Gas turbine rotor assembly balancing device

Abstract

This utility model provides a balancing device for a gas turbine rotor assembly. The balancing device includes: a ball bearing pressure plate, which is mounted on a ball bearing housing via hexagonal head screws; an installed ball bearing is installed between the pressure plate and the housing, and the installed ball bearing is sleeved on the surface of the installed rollers of the gas turbine combined rotor assembly; an axial limiting frame, which is mounted on the side surface of the ball bearing housing; and a swing frame. This device simulates the actual assembly and support conditions of the combined gas turbine rotor to the greatest extent possible, including the center position of the combined rotor, thereby minimizing the imbalance caused by assembly errors and changes in boundary conditions. This ensures high consistency in engine test results, reduces assembly errors and component errors inherent in the process bushings, and makes the final balancing result of the gas turbine rotor consistent with the installed state. The device is easy to operate, has low error, and high precision.

Description

Technical Field

[0001] This utility model relates to the field of gas turbine rotor assembly balancing technology, and is a balancing device for aero-engine gas turbine rotor assembly. Background Technology

[0002] Aero engines operate in a high-temperature, high-pressure, high-speed, and relatively complex environment. Engine components are subjected to significant centrifugal, thermal, and aerodynamic loads. Due to differences in materials and the tightness of fit between parts, thermal deformation can occur at varying temperatures, affecting structural strength. Furthermore, engines are functional products integrating various systems, resulting in high manufacturing costs, long processing cycles, and stringent product quality requirements. Therefore, controlling the engine manufacturing and assembly process is crucial. Imbalance in the gas turbine rotor can cause engine vibration, bearing overload, shorten engine life, and reduce operating efficiency. Thus, dynamic balancing of the gas turbine rotor is a very important aspect of the assembly process.

[0003] The gas turbine rotor of a certain type of aero-engine (usually composed of compressor, gas turbine disk, gas turbine blades, etc.) is a core high-speed rotating component of the aero-engine. Its dynamic balance accuracy directly affects the overall vibration level, reliability, lifespan and safety of the engine. Since the support points of the gas turbine of a certain type of aero-engine are close together and the operating conditions are far from the critical point, a low-speed dynamic balancing method is used to balance the combined gas turbine rotor.

[0004] Since the runout of the gas turbine combined rotor after installation cannot be measured, the runout value generated during the balancing process can only be used as a theoretical reference to provide a basis for the vibration of the subsequent engine test. However, the front bearing of the gas turbine combined rotor is a split bearing that is difficult to disassemble, so a process bushing has been used as a substitute. The rear bearing of the gas turbine is a roller bearing, which is also replaced by a process component. The rotor speed is high and the balancing accuracy is high, so the use of process components may affect the balancing accuracy and cause balancing distortion. Utility Model Content

[0005] This invention addresses the technical challenges of providing sufficient external surface for multifunctional component installation while ensuring the portability of the gas turbine rotor assembly balancing device, and protecting exposed components such as speakers when not in use. It provides a gas turbine rotor assembly balancing device for aero-engines.

[0006] This utility model solves the above-mentioned technical problems through the following technical solutions:

[0007] This utility model provides a balancing device for a gas turbine rotor assembly, the balancing device for the gas turbine rotor assembly comprising:

[0008] A ball bearing pressure plate is installed on a ball bearing housing by means of an internal hex head screw. An installed ball bearing is installed between the ball bearing pressure plate and the ball bearing housing. The installed ball bearing is sleeved on the surface of the installed roller of the gas turbine combined rotor assembly.

[0009] An axial limiting bracket is mounted on the side surface of the ball bearing housing.

[0010] The swing frame is fixed to the ball bearing housing by bearing seat fixing screws on the top side.

[0011] Furthermore, there are two ball bearing housings, which are placed parallel to each other.

[0012] Furthermore, the axial limiting frame includes a connecting ring, a connecting bolt, a limiting frame, a positioning rod, and a fixing rod. The end of the positioning rod is threadedly connected to the inner cavity of a back-tightening nut installed on the side surface of the ball bearing seat. A limiting frame is installed on the surface of the positioning rod, and a connecting bolt is installed on the side surface of the limiting frame. The fixing rod is installed inside the limiting frame, and a connecting ring is installed at the top of the fixing rod.

[0013] Furthermore, the connecting bolt passes through two limiting frames, and the two limiting frames are vertically distributed.

[0014] Furthermore, the bottom of the ball bearing housing is connected to the swing frame via a locating pin.

[0015] Furthermore, an axial limiting bracket is provided at each of the two axial ends of the gas turbine combined rotor assembly.

[0016] Furthermore, the positioning rod passes through the back tightening nut and the bottom side surface of the ball bearing housing, and the other end of the positioning rod is placed in the inner cavity of the limiting frame.

[0017] Furthermore, the positioning rod and the corresponding fixing rod are vertically distributed.

[0018] Furthermore, a balancing machine interface is provided on the bottom side of the swing frame, and the swing frame is fixed to the balancing machine guide rail by screws and the balancing machine interface with a wedge-shaped groove.

