is connected with the air inlet guide vanes (5) through the driven rocker arm (41) and can drive all the air inlet guide vanes (5) to synchronously rotate.
2. The mechanism of claim 1, wherein the mechanism further comprises: a driving assembly (1) is arranged on the outer side of a casing (8) of the air inlet section of the air compressor, the driving assembly (1) comprises a driving seat (11), a driving motor (12) and a telescopic pull rod (13), and the driving seat (11) is fixed on the outer wall of the casing (8); the driving motor (12) is fixed on the driving seat (11) and can control the telescopic action of the telescopic pull rod (13).
3. The mechanism of claim 1, wherein the mechanism further comprises: one end of the transmission pull rod (22) is rotatably connected with a transmission seat (21), and the transmission seat (21) is fixedly connected to the synchronous adjusting ring (3).
4. The mechanism of claim 1, wherein the mechanism further comprises: the lever fulcrum is arranged in the middle of the transmission connecting arm (23), one end of the transmission connecting arm (23) rotates with the transmission pull rod (22), and the other end of the transmission connecting arm (23) is rotatably connected with the telescopic pull rod (13).
5. The mechanism of claim 1, wherein the mechanism further comprises: guide vane end shafts (51) are respectively arranged at the inner end and the outer end of the air inlet guide vane (5), and the air inlet guide vane (5) can be controlled to rotate through the guide vane end shafts (51) at the outer end; a guide vane end shaft (51) at the outer end of the air inlet guide vane (5) penetrates out of the casing (8) and is connected with a driven rocker arm (41), and the driven rocker arm (41) is vertically connected with the guide vane end shaft (51).
6. The mechanism of claim 5, wherein the mechanism further comprises: one end of the driven rocker arm (41) is fixedly connected with a driven ring sleeve (42), and the other end of the driven rocker arm (41) is rotatably connected with a driven connecting sheet (44); the driven connecting sheet (44) is fixedly connected to the synchronous adjusting ring (3); the driven ring sleeve (42) is connected to the guide vane end shaft (51) by a driven pin (43).
7. The mechanism of claim 6, wherein: the end face of one side of the synchronous adjusting ring (3) facing the driven rocker arm (41) is provided with a plurality of grooves, and the grooves are used for installing the driven connecting pieces (44) in a one-to-one correspondence mode.
8. The mechanism of claim 1, wherein the mechanism further comprises: the outer wall of the casing (8) is provided with a guide fixing piece (7), one end of the guide fixing piece (7) is forked, and the driven rocker arm (41) can be limited, guided or fixed.
9. The mechanism of claim 1, wherein the mechanism further comprises: the synchronous adjusting ring (3) is made of light alloy; the thickness of the synchronous adjusting ring (3) is 18-20 mm.
10. The mechanism of claim 1, wherein the mechanism further comprises: an inner supporting ring (9) is arranged on the inner side of the casing (8), and the inner supporting ring (9) is rotatably connected with all the air inlet guide vanes (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122993216.0U CN215333648U (en) | 2021-12-02 | 2021-12-02 | Rotation adjusting mechanism of gas compressor air inlet guide vane of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122993216.0U CN215333648U (en) | 2021-12-02 | 2021-12-02 | Rotation adjusting mechanism of gas compressor air inlet guide vane of gas turbine |
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| Publication Number | Publication Date |
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| CN215333648U true CN215333648U (en) | 2021-12-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122993216.0U Active CN215333648U (en) | 2021-12-02 | 2021-12-02 | Rotation adjusting mechanism of gas compressor air inlet guide vane of gas turbine |
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| CN (1) | CN215333648U (en) |
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- 2021-12-02 CN CN202122993216.0U patent/CN215333648U/en active Active
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