An adjustable stator blade rotation device for a gas turbine and its design method

Abstract

An adjustable stationary vane rotation device and related method for a gas turbine are disclosed. The rotating ring of the adjustable stationary vane rotation device is connected to the adjustable stationary vane via a rocker arm assembly. The rotating ring is connected to two drive rods, each drive rod being connected to a drive device. The two drive rods are located on both sides of the rotating ring, with one drive rod connected to a main drive device and the other drive rod connected to a secondary drive device. An elastic compensation device is installed on the drive rod connected to either the secondary or main drive device. The elastic compensation device is used for synchronous compensation, ensuring that the movement trend of the rotating ring driven by the secondary and main drive devices is consistent and the cycle time is synchronized. The design method involves a dual drive system connecting the rotating ring, which balances the forces on the rotating ring. The axial rollers of the rotating ring are double-tracked. The gap between the track away from the rotating ring and the rotating ring is achieved through a combination of shims. Stress relief grooves are provided at the inner and / or outer diameters of the rotating ring.

Description

Technical Field

[0001] This invention belongs to the field of compressor technology in turbine manufacturing, specifically relating to an adjustable stator vane rotation device and design method for a gas turbine. Background Technology

[0002] Adjustable stationary vane mechanism is one of the important anti-surge measures for gas turbines. Under non-design conditions of the compressor, by adjusting the installation angle of the stationary vane to reduce the angle of attack of the airflow at the inlet of the next stage moving blade, airflow separation can be effectively suppressed, thereby improving the performance parameters of the compressor and the gas turbine as a whole under non-design conditions; most modern gas turbines adopt a multi-stage adjustable stationary vane structure.

[0003] The working process of adjustable stator blades is as follows: Generally, the controller sends a command to the actuator cylinder based on the received signals such as temperature and speed. The actuator cylinder's control lever drives the linkage ring to rotate, and the linkage ring drives the rocker arms of all guide vanes in that stage, so that all blades rotate synchronously to a corresponding angle. During the assembly process, each stage of adjustable stator blades needs to be rotated to its respective design angle and fixed before the blade tip grinding can be carried out. Then, each stage of adjustable stator blades needs to be rotated to its respective limit angle to determine the initial position of the actuator cylinder.

[0004] With the continuous development of gas turbine technology and the increasing performance requirements, the use of imported adjustable blades can effectively control the airflow direction and volume, change the surge margin, thereby improving the overall efficiency and safety. Therefore, gas turbine units often adopt a single-stage or multi-stage imported adjustable blade structure design.

[0005] like Figure 8 , Figure 9 As shown, the adjustable stationary vane 400 rotates along the rotation axis by rotating the vane root pin, achieving adjustment through the outer cylinder 200, copper sleeve 300, bushing 500, and inner ring 600. To ensure synchronous adjustment of all adjustable stationary vanes 400 at the same stage, a rotating ring connects the rocker arm assembly 100 of the adjustable structure on all vane root pins, forming a whole. This allows for synchronous rotation of all adjustable vanes by controlling the rotating ring. The rotating ring is supported by radial rollers 900, with at least three radial rollers supporting 900 to ensure rotation of the rotating ring 700 around the axis. Axial rollers 800 limit axial deviation, with at least three axial rollers supporting 800. A simplified structural diagram is shown below. Figure 10 , Figure 11 As shown, you can also refer to Figure 1 .

[0006] Publication No. CN114215612A discloses an adjustable stator vane and a turbine. The adjustable stator vane includes an inner ring, an outer ring, a stator blade, a sleeve, a connecting rod assembly, and a rotating mechanism. One end of the stator blade is disposed on the inner ring, and the other end is disposed on the outer ring. The sleeve is disposed between and connected to the stator blade and the connecting rod assembly. The connecting rod assembly connects the sleeve and the rotating mechanism. The adjustable stator vane of this invention changes the inlet and outlet airflow angles of the stator vane by adjusting its installation angle. By modifying the stator blade into an adjustable stator vane structure, the efficiency of the turbine under partial load conditions is improved.

[0007] Announcement No. CN112879351A discloses a fixing fixture for the adjustable stationary blade angle of a gas turbine compressor. The fixing fixture includes: a rocker arm for adjusting the angle of the adjustable stationary blade; a hollow connecting rod connected to the rocker arm for limiting the adjustment range of the adjustable stationary blade; and a sleeve for assisting in the connection between the rocker arm and the adjustable stationary blade. This invention provides a high-precision, easy-to-use, and consistent adjustable stationary blade angle fixing fixture through the cooperation of the rocker arm and the hollow connecting rod. This fixture has a simple structure, is easy to use, can quickly and accurately fix the blades of the adjustable stationary blade to a specific angle, and is easy to assemble and disassemble, with low cost.

