CN216714553U - Rotatable guide vane rotating mechanism control actuating cylinder of gas turbine - Google Patents
Rotatable guide vane rotating mechanism control actuating cylinder of gas turbine Download PDFInfo
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- CN216714553U CN216714553U CN202123122053.5U CN202123122053U CN216714553U CN 216714553 U CN216714553 U CN 216714553U CN 202123122053 U CN202123122053 U CN 202123122053U CN 216714553 U CN216714553 U CN 216714553U
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Abstract
The utility model relates to a rotatable guide vane rotating mechanism control actuating cylinder of a gas turbine, which comprises a control piston, a cover, a control actuating cylinder shell, a first nut, a first thrust block, a second thrust block, a control spring, a pipe joint, a control actuating cylinder inner cavity L and a restricted flow hole E, wherein the control piston is connected with the control piston through a first thrust block; the control actuating cylinder shell and the cover form a sealed chamber so as to control the action of the piston; the control spring is arranged between the thrust block and the control piston, the initial position of the control piston and the compression amount of the control spring are positioned by the first thrust block and the second thrust block, the first nut locks the first thrust block, the flow limiting hole E is arranged at the upper end of the control actuating cylinder shell, and the pipe joint is arranged at the lower end of the control actuating cylinder shell and communicated with high-pressure gas in the gas turbine compressor. The utility model solves the problem of insufficient margin under the low working condition running state of the gas turbine compressor by adjusting the angle of the rotatable guide vane, and realizes the self-adaptive adjustment of the working condition of the compressor and the angle of the rotatable guide vane.
Description
(I) technical field
The utility model belongs to the machinery manufacturing industry, and particularly relates to a control actuating cylinder of a rotatable guide vane rotating mechanism of a gas turbine.
(II) background of the utility model
The rotatable guide vane technology of the gas turbine is used for effectively solving the problems of low working condition, variable working condition and insufficient margin of the gas turbine, is often applied to the design of the gas turbine, has a large rotating angle range of the rotatable guide vane of the gas turbine, is relatively complex in movement of a rotatable guide vane executing mechanism for pushing the rotatable guide vane to rotate, and has high requirements on precision and driving force of a power source.
In order to meet the requirement of a gas turbine on meeting the parameter of efficiency and the like, the rotatable guide vane is adjusted only when the surge margin is low, so that the power source of the rotatable guide vane executing mechanism is required to act in part of time, and a simple structural form is required.
(III) the contents of the utility model
The utility model aims to solve the problem of insufficient margin under the low working condition operation state of a gas turbine compressor by adjusting the angle of the rotatable guide vane, the control actuating cylinder adjusts the rotation angle of the rotatable guide vane by controlling and pushing the main actuating cylinder of the rotatable guide vane rotating mechanism, and the self-adaptive adjustment of the working condition of the compressor and the angle of the rotatable guide vane is realized, the rotatable guide vane of the compressor does not act under the working condition with larger margin of the gas turbine, and the rotatable guide vane of the compressor acts to ensure that the margin meets the requirement under the working condition with smaller margin.
The purpose of the utility model is realized by the following steps:
a rotatable guide vane rotating mechanism control actuator cylinder of a gas turbine comprises a control piston, a cover, a control actuator cylinder shell, a first nut, a first thrust block, a second thrust block, a control spring, a pipe joint, a control actuator cylinder inner cavity L and a restricted flow hole E; the control actuating cylinder shell and the cover are fastened through a second nut to form a sealed cavity so as to control the action of the piston, the initial position of the control piston and the compression amount of the control spring are positioned by a first thrust block and a second thrust block, the first nut locks the first thrust block, a flow limiting hole E is formed in the upper end of the control actuating cylinder shell and communicated with the main actuating cylinder, and a pipe joint is formed in the lower end of the control actuating cylinder shell and communicated with high-pressure gas in the gas turbine compressor; high-pressure gas enters the control actuator cylinder through the pipe joint, a part of high-pressure gas enters the inner cavity L, a part of high-pressure gas is led to the main actuator cylinder through the flow limiting hole E, the margin is gradually insufficient along with the continuous rising of the working condition of the gas turbine, the acting force of the air pressure on the control piston is larger than the elastic force of the control spring, the control piston acts, then the power piston of the main actuator cylinder acts along with the high-pressure gas, the rotatable guide vane rotating mechanism is pushed to drive the rotatable guide vane to rotate, along with the falling of the working condition of the gas turbine, the acting force of the air pressure of the inner cavity L on the control piston is smaller than the elastic force of the control spring, the control piston begins to reset and is separated from the power piston of the main actuator cylinder, and then the power piston begins to reset until the original position is recovered.
Further, a cover nut is arranged on the first nut;
furthermore, a leather cup is arranged between the control piston and the control actuating cylinder shell.
