First and second devices for dynamic balancing of engine turbine rotors and rotors

Abstract

A first device for dynamically balancing an engine turbine rotor, which is arranged on a turbine disk with sufficient space, includes a lace and a groove arranged on the edge of the turbine disk, and is characterized in that the opening of the groove faces the center of the turbine disk, and the lace has a notch with an opening parallel to the axis of the turbine disk.

Description

Technical Field

[0001] The present invention relates to the field of power turbines, in particular to a first device for dynamic balancing, and further to a corresponding second device and an engine turbine rotor comprising the first device and the second device. Background Art

[0002] The dynamic balancing of an engine turbine rotor typically involves the following steps: dynamic balancing of shaft and disc components, typically achieved by removing material; dynamic balancing after assembly of the turbine disc and blades, achieved by adjusting the positions of blades of varying weights; and dynamic balancing of the rotor, typically the final balancing step. Rotor dynamic balancing is typically achieved by removing material or adding weight at specific locations. Consequently, the methods for dynamic balancing power turbine rotors are very limited. One of the most common methods involves adding balancing tape to the turbine disc and blade shroud, machining the tape to achieve the required balancing accuracy, and then performing post-assembly corrections to bring the assembly into balance. Since machining of the components is not possible after the turbine assembly stage, the most common method is to add counterweights to compensate for the balance.

[0003] Rotor dynamic balancing protects bearings from overload and fatigue fracture, thereby extending the service life of mechanical devices. Rotor imbalance typically results from uneven mass distribution, which in turn causes rotor vibration. The goal of balancing is to reduce the amplitude of this vibration to an acceptable level. Understanding the modal behavior of rotors becomes particularly important with larger or more flexible rotors. Balancing ensures smooth operation across the entire speed range. Therefore, simplifying the assembly and removal of balancing weights is crucial for cost and overall lifecycle performance.

[0004] One of the most common methods for rotor dynamic balancing currently involves adding counterweights at certain locations using bolts or screws. All of these counterweight balancing methods are patented. Therefore, it is necessary to find a method that can circumvent these patents and simplify the design of the counterweights as much as possible. Summary of the Invention

[0005] The present invention optimizes the installation of balancing weights by utilizing the lace and grooves on the rear edge of the turbine disk and the bent metal plate structure, thereby simplifying the design of the balancing weights, facilitating assembly and removal, and reducing costs. Furthermore, the balancing band is positioned on the final turbine stage, allowing for adjustment of the balancing amount after assembly of the stator module, thereby minimizing module imbalance.

[0006] The present invention proposes the following solutions:

[0007] A first device for dynamically balancing an engine turbine rotor, which is arranged on a turbine disk with sufficient space, includes a lace and a groove arranged on the edge of the turbine disk, the opening of the groove faces the center of the turbine disk, and the lace has a notch with an opening parallel to the axis of the turbine disk.

[0008] According to a preferred embodiment of the present invention, the turbine disk is a last-stage turbine disk, and the edge is a rear edge of the last-stage turbine disk.

[0009] According to a preferred embodiment of the present invention, the lace is an independent structure arranged at intervals along the circumference of the last-stage turbine disk, and the recess is in a basket shape.

[0010] The present invention also relates to a second device for dynamic balancing of an engine turbine rotor, which cooperates with the above-mentioned first device for dynamic balancing of an engine turbine rotor provided on a turbine disk having sufficient space.

[0011] According to a preferred embodiment of the present invention, the present invention comprises a pin and a boss respectively inserted into the groove of the turbine disk and the recess of the lace.

[0012] According to a preferred embodiment of the present invention, the pin and the boss are vertically connected to each other to form an integral body, wherein the pin is a trapezoidal column, and the boss is formed by bending a metal plate.

[0013] According to a preferred embodiment of the present invention, in addition to the middle part forming the boss, the metal plate also has a first end connected to the pin and a free second end opposite to the first end that is bent toward the turbine disk so as to be clamped on the corresponding end face of the lace.

[0014] According to a preferred embodiment of the present invention, the second device changes the weight of the pin and the metal plate according to the requirements of dynamic balance.

[0015] The present invention also relates to a dynamically balanced engine turbine rotor, comprising the above-mentioned first device for dynamically balancing the engine turbine rotor arranged on a turbine disk with sufficient space and the above-mentioned second device for dynamically balancing the engine turbine rotor.