[0008] Publication No. CN217652786U discloses a stator blade oscillation adjustment system for a gas turbine, including a stator blade mounting assembly, a stator blade adjustment assembly, and a drive assembly. The stator blade mounting assembly has multiple stator blades arranged in a ring, with the outer end of each stator blade radially engaging with the stator blade adjustment assembly. The drive assembly includes a telescopic unit, a stress sensor fixed to the output end of the telescopic unit, and a guide rod fixed to the stress sensor and coaxial with the telescopic unit. The telescopic unit can drive the stator blades to oscillate and adjust the blade direction through the transmission of the guide rod and the stator blade drive assembly. The advantage is that by driving the stator blade oscillation through the telescopic unit, when the stress value detected by the stress sensor exceeds a preset upper limit, the stress sensor feedback signal controls the state of the telescopic unit, causing it to reverse and revert, preventing equipment damage caused by forced actions and protecting structural safety.

[0009] like Figure 10 , Figure 11 As shown, the conventional adjustable stationary blade rotation mechanism uses a drive device to push or pull a pull rod, push rod, or drive rod 220 connected to the rotating ring 700, thereby driving the rotating ring 700 and driving the adjustable blade to rotate synchronously through the rocker arm assembly 100 connected to the rotating ring 700.

[0010] During actual operation of the unit, problems such as loosening (or deformation) of the connecting rod of the rocker arm assembly 100 and jamming during rotation of the rotating ring may occur. In severe cases, the connecting rod may break, causing the unit to trip and resulting in serious unit failure. Structural analysis and evaluation of the rotating mechanism revealed that, due to the angle of the connecting rod, the rotating ring bears a portion of the axial force during rotation. Because the rotating mechanism uses a connecting rod connection, space constraints necessitate adding axial roller supports (at least three) on one side of the rotating ring, only ensuring axial limitation on that side. Since the axial force direction is opposite when the blades move from "open" to "close" and from "close" to "open," this structure cannot effectively limit the axial displacement of the rotating ring. This transfers the axial force to the lateral radial roller supports, increasing frictional resistance and leading to further problems. In addition, the rotating ring is supported by radial rollers (at least 3 places) to control the center position. After the unit starts up and runs, due to thermal expansion, the rotating ring will be supported by the radial rollers and subjected to greater stress due to the difference in materials and operating temperature. This increases resistance and also increases the risk of jamming to some extent. Therefore, a greater mechanical driving force is required.

[0011] like Figure 7 When the drive device pushes and pulls the rotating ring 700, the rotating ring 700 drives the connecting rod 102, which in turn drives the rocker arm 101, causing the rocker arm 101 to rotate along the rotating shaft, which is also the rotating shaft of the adjustable stationary vane 400. At this time, the force pushing and pulling the rotating ring 700 can be divided into two components: one is the force that drives the connecting rod 102 to rotate the rocker arm 101, and the other is the force perpendicular to the rotating ring 700, which is the axial force. This force is the force that the rotating ring 700 bears when pushed and pulled, which is then evenly distributed to each rocker arm assembly 100. At position 00, the direction of the force remains unchanged. Each link 102 will generate a force on the vertical rotating ring 700, i.e., an axial component force. This force is the product of the force evenly distributed in the rotating ring 700 and the tangent of the included angle (between link 102 and rotating ring 700). Finally, the rotating ring 700 bears the resultant force of the axial component forces of all links 102. Therefore, when the rocker arm 101 and the rotating ring 700 have a certain angle, there is an axial component force on the rotating ring 700. The push and pull of the drive device are two processes, which results in the axial force on the rotating ring having two directions. Therefore, the axial roller limit on one side cannot satisfy the function of axial fixation.

[0012] In summary, existing gas turbine adjustable blade rotation mechanisms connected by connecting rods experience axial forces on the rotating ring during blade angle adjustment due to the angle of the connecting rods. When this axial force is significant, the presence of only one side with axial rolling supports (at least three points) for limiting axial displacement only on that side, leaving the other side unrestricted. This can lead to contact and collision between the rotating ring and the rollers of the radial rolling supports during unit operation, causing the rotating ring to jam, and in severe cases, even resulting in connecting rod breakage and unit shutdown. Furthermore, the rotating ring's center position is controlled by the radial roller support structure (at least three points). After unit startup, thermal expansion causes the rotating ring to be stretched and subjected to significant stress, further increasing the driving force for its rotation.

[0013] Faced with the aforementioned drawbacks, existing technologies lack effective countermeasures. There is a lack of effective technical measures to achieve adjustable stator blades in gas turbines and avoid the aforementioned problems such as connecting rod breakage and rotating ring jamming. Therefore, improvements are needed. Summary of the Invention

[0014] In view of this, and in response to the shortcomings of the existing technology, the purpose of this application is to provide an adjustable stator vane rotation device and design method for a gas turbine. This rotation mechanism can reduce the risk of rotating ring jamming during unit operation by adding a drive device, adding a stress relief groove, using a side baffle, or using a combination of the above solutions to a traditional rotation mechanism. When the rotating ring jams, it can also overcome the resistance caused by the jamming, thereby ensuring the safe and stable operation of the unit.

