Variable geometry turbine adjusting system with thermal state self-centering support and variable geometry turbine

Abstract

The invention provides a variable geometry turbine adjusting system with a thermal state self-centering supporting function and a variable geometry turbine, and relates to the technical field of aero-engines and gas turbines.The variable geometry turbine adjusting system comprises a supporting ring, a linkage ring and a plurality of maintaining structures; the supporting ring is coaxially arranged on the outer side of a static casing of the turbine. The linkage ring is rotatably arranged on the outer side of the supporting ring in a sleeving mode and suitable for being connected with and driving the multiple adjustable blades distributed in the circumferential direction of the turbine to synchronously rotate around the blade rotating shaft. The multiple maintaining structures are evenly distributed in the circumferential direction of the turbine at intervals and connected and supported between the supporting ring and the static casing correspondingly, and the maintaining structures are suitable for maintaining the supporting ring and the static casing to be coaxial under the condition that the static casing is subjected to thermal expansion deformation.

Description

Technical Field

[0001] At least one embodiment of this disclosure relates to the field of aero-engine and gas turbine technology, and more specifically, to a variable geometry turbine adjustment system and a variable geometry turbine with thermal self-centering support. Background Technology

[0002] Variable geometry turbines are a core technology for aero engines and gas turbines, and adjusting the turbine guide vane installation angle is the mainstream method for achieving this. The industry uses a linkage ring to connect each adjustable blade, and an actuator drives the linkage ring to rotate, causing the blades to adjust their angles synchronously. Maintaining concentricity between the linkage ring and the engine centerline is a crucial prerequisite for ensuring consistent blade angle adjustment.

[0003] Traditional designs achieve linkage ring centering by adjusting the screws in conjunction with the support casing. This approach suffers from a large temperature difference between the linkage ring and the support casing during turbine operation. To prevent interference and damage to components under hot conditions, a clearance must be reserved during assembly. This significantly reduces the centering accuracy of the linkage ring under complex aero-thermal conditions, making it difficult to ensure consistent blade angle adjustment and potentially leading to localized overload failure of the adjustment mechanism components. Furthermore, the appropriate clearance value depends on a precise assessment of the thermal expansion of the support casing. The complex three-dimensional flow, thermal resistance, and tolerance issues within the engine greatly increase the difficulty of assessment, further reducing the design and operational reliability of traditional structures.

[0004] Therefore, there is an urgent need for a variable geometry turbine adjustment system that can eliminate the reliance on the assessment of the thermal expansion of the support casing and achieve stable centering and support of the linkage ring under cold, hot and various complex working conditions. Summary of the Invention

[0005] In view of this, the present disclosure provides a variable geometry turbine adjustment system and a variable geometry turbine with thermal self-centering support. By setting a support ring and multiple retaining structures between the linkage ring and the stationary casing of the turbine, the linkage ring and the stationary casing are kept coaxial under thermal expansion and deformation.

[0006] One embodiment of this disclosure provides a variable geometry turbine adjustment system with thermal self-centering support, including a support ring coaxially disposed on the outside of the turbine's stationary casing; a linkage ring rotatably sleeved on the outside of the support ring, suitable for connecting and driving multiple adjustable blades distributed along the turbine circumference to rotate synchronously around the blade axis; and multiple retaining structures evenly spaced along the turbine circumference and respectively connected and supported between the support ring and the stationary casing, suitable for maintaining the support ring and the stationary casing coaxially under the condition of thermal expansion and deformation of the stationary casing.

[0007] According to an embodiment of this disclosure, the aforementioned retaining structure includes: a casing support disposed on the stationary casing; a support ring support disposed on the support ring; and a support rod, with both ends hinged to the casing support and the support ring support respectively, and the hinge axis being parallel to the turbine axis.

[0008] According to embodiments of this disclosure, the aforementioned retaining structure further includes a plurality of heat insulation units 36, which are respectively disposed at the hinge points of the support rod and the casing support and the support ring support, and are suitable for isolating heat transferred from the aforementioned stationary casing.

[0009] According to embodiments of this disclosure, the axes of the support rods of the plurality of aforementioned retaining structures are at an angle equal to the radial direction of the turbine, wherein the angle is 60° to 75°.