Compared with the prior art, the utility model has the following beneficial effects:
the structure of the utility model adopts the high-pressure gas introduced into the gas compressor to push the power piston of the control actuator cylinder to work, when the starting process and the working condition of the gas turbine are lower, the surge margin of the gas turbine meets the requirement, the control piston does not act, the working condition continues to rise, the surge margin becomes lower, the bleed gas compressor increases along with the rise of the working condition, the acting force of the high-pressure chamber of the control piston is greater than the resultant force of the acting force of the low-pressure chamber and the elastic force of the control spring, the control piston starts to operate, after the bleed gas pressure of the gas compressor continues to rise, the power piston of the main actuator cylinder starts to operate, and the rotatable guide vane actuating mechanism pushes the rotatable guide vane to rotate is realized.
(IV) description of the drawings
FIG. 1 is a schematic diagram of a control ram mechanism;
FIG. 2 is a schematic view of a vent of the control actuator;
FIG. 3 is a schematic diagram of a cup for the control piston.
(V) detailed description of the preferred embodiments
The utility model will be further described with reference to the following drawings and detailed description:
referring to fig. 1, a control actuator of a rotatable guide vane rotating mechanism of a gas turbine compressor comprises a control piston 1, a cover 2, a control actuator shell 3, a leather cup 4, a first nut 5, a cover nut 6, a first thrust block 7, a second thrust block 8, a second nut 9, a first bushing 10, a second bushing 11, a control spring 12, a spring seat 13, a screw 14, a first gasket 15, a first sealing ring 16, a second sealing ring 17, a second gasket 18, a third sealing ring 19, a first gasket 20, a lead seal 21, a pipe joint 22, a second gasket 23, a control actuator cavity L and a restricted flow hole E; the control cylinder shell 3 and the cover 2 are fastened by a second nut 9 to form a sealed chamber so as to control the action of the piston 1; the initial position of the control piston 1 and the compression of the control spring 12 are positioned by a first thrust block 7 and a second thrust block 8, the first nut 5 locks the first thrust block 7, a restricted orifice E is provided at the upper end of the control actuator housing 3 and communicates with the primary actuator, a coupling 22 is provided at the lower end of the control actuator housing 3, the high-pressure gas is communicated with the high-pressure gas in the compressor of the gas turbine, the high-pressure gas enters the control actuating cylinder through the pipe joint 22, one part of the high-pressure gas enters the inner cavity L, one part of the high-pressure gas passes through the flow limiting hole E and is led to the main actuating cylinder, the margin is gradually insufficient along with the continuous rising of the working condition of the gas turbine, the acting force of the pressure on the control piston 1 is larger than the elastic force of the control spring 12, the action of the control piston 1 is controlled, and then the power piston of the main actuating cylinder acts therewith to push the rotatable guide vane rotating mechanism to drive the rotatable guide vane to rotate. The first nut 5 is provided with a cover nut 6, and a leather cup 4 is arranged between the control piston 1 and the control actuator cylinder shell 3.
The stiffness of the control spring 12 of the control ram is dependent on the amount of force applied by the incoming gas to the control piston 1; high-pressure air is sealed between the control piston 1 and the control actuator cylinder shell 3 through a leather cup 4, and meanwhile, the actuator cylinder shell 3 is controlled to be coated with lubricant to prevent the control piston 1 from being jammed. The low-pressure chamber of the control piston 1 has the functions of draining condensed water and heating the outer wall of the control actuating cylinder. The high-pressure gas in the gas compressor of the gas turbine can be used as a power source of the control actuator cylinder, the control actuator cylinder adjusts the action of the rotatable guide vane, when the surge margin of the gas turbine meets the requirement, the control actuator cylinder controls the rotatable guide vane to not act, the surge margin is reduced along with the rise of the working condition of the gas turbine, at the moment, the control actuator cylinder controls the action of the rotatable guide vane executing mechanism to push the rotatable guide vane to rotate, the surge margin of the gas turbine is increased, and when the working condition of the gas turbine is reduced, the control actuator cylinder controls the rotating mechanism to reset.
High-pressure air of a compressor introduced by the control actuator cylinder enters an inner cavity L of the control actuator cylinder through a pipe joint 22 after being purified and cooled, a part of high-pressure air flows into a power cavity of the main actuator cylinder through a flow limiting hole E, the acting force on the control piston 1 is balanced with the elastic force of the control spring 12 along with the increase of the air pressure supplied to the inner cavity L of the control actuator cylinder, the balance is broken along with the continuous increase of the air pressure supplied to the inner cavity L of the control actuator cylinder, and the control piston 1 starts to act until the high-pressure air is contacted with the power piston of the main actuator cylinder. Along with the reduction of the working condition of the gas turbine, the acting force of the air pressure supplied to the inner cavity L of the control actuator cylinder on the control piston 1 is smaller than the elastic force of the control spring 12, the control piston 1 starts to reset and is separated from the power piston of the main actuator cylinder, and then the power piston starts to reset until the power piston returns to the original position.
Referring to fig. 2, the casing 3 of the control actuator is provided with an exhaust hole, when the control actuator operates at a temperature lower than 0 ℃, the exhaust hole is opened, and the casing 3 of the control actuator is heated by high-temperature and high-pressure air, so that the control actuator is prevented from being frozen to cause failure of the control actuator, and the operation reliability of the control actuator is improved.