[0015] To achieve the above and other related objectives, this application provides an adjustable stationary vane rotation device for a gas turbine, including a rotating ring and a rocker arm assembly. The rocker arm assembly includes a rocker arm and a connecting rod. The rotating ring is connected to the adjustable stationary vane through the rocker arm assembly. The rotating ring is connected to two drive rods, and each drive rod is connected to a drive device.

[0016] Two drive rods are set on both sides of the rotating ring, and the drive rod on one side is connected to the main drive device, while the drive rod on the other side is connected to the auxiliary drive device. An elastic compensation device is set on the drive rod connected to the auxiliary drive device or the main drive device. The elastic compensation device is used for synchronous compensation so that the movement trend of the rotating ring driven by the auxiliary drive device and the main drive device is consistent and the rhythm is synchronized.

[0017] Traditional rotating mechanisms use a single drive unit to drive a connecting rod or tie rod, which adjusts the adjustable blades by pushing and pulling the rotating ring. One technical solution of this application features a dual-drive structure. This structure can provide greater driving force to overcome jamming when the rotating mechanism becomes stuck. Furthermore, it uses an elastic compensation device, such as a disc spring, on the secondary drive unit side for synchronous compensation, ensuring synchronized output from both drive units. The dual-drive system also balances the position of the rotating ring, preventing axial tilting and center eccentricity caused by positional imbalance during single-drive output, which could lead to jamming.

[0018] Each drive rod is connected to a drive device, or the drive rod itself can have a drive device. The two ends of the drive rod are hinged and have their own telescopic drive, which can also achieve dual drive.

[0019] The technical solution provided in this application also has the following technical features:

[0020] Preferably, in one embodiment of this application, the driving devices drive the rotating ring to move in the same direction, i.e., the rotating ring moves in the same direction. That is, the rotating ring moves in the same direction under the drive of the two driving devices, forming a consistent movement trend, i.e., the movement direction is consistent. Unless the driving devices malfunction, it should be ensured that during normal operation, the forces applied to the rotating ring by the two driving devices make the rotation direction of the rotating ring consistent, i.e., the rotation direction is consistent. For example, the driving devices drive the rotating ring through the driving rod, one is a thrust and the other is a pull. Since the driving devices are on both sides of the rotating ring, an effective synchronous dual-drive structure is formed.

[0021] Preferably, in one embodiment of this application, the direction of movement of the rotating ring is the same as the direction of rotation of the rotating ring; thereby, during the process of the rotating ring adjusting the blades, the rotating ring is driven smoothly, the driving force is reliable, and the movement is stable.

[0022] Preferably, in one embodiment of this application, one side of the axial roller abuts against the rotating ring to form track I, and the other side of the axial roller is provided with track II; during unit operation, at least one track of the axial roller is effectively abutted, thereby avoiding the risk of a single track derailing without being restricted; the axial roller refers to the roller whose axis of rotation is parallel to the axis of the adjustable stationary blade.

[0023] Preferably, in one embodiment of this application, track II is fixed to the rotating ring.

[0024] Preferably, in one embodiment of this application, a baffle is added to the rotating ring, and the baffle limits the axial roller to form track II, so that the axial sides of the rotating ring are restricted in displacement.

[0025] A baffle is added on the rotating ring, and this structure enables the unilateral axial roller support to change from a single track to double tracks. When the rollers bear axial forces in different directions, only a single track is in contact and plays a supporting role, thereby limiting the axial displacement of the rotating ring, avoiding jamming during rotation of the rotating ring, and ensuring safe operation of the unit; the supporting rollers adopt spherical rollers, which can also ensure good contact when the rotating ring is axially tilted.

[0026] Preferably, in an embodiment of the present application, the baffle covers the axial roller for limiting the distance between its travel and extreme positions to both sides.

[0027] Preferably, in an embodiment of the present application, the axial roller is a spherical roller, which maintains contact when the rotating ring is axially tilted; the supporting rollers adopt spherical rollers, which can ensure good contact when the rotating ring is axially tilted.

[0028] Preferably, in an embodiment of the present application, the baffle is mounted on the rotating ring through a thread sealing assembly.

[0029] Preferably, in an embodiment of the present application, the thread sealing assembly comprises a bolt and a tooth pad.

[0030] Preferably, in an embodiment of the present application, a first gasket is arranged between the baffle and the rotating ring, and different thicknesses of the first gasket correspond to adjustment of the gap S2 between the baffle and the axial roller, and correspond to adjustment of the gap S between the axial roller and the rotating ring.

[0031] Preferably, in an embodiment of the present application, the first gasket is provided with a matching second gasket.