[0016] According to a preferred embodiment of the present invention, it includes a first dynamic balancing and a second dynamic balancing, and the second dynamic balancing refers to assembling the above-mentioned first device for dynamic balancing of the engine turbine rotor set on the turbine disk with sufficient space and the above-mentioned second device for dynamic balancing of the engine turbine rotor.

[0017] Thus, a method for achieving dynamic balancing of a turbine rotor and a rotor dynamic balancing component are realized, which can simplify design and manufacturing, facilitate assembly and disassembly, facilitate maintenance, and reduce costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A front view showing the position and schematic outline of the turbine disc where the first device of the present invention is located;

[0019] Figure 2 A partial view showing the arrangement of the lace and the recess of the first device of the present invention provided on the turbine disk;

[0020] Figure 3 A view showing the arrangement of the first device on the turbine disk and a front view of the turbine disk showing the included laces and grooves;

[0021] Figure 4 1 and 2 show a front view of the second device of the present invention and a view of the device assembled with the first device.

[0022] 100 First Device

[0023] 101 Lace

[0024] 102 grooves

[0025] 200 Second Device

[0026] 201 pins

[0027] 202 boss

[0028] 203 first end

[0029] 204 second end

[0030] 205 metal plate

[0031] 1011 Lace Notch

[0032] 300 Assembled first device and second device

[0033] 500 turbine disc

[0034] 501 turbine disc edge

[0035] 503 The second end surface of the turbine disk

[0036] 504 The first end surface of the turbine disk DETAILED DESCRIPTION

[0037] like Figure 1 and 2 As shown, a first device 100 for dynamic balancing of an engine turbine rotor is arranged on a turbine disk 500 with sufficient space, including a lace 101 and a groove 102 arranged on the edge 501 of the turbine disk 500, the opening of the groove 102 is toward the center of the turbine disk 500, and the lace 101 has a notch 1011 with an opening parallel to the axis of the turbine disk 500. Figure 2 A detailed view of the notch is also shown.

[0038] like Figure 1FIG. 5 shows an engine turbine rotor with three turbine disks. According to a preferred embodiment of the present invention, the turbine disk 500 is the last-stage turbine disk, and the edge 501 is the rear edge of the last-stage turbine disk.

[0039] like Figure 2 As shown, according to a preferred embodiment of the present invention, the lace 101 is an independent structure arranged at intervals along the circumference of the last-stage turbine disk 500, and the recess 1011 is in a basket shape.

[0040] Figure 4 A second device 200 for dynamic balancing of an engine turbine rotor is shown, which cooperates with the above-mentioned first device 100 for dynamic balancing of an engine turbine rotor provided on a turbine disk having sufficient space.

[0041] like Figure 4 As shown, the second device 200 includes a pin 201 and a boss 202 that are inserted into the groove 102 of the turbine disk 500 and the recess 1011 of the lace 101 respectively.

[0042] like Figure 4 As shown, according to a preferred embodiment of the present invention, the pin 201 and the boss 202 are vertically connected to each other to form a whole, wherein the pin 201 is a trapezoidal column, and the boss 202 is formed by bending a metal plate.

[0043] like Figure 4 As shown, according to a preferred embodiment of the present invention, in addition to the middle portion of the metal plate forming the boss 202, the first end portion 203 connected to the pin 201 and the free second end portion 204 opposite to the first end portion are also bent toward the turbine disk so as to be snapped onto the corresponding end surface of the lace. Figure 4 As shown, the first end face 504 and the second end face 503 can be seen.

[0044] When actually performing the dynamic balancing process, according to a preferred embodiment of the present invention, the second device 200 changes the weight of the pin 201 and the metal plate 205 according to the requirements of the dynamic balancing.

[0045] Although not shown in the figures, a person skilled in the art will readily appreciate that the present invention provides a dynamically balanced engine turbine rotor, comprising the aforementioned first device for dynamically balancing the engine turbine rotor, which is arranged on a turbine disk having sufficient space, and the aforementioned second device for dynamically balancing the engine turbine rotor.

[0046] According to a preferred embodiment of the present invention, it includes a first dynamic balancing and a second dynamic balancing, and the second dynamic balancing refers to the assembly of the above-mentioned first device for dynamic balancing of the engine turbine rotor provided on a turbine disk with sufficient space and the second device for dynamic balancing of the engine turbine rotor according to the above-mentioned method. One of the most commonly used methods for dynamic balancing of turbine disk rotors is to design a balancing belt on the turbine disk for independent parts, and remove material by turning or milling to achieve the required balance value. This stage can be called the first dynamic balancing. After the turbine is assembled, adjustments are required to make the components reach the balance value, but at this time the parts cannot be processed, and the rotor balance can only be compensated by adding counterweights. This stage can be called the second dynamic balancing. All counterweight balancing methods have been applied for patent protection. Therefore, it is necessary to find a method outside of patent protection and to simplify the design of the balancing block as much as possible.