[0010] According to embodiments of this disclosure, the outer surface of the support ring is configured as a continuous support surface that slides with the inner surface of the linkage ring; or the outer surface of the support ring is provided with a plurality of bosses spaced apart along the circumferential direction of the turbine, and the plurality of bosses slide on the inner surface of the linkage ring.

[0011] According to an embodiment of this disclosure, at least one drive unit is further included, disposed on the outside of the stationary casing, and the output end of the drive unit is connected to the linkage ring, which is adapted to drive the linkage ring to rotate circumferentially around the center line of the turbine.

[0012] According to embodiments of this disclosure, a plurality of blade rocker arms are also included, which are respectively connected between the aforementioned linkage ring and the corresponding plurality of adjustable blades, and are suitable for converting the circumferential motion of the aforementioned linkage ring into the rotational motion of the plurality of the aforementioned adjustable blades.

[0013] According to an embodiment of this disclosure, the first end of the blade rocker arm is fixedly connected to the rotation shaft of the adjustable blade end, and the second end is movably connected to the linkage ring via a ball joint connection structure.

[0014] According to an embodiment of this disclosure, the ball joint connection structure is disposed in a mounting groove that passes through the linkage ring along the turbine axis, and includes: a pin shaft that passes through the mounting groove along the turbine radial direction; a spherical bearing that is slidably sleeved on the pin shaft; and a bearing housing formed at the second end of the blade rocker arm, wherein the bearing housing is provided with a spherical socket that mates with the outer spherical surface of the spherical bearing; the blade rocker arm can freely swing relative to the linkage ring by means of the radial sliding of the spherical bearing along the pin shaft and the mating of the spherical socket with the outer spherical surface.

[0015] Another aspect of this disclosure provides a variable geometry turbine, including the variable geometry turbine adjustment system described above.

[0016] According to the embodiments of this disclosure, by coaxially setting a support ring on the outside of the stationary casing of the turbine and using a circumferentially distributed retaining structure to connect and support the support ring and the stationary casing, the two can always remain coaxial when the stationary casing undergoes thermal expansion and deformation. This ensures the centering accuracy of the linkage ring sleeved on the outside of the support ring, providing a stable structural foundation for the linkage ring to drive multiple adjustable blades to rotate synchronously around its own axis. This effectively ensures the consistency of the adjustable blade angle adjustment and significantly improves the operational stability and adjustment reliability of the variable geometry turbine adjustment system under various operating conditions. Attached Figure Description

[0017] The above and other objects, features and advantages of this disclosure will become clearer from the following description of embodiments with reference to the accompanying drawings, in which:

[0018] Figure 1 A perspective view of a variable geometry turbine adjustment system according to an embodiment of the present disclosure is shown;

[0019] Figure 2 A front view of a variable geometry turbine control system according to an embodiment of the present disclosure is shown;

[0020] Figure 3 A perspective view of the retaining structure according to an embodiment of the present disclosure is shown;

[0021] Figure 4 A schematic diagram of the stationary casing in cold and hot states according to an embodiment of the present disclosure is shown;

[0022] Figure 5 A schematic diagram of the structure of the driving unit according to an embodiment of the present disclosure is shown;

[0023] Figure 6 A perspective view of the blade rocker arm according to an embodiment of the present disclosure is shown.

[0024] In the accompanying drawings, the meanings of the reference numerals are as follows:

[0025] 1. Support ring; 11. Boss; 2. Linkage ring; 21. Mounting groove; 22. Pin; 23. Spherical bearing; 24. Support seat; 3. Retaining structure; 31. Casing support; 32. Support ring support; 33. Support rod; 34. Bolt; 35. Self-locking nut; 36. Heat insulation unit; 4. Stationary casing; 5. Blade rocker arm; 51. Bearing seat; 6. Adjustable blade; 61. Rotating shaft; 7. Drive unit; 71. Drive mounting seat. Detailed Implementation

[0026] The embodiments of the present disclosure will now be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the disclosure. In the following detailed description, numerous specific details are set forth to provide a thorough understanding of the embodiments of the present disclosure for ease of explanation. However, it will be apparent that one or more embodiments may be practiced without these specific details. Furthermore, descriptions of well-known structures and techniques are omitted in the following description to avoid unnecessarily obscuring the concepts of the present disclosure.