[0032] Preferably, in an embodiment of the present application, the second gasket is a combination of at least two gaskets; the combined gasket form facilitates formation of different thickness combinations through combination of multiple gaskets to meet the gap adjustment requirements. This is because if a single thickness is stacked, excessive use of gaskets will also cause stacking errors, while the adoption of gasket combinations with different thicknesses also reduces the number of gaskets used and relatively reduces use errors.

[0033] Preferably, in an embodiment of the present application, S1 is the gap between the side surface of the radial roller and one side of the ring groove of the rotating ring, S is the gap between the axial roller and the side surface of the rotating ring, and S2 is the gap between the axial roller and the baffle; adjust the rotating ring to lean toward the axial roller, so that the gap S=0 or S reaches an extreme value, and measure to obtain the minimum extreme value S1min of S1, wherein S1min and S2 satisfy S2 < S1min - (allowable axial displacement of the rotating ring + deformation amount of the baffle under force);

[0034] A radial roller refers to that the axis of the roller is perpendicular to the axis of the stationary blade arrangement, and radiates outward away from the axis of the stationary blade arrangement.

[0035] Preferably, in an embodiment of the present application, by adjusting the baffle, S1min and S2 satisfy S2 < S1min - (allowable axial displacement of the rotating ring + deformation amount of the baffle under load).

[0036] Preferably, in an embodiment of the present application, the sum of the allowable axial displacement of the rotating ring and the deformation amount of the baffle under load is 0.5 mm.

[0037] Preferably, in an embodiment of the present application, stress relief grooves are provided at the inner diameter and / or outer diameter of the rotating ring, and the stress relief grooves are used to relieve stress caused by thermal expansion; the structure with a plurality of stress relief grooves added at the inner diameter and / or outer diameter of the rotating ring can effectively alleviate the influence of stress caused by thermal expansion; in this solution, the stress relief grooves can be machined separately at the inner diameter and the outer diameter, or can be machined in combination, and stress relief grooves of different structural forms can be used alone or in combination.

[0038] Preferably, in an embodiment of the present application, the stress relief grooves are arranged in a uniform annular array.

[0039] Preferably, in an embodiment of the present application, the total depth L of the stress relief grooves is not greater than 1 / 3 of the total radial thickness of the rotating ring, and the total depth L is the distance between the extreme point at the innermost end of the groove and the boundary at the opening of the groove.

[0040] Preferably, in an embodiment of the present application, the shape of the stress relief groove is an intersection of a combination of a circle and a rectangle, or an intersection of a combination of a circle and an isosceles trapezoid, wherein the circle is deep inside, and the rectangle or the isosceles trapezoid is provided on the shallow surface.

[0041] To obtain a variable stator vane rotating device for a gas turbine, a design method of a variable stator vane rotating device for a gas turbine is provided, wherein the rotating ring is connected with dual drives, and the dual drives balance the stress on the rotating ring; axial rollers of the rotating ring are limited by double rails; the gap between the rail on a side away from the rotating ring and the rotating ring is realized by a combination gasket; and stress relief grooves are provided at the inner diameter and / or outer diameter of the rotating ring.

[0042] The beneficial effects of the present application are:

[0043] 1. In the present application, a dual-drive device is adopted to replace the traditional single-drive device design as the driving device of the rotating mechanism, and an elastic compensation device is added at the auxiliary driving device for synchronous compensation, which can also effectively balance the position of the rotating ring, reduce the risk of jamming, and provide a greater driving force to overcome the influence of jamming in the case of slight jamming.

[0044] 2. In the present application, by machining a plurality of stress relief grooves at the inner and outer diameters of the rotating ring, the influence of thermal expansion during unit operation is reduced, the stress borne by the rotating ring is reduced, thereby reducing the friction resistance of the mechanism and lowering the risk of jamming.

[0045] 3. This application changes the axial roller track from a single track to a double track by installing a baffle structure on the rotating ring. During unit operation, only one track is effective, thereby changing the axial unilateral displacement restriction of the rotating ring to a bidirectional restriction. This reduces the risk of jamming caused by axial contact friction without affecting the original function.

[0046] 4. This application combines various technical means to achieve the corresponding technical effects 1-3, reducing the impact of thermal expansion, minimizing the risk of jamming, and increasing the safety and stability of unit operation. Simultaneously, it can reduce the stress impact of thermal expansion, reduce the resistance impact of axial force, minimize the risk of jamming, and even in the event of jamming, overcome resistance with a large driving force margin, thus increasing the safety and stability of unit operation. Furthermore, different improvement combinations can be selected according to specific working conditions, such as any two or all combinations of dual-drive, stress relief groove, and dual-track schemes, which can optimize mechanism performance and achieve technical design improvements at minimal cost.

