Aeroengine fan rotor balancing structure and method

Abstract

The application belongs to the technical field of fan rotor balancing of an aero-engine, and particularly relates to a fan rotor balancing structure of an aero-engine and a method thereof, wherein the fan rotor balancing structure of the aero-engine comprises: a control gap, which is arranged in a first stator inner ring and located between two first stator blades; a control plate, which is detachably blocked in the control gap; a counterweight threaded hole, which is arranged on a limiting boss on the front side of a first rotor disc; and a counterweight bolt, which is screwed in the counterweight threaded hole.

Description

Technical Field

[0001] This application belongs to the field of aero-engine fan rotor balancing technology, specifically relating to an aero-engine fan rotor balancing structure and method. Background Technology

[0002] After prolonged use, the fan rotor components of an aircraft engine are prone to wear and deformation, resulting in imbalance and increased vibration. Therefore, it is necessary to rebalance the aircraft engine. Due to structural space limitations, currently, rebalancing an aircraft engine requires detaching or even disassembling the engine to locate and eliminate the imbalance, which is a long, time-consuming, and labor-intensive process.

[0003] This application is made in view of the aforementioned technical deficiencies.

[0004] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0005] The purpose of this application is to provide a balancing structure and method for an aero-engine fan rotor to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] One aspect provides a balancing structure for an aero-engine fan rotor, including:

[0008] The control gap is opened in the inner ring of the first-stage stator, located between the two first-stage stator blades;

[0009] The control panel is detachably sealed within the control opening;

[0010] The counterweight threaded hole is opened on a limiting boss on the front side of the first-stage rotor disc;

[0011] The counterweight bolt is screwed into the counterweight threaded hole.

[0012] According to at least one embodiment of this application, the above-described aircraft engine fan rotor balancing structure further includes:

[0013] The locking plate locks the counterweight bolt onto the corresponding limit boss.

[0014] According to at least one embodiment of this application, the above-described aircraft engine fan rotor balancing structure has multiple counterweight threaded holes and their corresponding counterweight bolts and locking plates.

[0015] According to at least one embodiment of this application, in the above-mentioned aircraft engine fan rotor balancing structure, two positioning bosses are formed on the inner side of the inner ring of the first-stage stator, distributed on both sides of the control notch, and have positioning grooves thereon.

[0016] The control panel has two folded edges on its inner side, which are distributed on both sides of the control panel, and each folded edge is locked in a positioning groove.

[0017] According to at least one embodiment of this application, in the above-described aircraft engine fan rotor balancing structure, the front end of the control panel and the bottom end of the control notch are in a stepped engagement contact and are connected by connecting screws, with the contact surfaces engaging with an inclined surface.

[0018] According to at least one embodiment of this application, the above-described aircraft engine fan rotor balancing structure has multiple control notches and corresponding control plates.

[0019] On the other hand, a method for balancing an aero-engine fan rotor is provided, including:

[0020] Remove the connecting screws, push the corresponding control panel, and remove the corresponding control panel from the control notch;

[0021] Rotate the fan rotor assembly so that the counterweight bolt that needs to be replaced is aligned with the control notch on the control panel that was removed.

[0022] Remove the control panel from the control notch, remove the counterweight bolts that need to be replaced and their corresponding locking plates, replace the new counterweight bolts and lock them with the locking plates;

[0023] After replacing the counterweight bolts, push the control panel to reseal the control notch and secure it with connecting screws. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the aircraft engine fan rotor balancing structure provided in the embodiments of this application;

[0025] Figure 2 This is a partial schematic diagram of the aircraft engine fan rotor balancing structure provided in the embodiments of this application;

[0026] Figure 3 yes Figure 2 Another perspective illustration;

[0027] Figure 4 This is a schematic diagram of the control panel provided in an embodiment of this application;

[0028] in:

[0029] 1-Support plate ring; 2-First-stage stator inner ring; 3-First-stage rotor disc; 4-Support plate; 5-First-stage stator blade; 6-First-stage rotor blade; 7-Limit ring; 8-Control panel; 9-Counterweight bolt; 10-Locking plate; 11-Connecting screw.

