A multi-dimensionally adjustable gas turbine auxiliary support device and a method of installing the same

Abstract

This invention provides a multi-dimensional adjustable auxiliary support device for gas turbines and its installation method, including an auxiliary support base, an upper connecting rod, a lower connecting rod, and an adjusting sleeve. The core of the device lies in the fact that the upper and lower connecting rods, connected to the adjusting sleeve by threads with opposite directions, form a precision fine-tuning mechanism. Multi-directional displacement compensation is achieved by installing a radial spherical bearing at the end of the connecting rod. This invention allows for convenient and precise fine-tuning of the support device height by rotating the adjusting sleeve, with an adjustment accuracy of ±0.1mm. Simultaneously, the radial spherical bearing effectively absorbs axial displacement of ±5mm and radial deflection of ±3° generated during unit operation, fully compensating for thermal expansion deformation and isolating vibration transmission. This device has a compact and reasonable structure, highly integrating height adjustment, thermal expansion compensation, and vibration isolation functions. It has significant advantages such as convenient installation, high adjustment accuracy, reliable operation, and strong versatility, making it particularly suitable for high-precision support and vibration reduction applications such as gas turbines and aero-engine test benches.

Description

Technical Field

[0001] This invention relates to the field of gas turbine and aero-engine technology, specifically to a multi-dimensional adjustable auxiliary support device for a gas turbine and its installation method. Background Technology

[0002] During operation, gas turbines and aero engines experience significant thermal expansion of their casings and internal structures due to the high-temperature combustion gases. Simultaneously, the high-speed rotation of the rotor and airflow disturbances induce intense mechanical vibrations. Traditional auxiliary support devices often employ rigid connections or simple shim adjustment structures, which have several inherent drawbacks: low adjustment accuracy and efficiency: height adjustment relies on manual addition or removal of shims, a cumbersome process that is difficult to guarantee accuracy and cannot achieve micron-level precise alignment. Insufficient thermal compensation: rigid connections or limited degrees of freedom of movement cannot effectively absorb the multi-directional displacements (axial, radial, and angular) caused by thermal expansion during unit operation, leading to significant additional stress within the equipment body and support structure, affecting equipment safety and lifespan. Poor vibration isolation: lacking effective vibration damping mechanisms, engine vibrations are directly transmitted through the support structure to the base platform and other related equipment, affecting testing accuracy, equipment stability, and generating noise. Limited functionality: it is difficult to integrate flexible adjustments of height, level, and angle into a single device, failing to meet the stringent requirements for installation accuracy and dynamic response under complex operating conditions. Therefore, there is an urgent need for a new type of auxiliary support device that integrates high-precision adjustment, effective thermal compensation, and excellent vibration reduction functions. Summary of the Invention

[0003] The purpose of this invention is to provide a multi-dimensional adjustable auxiliary support device for gas turbines and its installation method, which can achieve high-precision installation positioning, effectively compensate for thermal expansion deformation during operation, and has a good vibration isolation effect.

[0004] According to one objective of the present invention, a multi-dimensional adjustable auxiliary support device for a gas turbine is provided, comprising an auxiliary support base, an upper connecting rod, a lower connecting rod, and an adjusting sleeve; the upper connecting rod and the lower connecting rod are connected by the adjusting sleeve; the ends of the upper connecting rod and / or the lower connecting rod are provided with radial joint bearings, the top end of the upper connecting rod is connected to the support trunnion of the gas turbine body through another radial joint bearing, and the lower end of the lower connecting rod is connected to the auxiliary support base through the radial joint bearing.

[0005] Furthermore, the sections of the upper connecting rod and the lower connecting rod that connect to the adjusting screw sleeve are respectively provided with external threads in opposite directions, and the adjusting screw sleeve is correspondingly provided with internal threads in opposite directions.

[0006] Furthermore, rotating the adjusting screw sleeve can drive the upper connecting rod and the lower connecting rod to produce synchronous linear movements in opposite directions, thereby achieving height adjustment of the support device.

[0007] Furthermore, the accuracy of the height adjustment is ±0.1mm.

[0008] Furthermore, the radial spherical bearing allows the components connected to it to undergo axial displacement, the amount of which is ±5mm.