[0047] In summary, the technical solution of this application is an improvement on the traditional rotating mechanism, and the overall structure of the rotating ring remains largely unchanged. Therefore, this structure can be used in workshop processing and production, as well as for retrofitting in-service units with minimal modifications. Using this rotating ring structure for retrofitting in-service units can reduce the risk of potential hazards and lower the cost of troubleshooting, resulting in certain economic benefits. Attached Figure Description

[0048] Figure 1 This is a schematic diagram of a dual-drive structure for an adjustable stationary vane rotation device for a gas turbine according to the present invention;

[0049] Figure 2 This is a schematic diagram of the stress relief groove at point C of an adjustable stationary blade rotation device for a gas turbine according to the present invention;

[0050] Figure 3 This is a schematic diagram of the stress relief groove at point C of an adjustable stationary blade rotation device for a gas turbine according to the present invention;

[0051] Figure 4 This is a schematic diagram of the stress relief groove at point C of an adjustable stationary blade rotation device for a gas turbine according to the present invention;

[0052] Figure 5 This is a schematic diagram of the structure of an adjustable stationary blade rotating device for a gas turbine with a baffle added to the rotating ring according to the present invention;

[0053] Figure 6 for Figure 5 AA section view;

[0054] Figure 7 This is a schematic diagram of the forces acting on the rotating ring;

[0055] Figure 8 This is a schematic diagram of the structure of a conventional gas turbine adjustable stator vane rotation device.

[0056] Figure 9 This is a schematic diagram of a traditional adjustable stationary vane rotation mechanism.

[0057] Figure 10 A schematic diagram of the rotating ring structure of a traditional adjustable stationary vane rotating mechanism;

[0058] Figure 11 for Figure 10 Schematic diagram of the BB cross-section structure;

[0059] Figure 12 This is a schematic diagram of the clearances S1, S, and S2 of an adjustable stator blade rotation device for a gas turbine according to the present invention;

[0060] Figure 13 This is a perspective view of an adjustable stationary blade rotation device for a gas turbine according to the present invention, without the stress relief groove.

[0061] Figure 14 This is a perspective view of an adjustable stationary blade rotation device for a gas turbine according to the present invention, without the stress relief groove.

[0062] Figure 15 This is a three-dimensional structural diagram of the axial roller support of an adjustable stationary vane rotation device for a gas turbine according to the present invention;

[0063] Figure 16 This is a three-dimensional structural diagram of the radial roller support of an adjustable stationary vane rotation device for a gas turbine according to the present invention;

[0064] Figure 17 for Figure 13 Color illustrations;

[0065] Figure 18 for Figure 14 Color illustrations;

[0066] In the picture:

[0067] 100. Rocker arm assembly

[0068] 101. Rocker arm

[0069] 102. Connecting rod

[0070] 200, outer cylinder

[0071] 300, copper sleeve

[0072] 400. Adjustable still leaf

[0073] 500, bushing

[0074] 600, Inner Ring Road

[0075] 700, Rotating Ring

[0076] 800, Axial Roller Support

[0077] 801. Axial roller

[0078] 802, Axial Roller Support

[0079] 900, Radial roller support

[0080] 901. Radial roller

[0081] 902. Radial roller bracket

[0082] 110. Stress relief groove

[0083] 201. Outer wall surface of the outer cylinder

[0084] 120. Elastic compensation device

[0085] 130. Main drive unit

[0086] 140. Secondary drive unit

[0087] 150. Baffle

[0088] 180. Threaded sealing assembly

[0089] 190. Gasket I

[0090] 210. Gasket II

[0091] 220. Drive lever

[0092] C represents the schematic location of the stress relief groove. Detailed Implementation

[0093] The specific embodiments of this application will be further described in detail below with reference to the accompanying drawings. These embodiments are only for illustrating this application and are not intended to limit the scope of the invention.

[0094] In the description of this invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0095] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0096] Furthermore, in the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0097] like Figure 1 , 5 6, 13, 14, 17, 18, A gas turbine adjustable stationary blade rotation device, including a rotating ring 700 and a rocker arm assembly 100. The rocker arm assembly 100 includes a rocker arm 101 and a connecting rod 102. The rotating ring 700 is connected to the adjustable stationary blade 400 through the rocker arm assembly 100. The rotating ring 700 is connected to two drive rods 220, and each drive rod 220 is connected to a drive device.

[0098] Two drive rods 220 are arranged on both sides of the rotating ring 700, and the drive device connected to one drive rod 220 is the main drive device 130, while the drive device connected to the other drive rod 220 is the auxiliary drive device 140. An elastic compensation device 120 is provided on the drive rod 220 connected to the auxiliary drive device 140 or the main drive device 130. The elastic compensation device 120 is used for synchronous compensation so that the movement trend of the auxiliary drive device 140 and the main drive device 130 driving the rotating ring 700 is consistent and the rhythm is synchronized.