[0019] Furthermore, the bearing housing fixing screws number eight, and the ball bearing housings are connected to the swing frame on the balancing machine by the eight bearing housing fixing screws respectively.

[0020] Based on common knowledge in the field, the above-mentioned preferred conditions can be combined arbitrarily to obtain various preferred embodiments of this utility model.

[0021] The positive and progressive effects of this utility model are as follows:

[0022] The gas turbine rotor assembly balancing device proposed above improves balancing accuracy: it ensures that the assembly state of the gas turbine rotor during balancing is consistent with the actual installed state, thereby improving the accuracy of balancing measurements.

[0023] Reduce measurement errors: Avoid using non-installed parts during rotor balancing, as these parts have form and position errors, dimensional errors, and especially the coaxiality of the outer diameter of the balance support and the outer diameter of the journal during processing. This causes changes in the gas turbine assembly after assembly, which in turn leads to engine vibration due to inaccurate balancing results.

[0024] To simulate the actual assembly and support of the gas turbine combined rotor to the greatest extent possible, including the center position of the combined rotor, thereby minimizing the imbalance caused by assembly errors and changes in boundary conditions, ensuring high consistency of engine test results, and improving the first-time test pass rate;

[0025] By reducing assembly errors and component errors inherent in the process bushings, the final balance of the gas turbine rotor is consistent with the installed state, making operation convenient, with small errors and high precision. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application.

[0027] Figure 1 This is a three-dimensional structural diagram of the balancing device for the gas turbine rotor assembly of this utility model.

[0028] Figure 2 This is a three-dimensional structural diagram of the right side of the balancing device for the gas turbine rotor assembly of this utility model.

[0029] Figure 3 This is an overall exploded schematic diagram of the balancing device for the gas turbine rotor assembly of this utility model.

[0030] Figure 4 This is a schematic diagram of the bearing seat fixing screw connection structure of the balancing device for the gas turbine rotor assembly of this utility model.

[0031] Explanation of reference numerals in the attached figures

[0032] 1. Ball bearing pressure plate; 2. Socket head screw; 3. Axial limit bracket; 31. Connecting ring; 32. Connecting bolt; 33. Limit frame; 34. Positioning rod; 35. Fixing rod; 4. Ball bearing housing; 5. Back tightening nut; 6. Bearing housing fixing screw; 7. Swing frame; 8. Positioning pin; 9. Mounting ball bearing; 10. Gas turbine combined rotor assembly; 11. Balancing machine interface. Detailed Implementation

[0033] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0034] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0035] In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated device, element, or component to having a specific orientation, or to be constructed and operated in a specific orientation.

[0036] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in some cases to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0037] Furthermore, the terms "installation," "setup," "equipped with," "connection," "linking," and "socketing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral structure; 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, or an internal connection between two devices, components, or parts. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0038] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other.

[0039] like Figure 1-4 As shown, the gas turbine rotor assembly balancing device includes:

[0040] A ball bearing pressure plate 1 is installed on a ball bearing housing 4 by means of an internal hex head screw 2. An installed ball bearing 9 is installed between the ball bearing pressure plate 1 and the ball bearing housing 4. The ball bearing pressure plate 1 is fixed on the bearing housing by means of an internal hex head screw 2. The pressure of the pressure plate is applied evenly to the outer ring of the installed ball bearing 9 to ensure that the inner ring of the bearing is tightly fitted with the rotor mounting roller and the outer ring is seamlessly fitted with the inner wall of the bearing housing. This completely replicates the interference fit state of the bearing-rotor-bearing housing during engine installation and avoids rotor center offset caused by the size difference between the process bushing and the actual bearing. The installed ball bearing 9 is sleeved on the surface of the mounting roller of the gas turbine combined rotor assembly 10.

[0041] Axial limiting bracket 3 is installed on the side surface of the ball bearing housing 4;

[0042] The top side of the swing frame 7 is fixed to the ball bearing seat 4 by bearing seat fixing screws 6.

[0043] There are two ball bearing housings 4, and the two ball bearing housings 4 are placed in parallel.

[0044] The axial limiting frame 3 includes a connecting ring 31, a connecting bolt 32, a limiting frame 33, a positioning rod 34, and a fixing rod 35. The end of the positioning rod 34 is threadedly connected to the inner cavity of the back-tightening nut 5 installed on the side surface of the ball bearing seat 4. The limiting frame 33 is installed on the surface of the positioning rod 34. The connecting bolt 32 is installed on the side surface of the limiting frame 33. The fixing rod 35 is installed inside the limiting frame 33. The top end of the fixing rod 35 is equipped with a connecting ring 31.

[0045] The connecting bolt 32 passes through two limiting frames 33, and the two limiting frames 33 are vertically distributed.

[0046] The bottom of the ball bearing housing 4 is connected to the swing frame 7 by a positioning pin 8. The positioning pin 8 on the swing frame 7 passes through the bottom of the bearing housing, forcibly constraining the relative position of the two bearing housings. This ensures that the two bearing housings are placed in parallel and that their central axis is completely coincident with the bearing central axis when the engine is installed, thus avoiding rotor support deviation caused by bearing housing misalignment.