[0027] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. The terms “comprising,” “including,” etc., as used herein, indicate the presence of said features, steps, operations, and / or mechanisms, but do not exclude the presence or addition of one or more other features, steps, operations, or mechanisms. All terms used herein (including technical and scientific terms) have the meanings commonly understood by those skilled in the art, unless otherwise defined. It should be noted that the terms used herein are to be interpreted in a manner consistent with the context of this specification and should not be interpreted in an idealized or overly rigid manner.

[0028] When using expressions such as "at least one of A, B and C", they should generally be interpreted in accordance with the meaning that is commonly understood by those skilled in the art (e.g., "a system having at least one of A, B and C" should include, but is not limited to, a system having A alone, a system having B alone, a system having C alone, a system having A and B, a system having A and C, a system having B and C, and / or a system having A, B and C, etc.).

[0029] Those skilled in the art will understand that the features described in the various embodiments of this disclosure can be combined and / or combined in various ways, even if such combinations or combinations are not explicitly described in this disclosure. In particular, the features described in the various embodiments of this disclosure can be combined and / or combined in various ways without departing from the spirit and teachings of this disclosure. All such combinations and / or combinations fall within the scope of this disclosure.

[0030] Figure 1 A perspective view of a variable geometry turbine adjustment system according to an embodiment of the present disclosure is shown; Figure 2 A front view of a variable geometry turbine adjustment system according to an embodiment of the present disclosure is shown.

[0031] Embodiments of this disclosure provide a variable geometry turbine adjustment system with hot self-centering support, adapted to the variable geometry turbine blade angle adjustment conditions of aero-engines and gas turbines, with reference to... Figures 1 to 2As shown, it includes a support ring 1, a linkage ring 2, and multiple retaining structures 3. The support ring 1 is coaxially disposed on the outside of the stationary casing 4 of the turbine; the linkage ring 2 is rotatably sleeved on the outside of the support ring 1, and is suitable for connecting and driving multiple adjustable blades 6 distributed along the circumference of the turbine to rotate synchronously around the blade axis; the multiple retaining structures 3 are evenly spaced along the circumference of the turbine, and are respectively connected and supported between the support ring 1 and the stationary casing 4, and are suitable for keeping the support ring 1 and the stationary casing 4 coaxial in the event of thermal expansion and deformation of the stationary casing 4.

[0032] Specifically, the support ring 1 serves as the basic support structure for the linkage ring 2, providing a centering reference for the rotation of the linkage ring 2. The linkage ring 2 is rotatably fitted onto the outside of the support ring 1 and connected to multiple adjustable blades 6 distributed along the turbine circumference. It can rotate around the turbine centerline under power drive and drive each adjustable blade 6 to rotate synchronously around its own blade axis, thereby adjusting the turbine guide vane installation angle. Multiple retaining structures 3 are evenly spaced along the turbine circumference and are connected and supported at both ends between the support ring 1 and the stationary casing 4, providing stable radial support for the support ring 1.

[0033] Furthermore, the support structure 3 is configured to adapt to the thermal expansion and deformation characteristics of the stationary casing 4. When the stationary casing 4 undergoes thermal expansion and radial displacement due to turbine operation, it can adaptively deform its own structure to maintain the coaxial state of the support ring 1 and the stationary casing 4. This provides a continuous and accurate centering reference for the linkage ring 2, ensuring the consistency of the adjustment angle of each adjustable blade 6. This fundamentally solves the problems of thermal interference and low centering accuracy of traditional support structures.

[0034] In some embodiments, the support ring 1 and the linkage ring 2 are both arranged in the same airflow temperature environment outside the turbine, and the support ring 1 and the linkage ring 2 are made of the same material or high-temperature resistant alloy material with similar coefficients of thermal expansion.