[0099] The drive unit drives the rotating ring 700 to rotate via the drive rod 220. The two drive units make the drive rod 220 push and pull respectively, but there is a response time problem. This compensation is to compensate for this response time difference and ensure synchronous drive.

[0100] While a single drive unit is sufficient to drive the rotating ring to rotate 700 degrees, there is a risk that the rotating ring may become unbalanced due to force imbalance, and there is a lack of safety measures. Moreover, if the drive unit fails, the loss will be very large. The dual drive unit is designed to increase the output when necessary, to avoid damage to a single drive unit, and to reduce the possibility of the rotating ring becoming unbalanced by having drive units on both sides.

[0101] like Figure 1 As shown, a secondary drive device is added to the traditional rotating mechanism driven only by the main drive device, and an elastic compensation device is added to the drive rod between the secondary drive device and the rotating ring for synchronous compensation, so as to ensure that the two drive devices output power synchronously.

[0102] like Figure 8-11 Traditional rotating mechanisms use a single drive unit to drive the drive rod 220, and the drive rod 220 pushes and pulls the rotating ring to adjust the adjustable blades; this application provides a structure driven by a dual drive unit, such as... Figure 1 This structure can provide greater driving force to overcome jamming when the rotating mechanism is stuck. Furthermore, it uses an elastic compensation device, such as a disc spring, on the auxiliary drive side for synchronous compensation, ensuring synchronized output from both drive units. The dual drive system also balances the position of the rotating ring, preventing axial tilting and center eccentricity caused by positional imbalance during single-drive operation, which would otherwise contribute to jamming.

[0103] Specifically, in one embodiment of this application, the driving device drives the rotating ring 700 to move in the same direction as the driving rod 220, that is, the rotating ring 700 moves in the same direction.

[0104] Specifically, in one embodiment of this application, the direction of movement of the rotating ring 700 is the rotation direction of the rotating ring 700.

[0105] Specifically, in one embodiment of this application, such as Figure 5 and Figure 6 , Figure 15 One side of the axial roller 801 abuts against the rotating ring 700 to form track I, and track II is provided on the other side of the axial roller 801; during unit operation, at least one track of the axial roller 801 is effectively abutted.

[0106] Specifically, in one embodiment of this application, such as Figure 5 and Figure 6 , Figure 15 Track II is fixed to the rotating ring 700.

[0107] Specifically, in one embodiment of this application, such as Figure 5 and Figure 6 , Figure 15A baffle 150 is added to the rotating ring 700. The baffle 150 limits the axial roller 801 to form track II, thereby restricting the displacement on both sides of the rotating ring 700 in the axial direction.

[0108] like Figure 5 and Figure 6 , Figure 15 By drilling holes in the rotating ring 700, the baffle 150 is fixedly installed on the rotating ring 700 by the bolts and toothed pads of the bolt sealing assembly 180. The baffle 150 covers the axial roller 801 and controls its stroke and the distance from the extreme positions to both sides.

[0109] Specifically, in one embodiment of this application, such as Figure 5 and Figure 6 , Figure 15 The baffle 150 covers the axial roller 801 and is used to limit its travel and the distance between its extreme position and both sides; so that the axial roller support on one side changes from a single track to a double track, and when the roller is subjected to axial force in different directions, only a single track is in contact and plays a supporting role, thereby limiting the axial displacement of the rotating ring, avoiding jamming when the rotating ring rotates, and ensuring the safe operation of the unit.

[0110] Specifically, in one embodiment of this application, the axial roller 801 is a spherical roller, so that the axial roller 801 remains in contact when the rotating ring 700 is axially tilted.

[0111] Specifically, in one embodiment of this application, the baffle 150 is mounted on the rotating ring 700 via a threaded sealing assembly 180.

[0112] Specifically, in one embodiment of this application, the threaded sealing assembly 180 includes a bolt and a toothed washer.

[0113] Specifically, in one embodiment of this application, a shim I 190 is provided between the baffle 150 and the rotating ring 700. The different thicknesses of the shim I 190 correspond to adjusting the gap S2 between the baffle 150 and the axial roller 801, and correspondingly adjusting the gap S between the axial roller 801 and the rotating ring 700.

[0114] By adjusting the thickness of the shim I190 and the gaps between the baffle 150 and the roller, and between the roller and the rotating ring, it is ensured that when the rotating ring is subjected to axial force, only a single track is effective regardless of the direction.

[0115] Specifically, in one embodiment of this application, shim I 190 is provided with shim II 210. To ensure sufficient operating space during adjustment, shim II 210 is added and inserted if necessary to compensate for the gap value. At least three axial roller supports 800 are required. The baffle structure is installed on the three axial roller supports 800 with baffles and shim structures to ensure functional stability.