Referring to fig. 3, a packing cup 4 is provided between the control piston 1 of the control actuator and the control actuator housing 3 to seal during operation and ensure a pressure difference between both sides of the control piston 1.
The working principle of the utility model is as follows: the working condition of the gas turbine is increased, the gas pressure in the gas compressor is increased, the acting force of the gas pressure on the control piston 1 is smaller than the elastic force of the spring, and the surge margin of the gas turbine meets the requirement at the moment. Along with the continuous rising of gas turbine operating mode, the margin is less than gradually, and atmospheric pressure is greater than spring force to the effort of control piston 1, and control piston 1 action, and then the power piston of main actuator cylinder moves thereupon, promotes rotatable stator slewing mechanism and drives rotatable stator rotation, has realized increasing gas turbine surge margin, specifically as follows:
the power source of the control actuator cylinder is from bleed air of through flow of the air compressor, and high-temperature and high-pressure air passes through a cooling purifier to filter impurities and cool the air before entering the control actuator cylinder; the purified and cooled high-pressure gas enters a control cavity of the control actuator cylinder, part of the gas is discharged out of the control cavity through a flow-limiting nozzle, when the gas pressure is lower, the surge margin of the gas turbine meets the requirement, and the control actuator cylinder does not act at the moment; when the working condition of the gas turbine rises, the surge margin is gradually reduced, the pressure in a control cavity of the control actuator cylinder rises along with the rise of the working condition, after a part of gas is discharged through the flow limiting nozzle, the acting force on the control piston and the elastic force of the control spring are in a balanced state, and along with the rise of the pressure of high-pressure gas, the control piston starts to act until the control piston is contacted with a power piston of the main actuator cylinder and then acts together with the power piston; when the gas turbine is in a working condition, the pressure of introduced high-pressure gas is gradually reduced, after a certain threshold value is reached, the elastic force of a control spring of the control piston is larger than the acting force of the gas on the control piston, the control piston is separated from a power piston of the main actuating cylinder, and at the moment, the main actuating cylinder starts to reset until the main actuating cylinder returns to the original position. The utility model can be applied to power source control systems of actuating mechanisms of rotatable guide vanes of gas turbines and aero-engines.
Claims (3)
1. A rotatable guide vane rotating mechanism control actuator cylinder of a gas turbine is characterized by comprising a control piston (1), a cover (2), a control actuator cylinder shell (3), a first nut (5), a first thrust block (7), a second thrust block (8), a control spring (12), a pipe joint (22), a control actuator cylinder inner cavity L and a restricted orifice E; the control actuating cylinder shell (3) and the cover (2) are fastened through a second nut (9) to form a sealed chamber so as to control the action of the piston (1); the initial position of a control piston (1) and the compression amount of a control spring (12) are positioned by a first thrust block (7) and a second thrust block (8), a first nut (5) locks the first thrust block (7), a flow limiting hole E is arranged at the upper end of a control actuating cylinder shell (3) and is communicated with a main actuating cylinder, a pipe joint (22) is arranged at the lower end of the control actuating cylinder shell (3) and is communicated with high-pressure gas in a gas turbine compressor, the high-pressure gas enters the control actuating cylinder through the pipe joint (22), a part of the high-pressure gas enters an inner cavity L, a part of the high-pressure gas passes through the flow limiting hole E and is communicated with the main actuating cylinder, along with the continuous rising and gradual shortage of margin of the working condition of the gas turbine, the acting force of the air pressure on the control piston (1) is greater than the elastic force of the control spring (12), the control piston (1) acts, and then the power piston of the main actuating cylinder acts along with the flow limiting hole E, the rotatable guide vane rotating mechanism is pushed to drive the rotatable guide vane to rotate, along with the work condition reduction of the gas turbine, the acting force of the air pressure of the inner cavity L on the control piston (1) is smaller than the elastic force of the control spring (12), the control piston (1) starts to reset, the control piston is separated from the power piston of the main actuating cylinder, and then the power piston starts to reset until the power piston returns to the original position.
2. A gas turbine rotatable vane turning mechanism control ram according to claim 1, wherein a cage nut (6) is provided on the first nut (5).
3. A rotatable vane turning mechanism control ram of a gas turbine according to claim 1 or 2 characterised in that a cup (4) is provided between the control piston (1) and the control ram housing (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123122053.5U CN216714553U (en) | 2021-12-13 | 2021-12-13 | Rotatable guide vane rotating mechanism control actuating cylinder of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123122053.5U CN216714553U (en) | 2021-12-13 | 2021-12-13 | Rotatable guide vane rotating mechanism control actuating cylinder of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216714553U true CN216714553U (en) | 2022-06-10 |
Family
ID=81882728
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123122053.5U Active CN216714553U (en) | 2021-12-13 | 2021-12-13 | Rotatable guide vane rotating mechanism control actuating cylinder of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216714553U (en) |
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2021
- 2021-12-13 CN CN202123122053.5U patent/CN216714553U/en active Active
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