[0035] According to the above configuration, the thermal expansion of the support ring 1 and the linkage ring 2 during the turbine's cold, hot and variable operating conditions can be kept similar, effectively avoiding structural interference or excessive clearance at the sliding fit due to the difference in thermal expansion. This further ensures the stability and centering accuracy of the sliding support of the support ring 1 to the linkage ring 2, while also meeting the material requirements for the turbine under long-term high-temperature conditions.

[0036] Figure 3 A perspective view of the retaining structure according to an embodiment of the present disclosure is shown.

[0037] In one illustrative embodiment, reference is made to... Figure 3As shown, the retaining structure 3 includes a casing support 31, a support ring support 32, and a support rod 33. The casing support 31 is disposed on the stationary casing 4; the support ring support 32 is disposed on the support ring 1; the two ends of the support rod 33 are respectively hinged to the casing support 31 and the support ring support 32, and the hinge axis is parallel to the turbine axis.

[0038] Figure 4 A schematic diagram of the stationary casing in cold and hot states according to an embodiment of the present disclosure is shown.

[0039] Reference Figure 4 As shown, the solid line represents the cold state before the turbine starts, and the dashed line represents the hot state after the turbine starts. When a gas turbine or aero-engine is running hot, the temperature of the stationary casing 4 is typically much higher than the temperature of the support ring 1. Due to the high temperature, the stationary casing 4 undergoes thermal expansion, which in turn causes radial displacement of the casing support 31. Thanks to the hinged connection between the support rod 33 and the casing support 31 and support ring support 32, and the fact that multiple support rods 33 are evenly distributed along the turbine circumference, during the radial displacement of the casing support 31 driven by the thermal expansion of the stationary casing 4, the radial distance between the stationary casing 4 and the support ring 1 decreases. The support rod 33 rotates around the hinge axis, which in turn causes the support ring 1 to rotate slightly at an angle (i.e.,...). Figure 4 The deformation adaptive force achieved by the slight rotation of θ2 in the figure can not only avoid the thermal deformation force of the stationary casing 4 being directly transmitted to the support ring 1, but also keep the radial position of the support ring 1 from shifting, ensuring that the support ring 1 and the stationary casing 4 remain coaxial in cold, hot and working condition switching processes.

[0040] In some embodiments, the number of retaining structures 3 is three, the casing supports 31 are evenly distributed in a circle along the circumference of the stationary casing 4, and the support ring supports 32 are arranged in a one-to-one correspondence with the casing supports 31 and are evenly distributed in a circle along the circumference of the support ring 1.

[0041] In some embodiments, the housing support 31 and the support ring support 32 are provided with mating holes to provide a positioning reference for the fitting assembly of the hinge structure; both ends of the support rod 33 are provided with insertion structures, and the insertion structures are provided with corresponding mating holes. The insertion structures can be fitted and connected with the mating positions of the housing support 31 and the support ring support 32 to realize the pre-positioning of the support rod 33 with each support, which helps to improve the coaxiality of the hinge assembly.

[0042] Specifically, refer to Figure 3As shown, the hinged connection between the support rod 33 and the casing support 31 and the support ring support 32 is achieved by bolts 34 with adaptable screw sections passing through the mating holes of each component. The bolts 34 pass through the mating holes on the casing support 31, the support rod 33 insertion structure, and the support ring support 32 in sequence. The adaptable screw sections of the bolts 34 can be adapted to fit with each mating hole, which helps to ensure the coaxiality of the multiple components. Furthermore, a self-locking nut 35 is screwed on the other side of the bolt 34 away from the screwing end. Tightening the self-locking nut 35 completes the fastening assembly of the hinged structure. The self-locking nut 35 can reduce the loosening of the bolts 34 caused by vibration during turbine operation, which helps to ensure the connection stability of the hinged structure. Finally, the three support rods 33 form a triangular hinged support structure between the stationary casing 4 and the support ring 1, which helps to ensure the assembly fit of the hinged connection and also helps to improve the connection reliability and working stability of the overall support structure.

[0043] In one illustrative embodiment, reference is made to... Figure 3 As shown, the retaining structure 3 also includes multiple heat insulation units 36, which are respectively disposed at the hinge points of the support rod 33 and the casing support 31 and the support ring support 32, and are suitable for isolating heat transferred from the stationary casing 4.