[0030] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0031] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0032] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0033] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0034] In an aero-engine, the fan is located at the front end. Inside the front end of the fan casing, a support ring 1, a first-stage stator inner ring 2, and a first-stage rotor disk 3 are sequentially arranged. A support plate 4 is arranged circumferentially between the support ring 1 and the fan casing, supporting the support ring 1 and the fan casing. First-stage stator blades 5 are arranged circumferentially between the first-stage stator inner ring 2 and the fan casing. The first-stage stator blades 5 are adjustable blades, having a lower journal and an upper journal. The lower journal extends into a lower journal mounting hole on the first-stage stator inner ring 2, and the upper journal extends from an upper journal mounting hole on the fan casing, connecting to an adjustable blade angle adjustment mechanism. The first-stage stator blades 5 can be driven by the adjustable blade angle adjustment mechanism. The primary rotor disk 3 and the fan casing are circumferentially arranged with primary rotor blades 6 rotating synchronously. The primary rotor disk 3 has multiple circumferentially distributed tenons on its outer periphery. Each tenon forms an opening on the front side of the primary rotor disk 3. A tenon formed at the root of each primary rotor blade 6 engages with one of the openings in the tenon. The front side of the primary rotor disk 3 has multiple limiting bosses, each of which forms an inward limiting groove with the primary rotor disk 3. Each limiting groove engages a limiting ring 7, which presses against the tenon at the root of each primary rotor blade 6, thus axially positioning each primary rotor blade 6. Based on this, this application provides a balance structure and method for an aero-engine fan rotor. The following is a detailed description in conjunction with the attached... Figures 1 to 4 This application will be described in further detail.

[0035] An aircraft engine fan rotor balancing structure includes:

[0036] The control gap is opened in the inner ring 2 of the first-stage stator, located between the two first-stage stator blades 5;

[0037] The control panel 8 is detachably sealed in the control notch;

[0038] The counterweight threaded hole is opened on a limiting boss on the front side of the first-stage rotor disk 3;

[0039] Counterweight bolt 9 is screwed into the counterweight threaded hole.

[0040] Based on the aircraft engine fan rotor balancing structure disclosed in the above embodiments, the following steps can be followed when rebalancing the aircraft engine:

[0041] Remove the control panel 8 from the control notch;

[0042] Rotate the fan rotor assembly so that the counterweight bolt 9 is aligned with the control notch;

[0043] Remove the control notch from the control panel 8, remove the counterweight bolt 9, and replace it with a new counterweight bolt 9;

[0044] The control panel 8 was resealed to close the control gap, thus completing the rebalancing of the aircraft engine.

[0045] For the aircraft engine fan rotor balancing structure disclosed in the above embodiments, those skilled in the art will understand that when rebalancing the aircraft engine, it is only necessary to remove the control panel 8 from the control notch to expose the counterweight bolts 9 that need to be replaced, without having to remove or disassemble the aircraft engine, which is convenient, quick, time-saving and labor-saving.

[0046] In some optional embodiments, the above-described aircraft engine fan rotor balancing structure further includes:

[0047] Locking plate 10 locks the counterweight bolt 9 onto the corresponding limit boss. When the counterweight bolt 9 needs to be replaced, it is removed and locked after replacement.

[0048] In some optional embodiments, the above-mentioned aircraft engine fan rotor balancing structure has multiple counterweight threaded holes and their corresponding counterweight bolts 9 and locking plates 10. The specific number and distribution position can be determined by those skilled in the art based on the specific actual situation when applying this application, and will not be described in more detail here.

[0049] In some optional embodiments, in the above-described aircraft engine fan rotor balancing structure, two positioning bosses are formed on the inner side of the first-stage stator inner ring 2, distributed on both sides of the control notch, and have positioning grooves on them.

[0050] The control panel 8 has two folded edges on its inner side, which are distributed on both sides of the control panel 8. Each folded edge is locked in a positioning groove, thereby fixing the control panel 8 in the control notch and enabling positioning during the assembly and disassembly process of the control panel 8.