[0009] Furthermore, the radial spherical bearing allows the components connected to it to produce angular deflection in the radial plane, the amount of which is ±3°.

[0010] Furthermore, it also includes an anti-loosening component for locking the adjusting screw sleeve, the anti-loosening component comprising a flat nut and / or a locking washer.

[0011] Furthermore, the auxiliary support base is provided with a horizontal adjustment mechanism, which includes an adjustment screw for adjusting the lateral position of the support device in the horizontal plane.

[0012] Furthermore, the radial spherical bearing is made of wear-resistant high-temperature alloy material or is inlaid with a self-lubricating bushing.

[0013] According to another objective of the present invention, the present invention provides an installation method for the above-mentioned multi-dimensional adjustable gas turbine auxiliary support device, comprising the following steps: Step a: Fix the auxiliary support base to the installation foundation; Step b: Rotate the adjusting screw sleeve to adjust the height of the support device to a predetermined value; Step c: Connect the support point of the gas turbine or aircraft engine to the radial joint bearing at the top of the upper connecting rod.

[0014] This invention combines an upper connecting rod, a lower connecting rod, and an adjusting sleeve, with a radial spherical bearing at the end of the connecting rod, forming a highly integrated and fully functional support unit. This structure allows for rapid and precise height adjustment of the support device by rotating the adjusting sleeve, completely eliminating the drawbacks of low precision and inefficiency associated with traditional shim adjustment methods. Simultaneously, the introduction of the radial spherical bearing enables the device to automatically adapt to and effectively absorb axial displacement and radial deflection caused by thermal expansion during gas turbine operation, significantly reducing the risk of deformation and damage to the equipment due to thermal stress. Furthermore, this compact structure also provides excellent vibration isolation, improving the unit's operational stability and testing accuracy. The overall device has a reasonable structure, is easy to adjust, and integrates height adjustment, thermal compensation, and vibration reduction functions into one unit. It is highly versatile and can significantly improve installation efficiency and equipment operational reliability. Attached Figure Description

[0015] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0016] Figure 1 This is a cross-sectional structural diagram of an embodiment of the present invention; In the diagram: 1. Locking nut; 2. Radial spherical bearing; 3. Upper connecting rod; 4. Flat nut; 5. Adjusting sleeve; 6. Locking washer; 7. Lower connecting rod; 8. Auxiliary support seat; 9. Nut seat; 10. Adjusting screw. Detailed Implementation

[0017] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used 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. Therefore, they should not be construed as limiting this invention.

[0019] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; and they may 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 based on the specific circumstances.

[0020] Example 1 like Figure 1 As shown in the figure, this embodiment of a multi-dimensional adjustable gas turbine auxiliary support device includes a base, an upper connecting rod 3, a lower connecting rod 7, and an auxiliary support seat 8; wherein: The upper connecting rod 3 and the lower connecting rod 7 are connected by an adjusting sleeve 5; the threaded sections of the upper connecting rod 3 and the lower connecting rod 7 connected to the adjusting sleeve 5 have opposite thread directions. Rotating the adjusting sleeve 5 can drive the upper connecting rod 3 and the lower connecting rod 7 to move synchronously in opposite directions, so as to realize the height adjustment of the support device.

[0021] In this embodiment, the height adjustment accuracy achievable by the adjusting screw sleeve 5 is ±0.1mm. One rotation of the adjusting screw sleeve 5 results in a total height change of 2mm for the support device.

[0022] In this embodiment, the upper connecting rod 3 and the lower connecting rod 4 are respectively provided with threads of opposite directions (i.e., forward threads and reverse threads), and they both engage with an adjusting sleeve 5. By rotating the adjusting sleeve 5, the upper and lower connecting rods can be driven to move synchronously in opposite directions, thereby achieving precise fine-tuning of the total height of the support device.

[0023] The upper connecting rod 3 and / or the lower connecting rod 7 are provided with radial spherical bearings 2 at their ends. The radial spherical bearings 2 allow axial displacement of the components connected to them, with an axial displacement of ±5mm. The radial spherical bearings 2 allow angular deflection of the components connected to them in the radial plane, with an angular deflection of ±3°. The radial spherical bearings 2 are made of wear-resistant high-temperature alloy or are fitted with self-lubricating bushings.