[0044] When the turbine is working, the temperature of the stationary casing 4 is much higher than that of the support ring 1. The heat insulation unit 36 ​​can effectively block the heat conduction path of the stationary casing 4, reduce the temperature at the connection between the support rod 33 and the support ring 1, so that the temperature of the support ring 1 is mainly affected by the ambient air temperature, reduce the thermal expansion deformation of the support ring 1 itself, avoid structural interference caused by the difference in thermal expansion between the support ring 1 and the stationary casing 4, and further improve the centering accuracy.

[0045] In some embodiments, the heat insulation unit 36 ​​includes a high thermal resistance gasket structure to adapt to the assembly space and working conditions at the hinge. The high thermal resistance gasket is respectively attached to the hinge contact surfaces of the two ends of the support rod 33 and the casing support 31 and the support ring support 32.

[0046] In some embodiments, the heat insulation unit 36 ​​is made of a low thermal conductivity and high temperature resistant material adapted to the high temperature conditions of the turbine, such as ceramic matrix composite material, high temperature heat insulation mica gasket, etc., which can maintain stable heat insulation performance and structural strength in the high temperature environment of turbine operation. The thickness of the gasket is adapted to the assembly gap at the hinge, so as to ensure the heat insulation effect without interfering with the hinge rotation flexibility between the support rod 33 and the support.

[0047] In some embodiments, the support rod 33 is made of a high-temperature alloy material with low thermal conductivity, forming a double thermal barrier structure with the high thermal resistance gasket at the hinge. Combined with the structural design of the support rod 33 itself, this further reduces the efficiency of heat transfer from the stationary casing 4 through the casing support 31 and the support rod 33 to the support ring support 32 and the support ring 1, thereby more effectively controlling the temperature change of the support ring 1 and reducing its thermal expansion deformation.

[0048] In one illustrative embodiment, reference is made to... Figure 2 As shown, the axes of the multiple retaining structures 3 and the support rods 33 are at an angle θ1 equal to the radial direction of the turbine, with the angle θ1 ranging from 60° to 75°.

[0049] Specifically, the included angle θ1 balances the support stiffness and deformation adaptability of structure 3. If the included angle θ1 is too small, the radial support stiffness of the support rod 33 will be insufficient, and it will be unable to provide stable radial positioning for the support ring 1. If the included angle θ1 is too large, the angular rotation space of the support rod 33 will be limited, making it difficult to adapt to the thermal expansion radial displacement of the stationary casing 4. This disclosure limits the included angle θ1 to 60° to 75°, which can ensure the radial support stability of the support ring 1 while giving the support rod 33 sufficient deformation adaptability space to adapt to various thermal expansion deformation conditions of the stationary casing 4.

[0050] In one illustrative embodiment, reference is made to... Figure 2 and Figure 3 As shown, the outer surface of the support ring 1 is constructed as a continuous support surface that slides with the inner surface of the linkage ring 2; or the outer surface of the support ring 1 is provided with a plurality of bosses 11 spaced apart along the circumference of the turbine, and the plurality of bosses 11 slide on the inner surface of the linkage ring 2.

[0051] The outer surface of the support ring 1 and the inner surface of the linkage ring 2 are in sliding fit. To adapt to different processing techniques, operating conditions, and cost requirements, this disclosure includes, but is not limited to, the following two support structure forms. Both can achieve stable sliding support of the support ring 1 for the linkage ring 2, and both can ensure the centering accuracy of the linkage ring 2 during rotation. Specifically:

[0052] Continuous support surface structure: The outer surface of the support ring 1 is directly constructed into a continuous cylindrical surface that matches the inner surface of the linkage ring 2, i.e., a continuous support surface. This continuous support surface slides in full with the inner surface of the linkage ring 2, providing full circumferential support for the linkage ring 2. It has good support stability and higher centering accuracy, making it suitable for high-end working conditions such as aero-engines with stringent requirements for adjustment angle accuracy.