[0051] In some optional embodiments, in the above-mentioned aircraft engine fan rotor balancing structure, the front end of the control plate 8 and the bottom end of the control notch are in a stepped engagement, and the contact surfaces are engaged by an inclined surface to stop and position the disassembly and assembly of the control plate 8, and to connect it with the connecting screw 11. When it is necessary to remove the control plate 8, the connecting screw 11 is removed first, and then the control plate 8 is reassembled and the connecting screw 11 is screwed back on.

[0052] In some optional embodiments, the above-described aircraft engine fan rotor balancing structure has multiple control notches and corresponding control plates 8. The specific number and distribution position of these notches can be determined by those skilled in the art based on the specific actual situation when applying this application, and will not be described in more detail here.

[0053] A method for balancing an aircraft engine fan rotor includes:

[0054] Remove the connecting screw 11, push the corresponding control plate 8, and remove the corresponding control plate 8 from the control notch;

[0055] Rotate the fan rotor assembly so that the counterweight bolt 9 that needs to be replaced is aligned with the control notch of the control panel 8 that was removed.

[0056] Remove the control notch of the control panel 8, remove the counterweight bolt 9 that needs to be replaced and its corresponding locking plate 10, replace the new counterweight bolt 9 and lock it with the locking plate 10;

[0057] After replacing the counterweight bolt 9, push the control plate 8 to reseal the control notch and fix it with the connecting screw 11.

[0058] The aircraft engine fan rotor balancing method disclosed in the above embodiments is implemented based on the aircraft engine fan rotor balancing structure disclosed in the above embodiments. The description is relatively simple. For specific details, please refer to the relevant description of the aircraft engine fan rotor balancing structure. The technical effects can also be referred to the technical effects of the relevant parts of the aircraft engine fan rotor balancing structure. It will not be repeated here.

[0059] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0060] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for balancing an aero-engine fan rotor, implemented based on an aero-engine fan rotor balancing structure, the aero-engine fan rotor balancing structure comprising: The control gap is opened in the inner ring (2) of the first-stage stator, located between the two first-stage stator blades (5); The control panel (8) is detachably sealed in the control notch; The counterweight threaded hole is opened on a limiting boss on the front side of the first-stage rotor disc (3); The counterweight bolt (9) is screwed into the counterweight threaded hole; The locking plate (10) locks the counterweight bolt (9) onto the corresponding limiting boss; There are multiple counterweight threaded holes and their corresponding counterweight bolts (9) and locking plates (10); The method for balancing the fan rotor of an aero-engine is characterized by comprising: Remove the connecting screw (11), push the corresponding control plate (8), and remove the corresponding control plate (8) from the control notch; Rotate the fan rotor assembly so that the counterweight bolt (9) that needs to be replaced is aligned with the control notch of the control panel (8) that has been removed; Remove the control notch of the control panel (8), remove the counterweight bolt (9) that needs to be replaced and its corresponding locking plate (10), replace the new counterweight bolt (9) and lock it with the locking plate (10); After replacing the counterweight bolt (9), push the control panel (8) to reseal the control notch and fix it with the connecting screw (11).

2. The aero-engine fan rotor balancing method according to claim 1, characterized in that, In the balance structure of the fan rotor of the aero-engine, two positioning bosses are formed on the inner side of the inner ring (2) of the first stage stator and distributed on both sides of the control notch, and have positioning grooves on them. The control panel (8) has two folded edges on its inner side, which are distributed on both sides of the control panel (8), and each folded edge is locked in a positioning groove.

3. The aero-engine fan rotor balancing method according to claim 2, characterized in that, In the balance structure of the aero-engine fan rotor, the front end of the control plate (8) and the bottom end of the control notch are in a stepped contact and are connected by a connecting screw (11), with the contact surfaces in a beveled fit.

4. The aero-engine fan rotor balancing method according to claim 3, characterized in that, In the balance structure of the fan rotor of an aero-engine, there are multiple control notches and their corresponding control plates (8).

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