[0024] In this embodiment, a radial spherical bearing 2 is provided at the top of the upper connecting rod 3 and / or the bottom of the lower connecting rod 7. The radial spherical bearing 2 allows the components connected to it to undergo a certain displacement in the axial direction and a certain angle of deflection in the radial plane, thereby absorbing multi-directional deformation caused by thermal expansion.

[0025] The top of the upper connecting rod 3 is connected to the gas turbine body through a radial spherical bearing 2.

[0026] The bottom end of the lower connecting rod 7 is connected to the auxiliary support seat 8 through a radial spherical bearing 2.

[0027] The device in this embodiment also includes an anti-loosening component for locking the adjusting sleeve 5, the anti-loosening component including a flat nut 4 and / or a locking washer 6.

[0028] The auxiliary support base 8 is equipped with a horizontal adjustment mechanism, which includes a nut seat 9 and an adjusting screw 10. The adjusting screw 10 is used to adjust the lateral position of the support device in the horizontal plane.

[0029] This embodiment integrates components such as locking nut 1, flat nut 4, and locking washer 6, which can reliably lock after adjustment to prevent loosening. At the same time, the entire connecting rod-bearing structure itself has certain damping characteristics, which can isolate and attenuate vibration.

[0030] The aforementioned multi-dimensional adjustable gas turbine auxiliary support device and its installation method include the following steps: Step a: Fix the auxiliary support base 8 to the installation foundation; Step b: Rotate the adjusting screw sleeve 5 to adjust the support device to the predetermined height; Step c: Connect the support point of the gas turbine or aircraft engine to the radial joint bearing 2 at the top of the upper connecting rod 3.

[0031] After step a and before step b, there is also a step of making preliminary horizontal adjustment by adjusting the adjusting screw 10 on the auxiliary support 8.

[0032] Following step c, the process further includes tightening the locking nut 1 and the anti-loosening component to lock the adjustment state.

[0033] Example 2 like Figure 1 As shown in the figure, this embodiment of a multi-dimensional adjustable gas turbine auxiliary support device includes an auxiliary support base 8, an upper connecting rod 3, a lower connecting rod 7, and an adjusting screw sleeve 5, wherein: The auxiliary support base 8 is fixed to the mounting base of the gas turbine by bolts or other fasteners. Adjusting screws 10 may be provided on the auxiliary support base 8 for initial adjustment of the lateral position of the support device in the horizontal plane.

[0034] The lower end of the lower connecting rod 7 is connected to the auxiliary support seat 8 via a radial spherical bearing 2. The outer ring of the radial spherical bearing 2 is interference-fitted with the auxiliary support seat 8 or fixed by a clamp, and the inner ring is fitted with the journal at the lower end of the lower connecting rod 7. This structure allows the lower connecting rod 7 to have an axial displacement of ±5mm relative to the auxiliary support seat 8 and a radial deflection of ±3°.

[0035] The upper connecting rod 3 and the lower connecting rod 7 are each machined with external threads in opposite directions. The adjusting sleeve 5 is a hollow sleeve with two sections of internal threads in opposite directions machined in its inner hole, which mesh with the external threads of the upper connecting rod 3 and the lower connecting rod 7, respectively. By rotating the adjusting sleeve 5 with a tool, the upper connecting rod 3 and the lower connecting rod 7 will synchronously extend into or out of the adjusting sleeve 5 under the drive of the threads, thereby achieving precise changes in the overall height of the entire support device. In this embodiment, one rotation of the adjusting sleeve 5 changes the overall height of the device by 2mm, achieving fine adjustment.

[0036] The top of the upper connecting rod 3 is connected to the support trunnion (not shown in the figure) of the gas turbine body via another radial spherical bearing 2. This spherical bearing also has multi-degree-of-freedom compensation capability.

[0037] At the upper ends of the adjusting screw sleeve 5, a flat nut 4 and a locking washer 6 are respectively provided. After the height is adjusted to the target value, tighten the flat nut 4, and use the anti-loosening function of the locking washer 6 to effectively prevent the adjusting screw sleeve 5 from loosening in a vibration environment.

[0038] At the top of the upper connecting rod 3, a locking nut 1 is also provided for locking the spherical bearing 2 connected to the gas turbine after final installation.

[0039] Installation and operation process: The auxiliary support 8 is fixed on the gas turbine mounting base, and the level is initially achieved by adjusting the screws 10.