[0053] The support ring 1 has a spaced boss structure: instead of a continuous cylindrical surface, the outer surface of the support ring 1 is provided with multiple bosses 11 evenly spaced along the turbine circumference. The outer end face of each boss 11 is a smooth arc surface, and the outer end faces of each boss 11 are coplanar, forming a cylindrical surface that matches the inner surface of the linkage ring 2. The inner surface of the linkage ring 2 slides in contact with the outer end faces of each boss 11, achieving spaced sliding support. This structure eliminates the need for precision machining of the entire outer surface of the support ring 1; only the outer end faces of the bosses 11 need to be machined, significantly reducing machining costs and difficulty, and making it suitable for operating conditions such as gas turbines where cost control is critical.

[0054] In some embodiments, refer to Figure 2 As shown, a linkage ring support seat 24 is formed on the inner side of the linkage ring 2. This linkage ring support seat 24 is the sliding contact area between the linkage ring 2 and the support ring 1 (or boss 11). The inner surface of the support ring 24 facing the support ring 1 is coated with a wear-resistant self-lubricating material. This wear-resistant self-lubricating material is suitable for the operating temperature and sliding friction conditions of the turbine. It can effectively reduce the sliding friction resistance between the linkage ring 2 and the support ring 1, improve the smoothness of the linkage ring 2 rotating around the support ring 1, and enhance the wear resistance of the linkage ring support seat 24. This reduces wear caused by long-term sliding contact, extends the service life of the linkage ring 2 and the support ring 1, and avoids affecting the centering accuracy due to wear-induced gaps.

[0055] Figure 5 A schematic diagram of the structure of the drive unit according to an embodiment of the present disclosure is shown.

[0056] In one illustrative embodiment, reference is made to... Figure 5 As shown, it also includes at least one drive unit 7, which is disposed on the outside of the stationary casing 4. The output end of the drive unit 7 is connected to the linkage ring 2 and is suitable for driving the linkage ring 2 to rotate circumferentially around the turbine centerline.

[0057] In some embodiments, the drive unit 7 can be a conventional power component in the field of aero-engines / gas turbines, such as an electric actuator or a hydraulic actuator, as long as it can provide a stable circumferential driving force for the linkage ring 2. Meanwhile, the number of drive units 7 can be flexibly adjusted according to the turbine specifications and the rotational resistance of the linkage ring 2. It can be a single or multiple drive units 7, which can be evenly distributed along the turbine circumference.

[0058] In some embodiments, the drive unit 7 is equipped with a drive mounting base 71, which is fixed to the outside of the stationary casing 4 by fasteners. At least one end of the drive unit 7 is fitted with a spherical plain bearing, and one end is movably connected to the actuator mounting base via the spherical plain bearing and / or the other end is movably connected to the outer wall of the linkage ring 2 via the spherical plain bearing. The drive unit 7, through the connection method of double-sided spherical plain bearings, can adapt to the slight deformation and positional displacement generated by the stationary casing 4 and the linkage ring 2 during turbine operation, compensate for the motion deviation between the drive unit 7 and the linkage ring 2, avoid drive force transmission jamming caused by hard connection, and reduce stress concentration at the connection point between the drive unit 7 and the linkage ring 2, thereby improving the power transmission stability and structural service life of the drive unit 7.

[0059] Figure 6 A perspective view of the blade rocker arm according to an embodiment of the present disclosure is shown.

[0060] In one illustrative embodiment, reference is made to... Figure 6 As shown, it also includes multiple blade rocker arms 5, which are respectively connected between the linkage ring 2 and the corresponding multiple adjustable blades 6, and are suitable for converting the circumferential motion of the linkage ring 2 into the rotational motion of the multiple adjustable blades 6.

[0061] In detail, when the linkage ring 2 rotates circumferentially around the turbine centerline, it applies a radial driving force to the adjustable blade 6 through the blade rocker arm 5. This driving force drives the adjustable blade 6 to rotate around its own rotation axis 61, thereby adjusting the installation angle of a single blade. Since the structural parameters of each blade rocker arm 5 are consistent and the circumferential rotation of the linkage ring 2 is synchronous, each adjustable blade 6 can rotate synchronously under the drive of the blade rocker arm 5, ensuring the consistency of the adjustment angle.