[0116] Specifically, in one embodiment of the present application, the gasket II 210 is a combination of at least two gaskets. The combination of two or more gaskets for the gasket II 210 facilitates matching to select the required thickness for use after stacking, that is, the total thickness of the gaskets is the effective thickness.

[0117] Specifically, in one embodiment of the present application, the sum of the allowable axial displacement of the rotating ring and the deformation under force of the baffle is set to 0.5 mm.

[0118] Specifically, in one embodiment of the present application, as shown in Figure 16 which is a structural schematic diagram of the radial roller support 900, as shown in Figure 12 , S1 is the gap between the side surface of the radial roller 901 and one side of the ring groove of the rotating ring 700, S is the gap between the axial roller 801 and the side surface of the rotating ring 700, and S2 is the gap between the axial roller 801 and the baffle 150; adjust the rotating ring 700 to move toward the axial roller 801 so that the gap S is 0 or reaches an extreme value, measure and obtain the minimum limit value S1min of S1, and S1min and S2 satisfy the relation: S2 < S1min - (allowable axial displacement of the rotating ring + deformation under force of the baffle);

[0119] adjust the required gaps, and according to the deformation between the baffles and the elongation of the bolts, and based on the relationship among the gaps S1, S and S2, ensure that the deformation caused by the maximum axial force and the elongation of the bolts can still meet the requirements during the operation of the unit, that is, only a single raceway is effective and there is no axial contact between the radial support roller and the rotating ring, which reduces the risk of jamming when the rotating ring rotates and ensures the safe operation of the unit.

[0120] Specifically, in one embodiment of the present application, by adjusting the baffle 150, S1min and S2 are enabled to satisfy the relation S2 < S1min - (allowable axial displacement of the rotating ring + deformation under force of the baffle).

[0121] Specifically, in one embodiment of the present application, as shown in Figure 1-4 , a stress relief groove 110 is provided at the inner diameter and / or outer diameter of the rotating ring 700, and the stress relief groove 110 is configured to eliminate the stress caused by thermal expansion; the stress relief groove 110 is provided at the inner and outer diameters of the rotating ring 700, and the structural form is as shown in Figure 2-4 ;

[0122] a plurality of stress relief grooves can be machined at appropriate positions on the inner diameter and / or outer diameter of the rotating ring, as shown at position C in Figure 1 to minimize the influence caused by factors such as thermal expansion; the total depth L of the stress relief grooves is not greater than 1 / 3 of the total radial thickness of the rotating ring; the stress relief grooves can be used separately on the inner diameter or the outer diameter, or can be used simultaneously; the three stress relief groove schemes can be used alone or in combination according to actual conditions.

[0123] Specifically, in one embodiment of this application, the stress relief grooves 110 are arranged in a uniform annular array.

[0124] Specifically, in one embodiment of this application, such as Figure 2-4 The total depth L of the stress relief groove 110 is not greater than 1 / 3 of the radial total thickness of the rotating ring 700. The total depth L is the distance between the innermost limit point of the groove and the boundary of the groove opening.

[0125] Specifically, in one embodiment of this application, such as Figure 2-4 The stress relief groove 110 is a combination of circular and rectangular shapes, or a combination of circular and isosceles trapezoidal shapes, wherein the circular shape extends into the interior, and the rectangular or isosceles trapezoidal shape is set on the surface of the shallow layer.

[0126] To realize an adjustable stationary blade rotation device for a gas turbine, a design method for an adjustable stationary blade rotation device for a gas turbine is provided. The rotating ring 700 is connected to a dual drive, and the dual drive balances the force on the rotating ring 700. The axial roller 801 of the rotating ring 700 is a double track limiter. The gap between the track away from the rotating ring 700 and the rotating ring 700 is achieved by a combination of shims. Stress relief grooves 110 are provided at the inner diameter and / or outer diameter of the rotating ring 700.

[0127] In general, such as Figure 1-7 The present invention aims to solve the problems of jamming of the rotating ring, stress concentration due to thermal expansion of the rotating ring, and insufficient movement limit of the rotating ring;

[0128] This invention increases the driving force of the drive rod 220, giving the rotating ring greater margin to overcome resistance in situations where jamming is possible, thus ensuring the normal and stable operation of the unit. It is applicable to various environmental conditions.

[0129] Furthermore, based on the above, by adding a baffle 150 to limit the axial roller 801, the resistance caused by the axial force when the rotating ring rotates is reduced, and the risk of jamming is reduced. When the angle between the connecting rod 102 and the rotating ring 700 is large, that is, when the axial force is large, the above defects can be effectively overcome.

[0130] Furthermore, based on the above, a thermal stress relief groove is added to the rotating ring to effectively alleviate the stress caused by thermal expansion. When used in environments with large temperature differences, it can significantly alleviate stress problems.

[0131] Combined applications are made according to the conditions under which the rotating mechanism is used.

[0132] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present invention, and these improvements and substitutions should also be considered within the scope of protection of the present invention.