[0047] An axial limiting frame 3 is provided at each of the two axial ends of the gas turbine combined rotor assembly 10, which can limit the axial movement of the rotor during the balancing process, ensure that the axial position of the rotor is consistent with the axial positioning parameters at the time of installation, and avoid interference of axial displacement with the balancing measurement.

[0048] The positioning rod 34 passes through the back tightening nut 5 and the bottom side surface of the ball bearing seat 4, and the other end of the positioning rod 34 is placed in the inner cavity of the limiting frame 33.

[0049] The positioning rod 34 and the corresponding fixing rod 35 are vertically distributed to enhance the structural stability of the limiting frame, which can limit the axial movement of the rotor during the balancing process, ensure that the axial position of the rotor is consistent with the axial positioning parameters during installation, and avoid interference of axial displacement on the balance measurement.

[0050] The bottom side of the swing frame 7 is provided with a balancing machine interface 11. The swing frame 7 is fixed to the balancing machine guide rail by screws and the wedge-shaped groove of the balancing machine interface 11. The wedge-shaped groove on the bottom side of the swing frame 7 is precisely matched with the balancing machine interface 11. The swing frame 7 is fixed to the balancing machine guide rail by screws to ensure that the horizontality and verticality of the swing frame 7 are consistent with the support guide rail parameters when the engine is installed, so as to provide a fixed reference for the subsequent installation of the bearing seat.

[0051] The number of bearing housing fixing screws 6 is eight, and the ball bearing housing 4 is connected to the swing frame 7 on the balancing machine through the eight bearing housing fixing screws 6 respectively.

[0052] The circuits, electronic components, and modules involved are all existing technologies, which can be fully implemented by those skilled in the art, and need not be elaborated upon. The content protected by this application does not involve any improvement to the software and methods.

[0053] This utility model is not limited to the above-described embodiments. Any changes in its shape or structure fall within the protection scope of this utility model. The protection scope of this utility model is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of this utility model, but all such changes and modifications fall within the protection scope of this utility model.

Claims

1. An aircraft engine gas turbine rotor assembly balancing device, characterized by, The gas turbine rotor assembly balancing device comprises: A ball bearing pressing plate (1) is installed on a ball bearing bearing seat (4) through an internal hex head screw (2), a built-in ball bearing (9) is installed between the ball bearing pressing plate (1) and the ball bearing bearing seat (4), and the built-in ball bearing (9) is sleeved on a built-in ball bearing surface of a gas turbine combined rotor assembly (10); An axial limiting frame (3) is installed on a side surface of the ball bearing bearing seat (4); A swing frame (7) is fixed to the ball bearing bearing seat (4) through a bearing seat fixing screw (6).

2. The gas turbine rotor assembly balancing apparatus of claim 1, wherein: The number of the ball bearing bearing seats (4) is two, and the two ball bearing bearing seats (4) are placed in parallel.

3. The gas turbine rotor assembly balancing apparatus of claim 1, wherein: The axial limiting frame (3) comprises a connecting ring (31), a connecting bolt (32), a limiting frame (33), a positioning rod (34), and a fixing rod (35), the end of the positioning rod (34) is threadedly connected to an inner cavity of a back-tightening nut (5) installed on a side surface of the ball bearing bearing seat (4), the surface of the positioning rod (34) is provided with the limiting frame (33), the side surface of the limiting frame (33) is provided with the connecting bolt (32), the fixing rod (35) is installed in the limiting frame (33), and the top end of the fixing rod (35) is provided with the connecting ring (31).

4. The gas turbine rotor assembly balancing apparatus of claim 3, wherein: The connecting bolt (32) penetrates two limiting frames (33), and the two limiting frames (33) are distributed vertically.

5. The gas turbine rotor assembly balancing apparatus of claim 1, wherein: The bottom of the ball bearing bearing seat (4) is connected to the swing frame (7) through a positioning pin (8).

6. The gas turbine rotor assembly balancing apparatus of claim 1, wherein: The gas turbine combined rotor assembly (10) is respectively provided with one axial limiting frame (3) at two axial ends.

7. The gas turbine rotor assembly balancing apparatus of claim 3, wherein: The positioning rod (34) penetrates the back-tightening nut (5) and a bottom end side surface of the ball bearing bearing seat (4), and the other end of the positioning rod (34) is placed in an inner cavity of the limiting frame (33).

8. The gas turbine rotor assembly balancing apparatus of claim 3, wherein: The positioning rod (34) and the corresponding fixing rod (35) are vertically distributed.

9. The gas turbine rotor assembly balancing apparatus of claim 1, wherein: The bottom side of the swing frame (7) is provided with a balancing machine interface (11), and the swing frame (7) is fixed to a balancing machine guide rail through a screw and the wedge-shaped slot balancing machine interface (11).

10. The gas turbine rotor assembly balancing apparatus of claim 1, wherein: The number of the bearing seat fixing screws (6) is eight, and the ball bearing bearing seat (4) is connected to the swing frame (7) on the balancing machine through the eight bearing seat fixing screws (6).

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