[0062] In one illustrative embodiment, reference is made to... Figure 6 As shown, the first end of the blade rocker arm 5 is fixedly connected to the rotating shaft 61 at the end of the adjustable blade 6, and the second end is movably connected to the linkage ring 2 through a ball joint connection structure.

[0063] According to the above configuration, the first end of the blade rocker arm 5 is fixedly connected to the rotating shaft 61 at the end of the adjustable blade 6. The fixed connection ensures lossless power transmission, allowing the swing of the blade rocker arm 5 to directly drive the adjustable blade 6 to rotate. The second end is movably connected to the linkage ring 2 through a ball joint connection structure. The movable connection allows the blade rocker arm 5 to swing in multiple directions relative to the linkage ring 2, compensating for the motion deviation between the linkage ring 2 and the blade rocker arm 5 during the circumferential rotation, avoiding structural jamming, stress concentration, and other problems caused by hard connection, and improving the smoothness of power transmission and the service life of the structure.

[0064] In one illustrative embodiment, reference is made to... Figure 6As shown, the ball joint connection structure is installed in the mounting groove 21 that runs through the linkage ring 2 along the turbine axis, and includes a pin 22, a spherical bearing 23, and a bearing housing 51. The pin 22 passes through the mounting groove 21 radially along the turbine; the spherical bearing 23 is slidably sleeved on the pin 22; the bearing housing 51 is formed at the second end of the blade rocker arm 5, and the bearing housing 51 is provided with a spherical socket that mates with the outer spherical surface of the spherical bearing 23; through the radial sliding of the spherical bearing 23 along the pin 22 and the mating of the spherical socket with the outer spherical surface, the blade rocker arm 5 can swing freely relative to the linkage ring 2.

[0065] Specifically, the ball joint connection structure is set in the mounting groove 21 that runs through the linkage ring 2 along the turbine axis, and the pin 22 passes through the mounting groove 21 along the radial direction of the turbine, providing a basic installation and positioning reference for the ball joint connection structure; the spherical bearing 23 is slidably sleeved on the outside of the pin 22, and it can slide slightly along the axial and radial directions of the pin 22; the bearing seat 51 is integrally formed on the second end of the blade rocker arm 5, and the inner side of the bearing seat 51 is provided with a spherical socket that matches the outer spherical surface of the spherical bearing 23. The outer spherical surface of the spherical bearing 23 fits against the spherical socket to form a spherical fit.

[0066] According to the above configuration, the ball joint connection structure achieves free swinging of the blade rocker arm 5 relative to the linkage ring 2 through dual motion adaptation: firstly, the spherical bearing 23 slides radially along the pin shaft 22; secondly, there is relative rotation between the outer spherical surface of the spherical bearing 23 and the spherical socket of the bearing seat 51. This dual motion adaptation can compensate for various motion deviations caused by the circumferential rotation of the linkage ring 2 and the slight radial displacement of the support ring 1, allowing the blade rocker arm 5 to swing slightly in any direction, completely avoiding structural jamming, ensuring smooth power transmission, and effectively dispersing structural stress, thereby extending the service life of components such as the blade rocker arm 5 and the linkage ring 2.

[0067] In some embodiments, a pin limiting hole is provided at the end of the pin shaft 22. After the ball joint connection structure is assembled, a deformable metal wire is inserted into the pin limiting hole and the deformable metal wire is appropriately bent and deformed to form an axial limit on the pin shaft 22.

[0068] According to the above setting method, no additional limiting fasteners are required, which can effectively prevent the axial movement of the pin 22 caused by vibration and rotation of the linkage ring 2 during turbine operation, and ensure the assembly stability of the ball joint connection structure. At the same time, the design cost of this limiting structure is low, and the pin 22 can be pulled out simply by restoring the deformable metal wire to its original shape during equipment maintenance and disassembly.

[0069] Embodiments of this disclosure also provide a variable geometry turbine, including a variable geometry turbine adjustment system with hot self-centering support. By integrating the adjustment system with existing components such as the turbine's stationary casing 4 and adjustable blades 6, dynamic and precise adjustment of the turbine guide vane installation angle is achieved.