[0047] In actual dynamic balancing, this balancing weight block component is used. This component can be applied to the dynamic balancing of the rotor, simplifying the original balancing method. Figure 1 As shown in the figure, after the turbine rotor is assembled, or even after the intermediate support module is assembled, there is still enough space to add counterweights to the turbine disc of this stage. Laces and grooves are machined on the rear edge of the turbine disc for assembling counterweights. There are 36 laces along the rear edge of the turbine disc (as shown in the figure). Figure 2 (As shown). The lace has a basket-like shape, with a safety rounded corner at the bottom to prevent stress concentration. Compared to traditional prismatic shapes, this structure reduces the risk of cracking by 60%. The lace also prevents rotation after the balance weight is assembled.

[0048] Furthermore, the grooves on the turbine disk (such as Figure 3 The counterweight and groove are angled to ensure a minimum gap between the two components. This shape ensures that the counterweight is held in place within the groove by centrifugal force during turbine operation.

[0049] The counterweight block can achieve dynamic balance of the turbine rotor without the need for complex counterweight block assembly using bolts, screws, etc., thereby greatly reducing design verification and manufacturing difficulty, lowering parts costs, greatly reducing assembly difficulty, and making future maintenance and disassembly more convenient.

[0050] The axial balance weight of the present invention (such as Figure 4 The device (shown in FIG. 1 ) comprises a pin (1) that enters a groove in a circular disc and a metal plate (2) bent at the end of the disc. The pin (1) is a trapezoidal column, sized to fit the acute-angle groove and prevents relative displacement or rotation with the turbine disc. The center and ends of the metal plate (2) are bent inward, locking onto the lace and side surfaces of the rear edge of the turbine disc.

[0051] Thanks to the balancing weight, dynamic balancing can be easily achieved after rotor assembly, even after the intermediate support module is installed, if adjustments or corrections are needed. This reduces the complexity of dynamic balancing, facilitates rotor maintenance, and reduces costs. Furthermore, from an assembly perspective, the balancing weight components and assembly steps have been optimized, with the weight now clipped into the turbine disc, rather than bolted or screwed.

Claims

1. A second device for dynamic balancing of an engine turbine rotor, characterized in that: Cooperating with a first device for dynamically balancing an engine turbine rotor, which is arranged on a turbine disk with sufficient space, the first device includes a lace and a groove arranged on the edge of the turbine disk, characterized in that the opening of the groove faces the center of the turbine disk, the lace has a notch with an opening parallel to the axis of the turbine disk, the turbine disk is the last-stage turbine disk, the edge is the rear edge of the last-stage turbine disk, the lace is an independent structure arranged at intervals along the circumference of the last-stage turbine disk, and the notch is basket-shaped. The second device includes a pin and a boss respectively inserted into the groove of the turbine disk and the notch of the lace; the pin and the boss are vertically connected to each other to form a whole, wherein the pin is a trapezoidal column, and the boss is formed by bending a metal plate; in addition to forming the middle part of the boss, the first end connected to the pin and the free second end opposite to the first end of the metal plate are also bent toward the turbine disk so as to be clamped on the corresponding end face of the lace.

2. The second device for dynamic balancing of an engine turbine rotor according to claim 1, characterized in that: It includes a pin and a boss which are respectively inserted into the groove of the turbine disk and the recess of the lace.

3. The second device for dynamic balancing of an engine turbine rotor according to claim 2, characterized in that: The pin and the boss are vertically connected to each other to form a whole, wherein the pin is a trapezoidal column, and the boss is formed by bending a metal plate.

4. The second device for dynamic balancing of an engine turbine rotor according to claim 3, characterized in that: In addition to the middle portion forming the boss, the metal plate also has a first end connected to the pin and a free second end opposite to the first end bent toward the turbine disk so as to be snapped onto the corresponding end surface of the lace.

5. The second device for dynamic balancing of an engine turbine rotor according to claim 4, characterized in that: The second device changes the weight of the pin and the metal plate according to the requirements of dynamic balance.

6. A dynamically balanced engine turbine rotor, characterized in that: The invention comprises a second device for dynamic balancing of an engine turbine rotor according to any one of claims 1 to 5.

Images