[0040] Rotate the adjusting screw 5 to precisely adjust the height of the entire support device to the design value.

[0041] The gas turbine is hoisted into place, its supporting trunnion is connected to the spherical bearing 2 at the top of the upper connecting rod 3, and pre-tightened with the lock nut 1.

[0042] During gas turbine operation, the resulting thermal expansion causes displacement of its support points. At this time, the radial spherical bearings 2 at the upper and lower ends absorb axial displacement and radial deflection through their internal clearances and spherical movement, ensuring that thermal stress does not accumulate in the support structure. The threaded connections and bearing structures in the device together constitute a damping system capable of isolating and attenuating vibrations from the engine.

[0043] This invention achieves stepless, precise micro-adjustment of the support height, with an adjustment accuracy of ±0.1mm or even higher, significantly improving installation alignment efficiency and precision. Through the design of the radial spherical bearing, the support device is given degrees of freedom in multiple dimensions, enabling it to actively adapt to and absorb the thermal expansion deformation of the unit, thus eliminating thermal stress.

[0044] This invention features a compact structure that highly integrates adjustment, compensation, and vibration reduction functions. It is easy to install and maintain, highly versatile, and adaptable to various types of gas turbines and aero engines. It provides stable support stiffness and excellent vibration isolation performance, improving the unit's operating environment and enhancing the accuracy of test data and equipment reliability.

[0045] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A multi-dimensional adjustable auxiliary support device for a gas turbine, characterized in that, It includes an auxiliary support base, an upper connecting rod, a lower connecting rod, and an adjusting screw sleeve; the upper connecting rod and the lower connecting rod are connected by the adjusting screw sleeve; the ends of the upper connecting rod and / or the lower connecting rod are provided with radial joint bearings, the top end of the upper connecting rod is connected to the support trunnion of the gas turbine body through another radial joint bearing, and the lower end of the lower connecting rod is connected to the auxiliary support base through the radial joint bearing.

2. The multi-dimensional adjustable gas turbine auxiliary support device according to claim 1, characterized in that, The sections of the upper connecting rod and the lower connecting rod that connect to the adjusting screw sleeve are respectively provided with external threads in opposite directions, and the adjusting screw sleeve is correspondingly provided with internal threads in opposite directions.

3. The multi-dimensional adjustable gas turbine auxiliary support device according to claim 2, characterized in that, Rotating the adjusting sleeve can drive the upper connecting rod and the lower connecting rod to produce synchronous linear movements in opposite directions, thereby achieving height adjustment of the support device.

4. The multi-dimensional adjustable gas turbine auxiliary support device according to claim 3, characterized in that, The height adjustment accuracy is ±0.1mm.

5. The multi-dimensional adjustable gas turbine auxiliary support device according to claim 1, characterized in that, The radial spherical bearing allows the components connected to it to undergo axial displacement, the amount of which is ±5 mm.

6. The multi-dimensional adjustable gas turbine auxiliary support device according to claim 1 or 5, characterized in that, The radial spherical bearing allows the components connected to it to produce angular deflection in the radial plane, the amount of which is ±3°.

7. The multi-dimensional adjustable gas turbine auxiliary support device according to claim 2, characterized in that, It also includes an anti-loosening component for locking the adjusting screw sleeve, the anti-loosening component comprising a flat nut and / or a locking washer.

8. The multi-dimensional adjustable gas turbine auxiliary support device according to claim 1, characterized in that, The auxiliary support base is provided with a horizontal adjustment mechanism, which includes an adjustment screw for adjusting the lateral position of the support device in the horizontal plane.

9. The multi-dimensional adjustable gas turbine auxiliary support device according to claim 1, characterized in that, The radial spherical bearing is made of wear-resistant high-temperature alloy or is inlaid with a self-lubricating bushing.

10. The installation method of the multi-dimensional adjustable gas turbine auxiliary support device according to any one of claims 1-9, characterized in that, Includes the following steps: Step a: Fix the auxiliary support base to the installation foundation; Step b: Rotate the adjusting screw sleeve to adjust the height of the support device to a predetermined value; Step c: Connect the support point of the gas turbine or aircraft engine to the radial joint bearing at the top of the upper connecting rod.

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