[0070] According to the above configuration, the variable geometry turbine can ensure the precise centering of the linkage ring 2 under various scenarios such as turbine cold start, hot operation, and variable operating conditions, and realize the synchronous angle adjustment of the adjustable blades 6. This effectively improves the operating efficiency, structural stability and service life of the variable geometry turbine, while reducing the design and assembly difficulty of the turbine. It eliminates the need for precise assessment of the thermal expansion of the stationary casing 4, and greatly improves the reliability of engineering applications.

[0071] The embodiments of this disclosure have been described above. However, these embodiments are for illustrative purposes only and are not intended to limit the scope of this disclosure. Although various embodiments have been described above, this does not mean that the measures in the various embodiments cannot be used advantageously in combination. Various substitutions and modifications can be made by those skilled in the art without departing from the scope of this disclosure, and all such substitutions and modifications should fall within the scope of this disclosure.

Claims

1. A variable geometry turbine control system with thermal self-centering support, characterized in that, include: The support ring is coaxially mounted on the outside of the stationary casing of the turbine; The linkage ring is rotatably sleeved on the outside of the support ring and is suitable for connecting and driving multiple adjustable blades distributed along the circumference of the turbine to rotate synchronously around the blade axis. as well as Multiple retaining structures are evenly spaced along the circumference of the turbine and are respectively connected and supported between the support ring and the stationary casing, which are suitable for keeping the support ring and the stationary casing coaxial in the event of thermal expansion and deformation of the stationary casing.

2. The variable geometry turbine adjustment system according to claim 1, characterized in that, The retaining structure includes: A housing support is provided on the stationary housing; Support ring support, disposed on the support ring; and The support rod is hinged at both ends to the casing support and the support ring support, respectively, and the hinge axis is parallel to the turbine axis.

3. The variable geometry turbine adjustment system according to claim 2, characterized in that, The retaining structure also includes multiple heat insulation units, which are respectively disposed at the hinge joints between the support rod and the casing support and the support ring support, and are suitable for isolating heat transferred from the stationary casing.

4. The variable geometry turbine adjustment system according to claim 2, characterized in that, The axes of the support rods of the plurality of retaining structures are at an angle equal to the radial direction of the turbine, the angle being 60° to 75°.

5. The variable geometry turbine adjustment system according to claim 1, characterized in that, The outer surface of the support ring is configured as a continuous support surface that slides in conjunction with the inner surface of the linkage ring; or The outer surface of the support ring is provided with a plurality of bosses spaced apart along the circumference of the turbine, and the plurality of bosses are slidably supported on the inner surface of the linkage ring.

6. The variable geometry turbine adjustment system according to claim 1, characterized in that, It also includes at least one drive unit, which is disposed on the outside of the stationary casing. The output end of the drive unit is connected to the linkage ring and is suitable for driving the linkage ring to rotate circumferentially around the center line of the turbine.

7. The variable geometry turbine adjustment system according to claim 1, characterized in that, It also includes multiple blade rocker arms, which are respectively connected between the linkage ring and the corresponding multiple adjustable blades, and are suitable for converting the circumferential motion of the linkage ring into the rotational motion of the multiple adjustable blades.

8. The variable geometry turbine adjustment system according to claim 7, characterized in that, The first end of the blade rocker arm is fixedly connected to the rotation shaft of the adjustable blade end, and the second end is movably connected to the linkage ring through a ball joint connection structure.

9. The variable geometry turbine adjustment system according to claim 8, characterized in that, The ball joint connection structure is disposed in a mounting groove that extends through the linkage ring along the turbine axis, including: A pin is radially inserted into the mounting groove along the turbine. A spherical bearing, slidably fitted onto the pin; and A bearing housing is formed at the second end of the blade rocker arm, and the bearing housing is provided with a spherical bearing socket that mates with the outer spherical surface of the spherical bearing; The blade rocker arm can swing freely relative to the linkage ring by the radial sliding of the spherical bearing along the pin shaft and the engagement of the spherical bearing socket with the outer spherical surface.

10. A variable geometry turbine, characterized in that, Includes the variable geometry turbine control system as described in any one of claims 1 to 9.

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