Claims

1. A gas turbine adjustable stator blade rotation device, comprising a rotating ring (700) and a rocker arm assembly (100), the rocker arm assembly (100) comprising a rocker arm (101) and a connecting rod (102), the rotating ring (700) being connected to the adjustable stator blade (400) via the rocker arm assembly (100), characterized in that, The rotating ring (700) is connected to two driving rods (220), and each driving rod (220) is connected with a driving device; The two driving rods (220) are arranged on both sides of the rotating ring (700), the driving device connected to the driving rod (220) on one side is a main driving device (130), and the driving device connected to the driving rod (220) on the other side is an auxiliary driving device (140); an elastic compensation device (120) is arranged on the driving rod (220) connected to the auxiliary driving device (140) or the main driving device (130), the elastic compensation device (120) is used for synchronous compensation, so that the movement trends of the rotating ring (700) driven by the auxiliary driving device (140) and the main driving device (130) are consistent and the beats are synchronized; One side of the axial roller (801) abuts against the rotating ring (700) to form a track I, and the other side of the axial roller (801) is provided with a track II; during the operation of the unit, at least one track of the axial roller (801) is effectively abutted; A baffle (150) is additionally arranged on the rotating ring (700), the baffle (150) limits the axial roller (801) to form the track II, so that displacement limitation is formed on both axial sides of the rotating ring (700); A first gasket (190) is arranged between the baffle (150) and the rotating ring (700), different thicknesses of the first gasket (190) correspondingly adjust the clearance S2 between the baffle (150) and the axial roller (801), and correspondingly adjust the clearance S between the axial roller (801) and the rotating ring (700); S1 is the clearance between the side surface of the radial roller (901) and one side of the ring groove of the rotating ring (700); adjusting the rotating ring (700) to lean against the axial roller (801), so that the clearance S is 0 or S is an extreme value, measuring to obtain the extreme minimum value S1min of S1, and adjusting the baffle (150) to make S1min and S2 satisfy S2 < S1min - Δ, where Δ is the sum of the allowable axial displacement of the rotating ring and the deformation amount of the baffle under load.

2. The adjustable stationary blade rotation device for a gas turbine as described in claim 1, characterized in that, The consistent movement trend of the rotating ring (700) driven by the driving devices means that the movement direction of the rotating ring (700) is consistent; the movement direction of the rotating ring (700) is the rotation direction of the rotating ring (700).

3. The adjustable stationary blade rotation device for a gas turbine as described in claim 1, characterized in that, The track II is connected and fixed on the rotating ring (700).

4. The adjustable stationary blade rotation device for a gas turbine as described in claim 1, characterized in that, The baffle (150) covers the axial roller (801) and is used for limiting the distances from its stroke and extreme position to both sides; the axial roller (801) is a spherical roller, so that contact is maintained when the rotating ring (700) tilts axially.

5. The adjustable stator vane rotation device for a gas turbine as described in claim 1, characterized in that, The baffle (150) is mounted on the rotating ring (700) through a thread seal assembly (180); the thread seal assembly (180) comprises a bolt and a toothed pad.

6. The adjustable stator vane rotation device for a gas turbine as described in claim 1, characterized in that, The first gasket (190) is provided with a second gasket (210) in a matching manner; the second gasket (210) is a combination of at least two gaskets.

7. The adjustable stationary blade rotation device for a gas turbine as described in claim 1, characterized in that, A stress relief groove (110) is arranged at the inner diameter and / or outer diameter of the rotating ring (700), and the stress relief groove (110) is used for eliminating stress caused by thermal expansion.

8. The adjustable stationary blade rotation device for a gas turbine as described in claim 7, characterized in that, The stress relief grooves (110) are arranged in a uniform ring array; the total depth L of the stress relief grooves (110) is not greater than 1 / 3 of the radial total thickness of the rotating ring (700), and the total depth L is the distance between the innermost limit point of the groove and the boundary of the groove opening.

9. The adjustable stationary blade rotation device for a gas turbine as described in claim 7, characterized in that, The stress relief groove (110) is a combination of circular and rectangular shapes, or a combination of circular and isosceles trapezoidal shapes, wherein the circular shape extends into the interior and the rectangular or isosceles trapezoidal shape is set on the surface of the shallow layer.

10. A design method for an adjustable stator blade rotation device for a gas turbine, characterized in that, The device includes an adjustable stator blade rotating device for a gas turbine as described in any one of claims 1-7, wherein the rotating ring (700) is connected to a dual drive, and the dual drive balances the force on the rotating ring (700); the axial roller (801) of the rotating ring (700) is a double track limiter; the gap between the track away from the rotating ring (700) and the rotating ring (700) is achieved by a combination shim; and stress relief grooves (110) are provided at the inner diameter and / or outer diameter of the rotating ring (700).

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