Aero-engine fan rotor swing structure

Abstract

The application belongs to the technical field of fan rotor blade hole exploration inspection of an aero-engine, and particularly relates to a fan rotor oscillation structure of an aero-engine, which comprises: an adapter ring arranged in an air inlet inner ring, a rear end connected to a front side of a fan rotor disc of a first stage, and a front end provided with a tooth pattern; a driving rod arranged through a stepped hole formed on an air inlet casing and a through hole formed on the air inlet inner ring, and provided with a sleeve tooth on an outer wall of one end and a stepped guide protrusion on an outer wall of the other end; wherein the stepped guide protrusion on the driving rod is inserted into the stepped hole formed on the air inlet casing; and the sleeve tooth on the driving rod is engaged with the tooth pattern on the adapter ring.

Description

Technical Field

[0001] This application belongs to the field of borehole inspection technology for aero-engine fan rotor blades, specifically relating to a rocking structure for an aero-engine fan rotor. Background Technology

[0002] The specific process of borescope inspection of aero-engine fan rotor blades is as follows: insert a borescope through the borescope hole opened on the fan casing, rotate the fan rotor blades, and use the borescope to inspect each fan rotor blade one by one.

[0003] Currently, when performing borehole inspections on aero-engine fan rotor blades, operators manually rotate the blades through the aero-engine air intake or using tools. This technical approach has the following drawbacks:

[0004] 1) The air intake structure of the aircraft engine is long and thin. It is inconvenient to operate and it is easy to cause pollution to the air intake and damage to the fan rotor blades.

[0005] 2) At least two people are needed to complete the borehole inspection of the fan rotor blades of the aero-engine, which presents communication barriers and makes coordination difficult.

[0006] This application is made in view of the aforementioned technical deficiencies.

[0007] 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 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

[0008] The purpose of this application is to provide a rotor swing structure for an aircraft engine fan to overcome or mitigate at least one of the known technical defects.

[0009] The technical solution of this application is:

[0010] An aircraft engine fan rotor rocking structure includes:

[0011] The adapter ring is set inside the intake inner ring, with its rear end connected to the front side of the first-stage fan rotor disc, and its front end has teeth.

[0012] The drive rod passes through a stepped hole on the intake casing and a through hole on the intake inner ring at one end. The outer wall of this end has a sleeve tooth, and the outer wall of the other end has a stepped guide protrusion.

[0013] in,

[0014] The stepped guide protrusion on the drive rod is inserted into the stepped hole opened on the intake casing;

[0015] The teeth on the drive rod mesh with the teeth on the adapter ring.

[0016] According to at least one embodiment of this application, in the above-described aircraft engine fan rotor rocking structure, the end face of the drive rod exposed at one end of the air intake casing is cross-shaped.

[0017] According to at least one embodiment of this application, in the above-described aircraft engine fan rotor rocking structure, the front side of the first-stage fan rotor disk has an inward annular folded edge.

[0018] The adapter ring has an outward-facing annular fold at the rear end;

[0019] The inward and outward circular flanges are connected by multiple bolt fasteners.

[0020] According to at least one embodiment of this application, in the above-described aircraft engine fan rotor rocking structure, the inward annular fold and the outward annular fold are centered and positioned by a stop.

[0021] This application has at least the following beneficial technical effects:

[0022] A fan rotor rotation structure for an aero-engine is provided. The design incorporates a drive rod with teeth that pass through a stepped hole in the intake casing and a through hole in the inner intake ring. These teeth engage with the teeth of an adapter ring connected to the front side of the first-stage fan rotor disc. The drive rod, via the adapter ring, drives the first-stage fan rotor disc to rotate, causing the fan rotor blades of each stage to rotate for individual inspection. This method is convenient and quick, avoiding the defects caused by manually rotating the fan rotor blades through the aero-engine intake duct or by using tools. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of one state of the aircraft engine fan rotor rotation structure provided in the embodiments of this application;

[0024] Figure 2 This is a schematic diagram of another state of the aircraft engine fan rotor rotation structure provided in the embodiments of this application;

[0025] Figure 3 This is a schematic diagram of the drive rod provided in an embodiment of this application;

[0026] Figure 4 yes Figure 3 A schematic diagram of direction A;

[0027] in:

[0028] 1-Fan casing; 2-Intake casing; 3-Intake inner ring; 4-Adjustable intake stator blade; 5-Fan rotor disc; 6-Fan rotor blade; 7-Adapter ring; 8-Drive rod.

[0029] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0030] 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.

[0031] 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.

[0032] 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.

[0033] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.

[0034] In an aero-engine, the front end of the fan casing 1 is connected to the rear end of the intake casing 2. An intake inner ring 3 is provided inside the intake casing 2. Multiple adjustable intake stator blades 4 are distributed circumferentially between the intake casing 2 and the intake inner ring 3. The upper journal of each adjustable intake stator blade 4 is inserted into an upper journal mounting hole on the intake casing 2, and the lower journal is inserted into a lower journal mounting hole on the intake inner ring 3. The angle can be adjusted by an angle adjustment mechanism provided outside the intake casing 2. A multi-stage fan rotor disk 5 is provided inside the fan casing 1. Multiple fan rotor blades 6 are connected circumferentially to each stage of the fan rotor disk 5. The fan rotor disks 5 at each stage are connected by drums to form the fan rotor system. The first-stage fan rotor disk 5 is located after the intake inner ring 3. Based on this, this application provides an aero-engine fan rotor rocking structure, including:

[0035] The adapter ring 7 is set inside the intake inner ring 3, with its rear end connected to the front side of the first-stage fan rotor disc 5, and its front end has teeth.

[0036] The drive rod 8 has one end passing through the stepped hole on the intake casing 2 and the through hole on the intake inner ring 3. The outer wall of this end has a sleeve tooth, and the outer wall of the other end has a stepped guide protrusion. There is an active gap between the drive rod 8 and the stepped hole on the intake casing 2 and the through hole on the intake inner ring 3.

[0037] in,

[0038] The stepped guide protrusion on the drive rod 8 is inserted into the stepped hole opened on the intake casing 2;

[0039] The teeth on the drive rod 8 mesh with the teeth on the adapter ring 7.

[0040] When performing borehole inspection on the aero-engine fan rotor blades, the fan rotor blades 6 can be rotated using the aero-engine fan rotor rotation structure disclosed in the above embodiments. The specific process is as follows:

[0041] The end of the drive rod 8 with the sleeve teeth on its outer wall passes through the stepped hole on the intake casing 2 and the through hole on the intake inner ring 3, and extends into the intake inner ring 3.

[0042] Insert the end of the drive rod 8 with the stepped guide protrusion on its outer wall into the stepped hole on the intake casing 2 for guidance, so that the sleeve teeth on the drive rod 8 contact the adapter ring 7.

[0043] Rotate the drive rod 8 to make the upper sleeve teeth of the drive rod 8 mesh with the teeth on the adapter ring 7;

[0044] Rotate the drive rod 8, which drives the first-stage fan rotor disc 5 to rotate through the adapter ring 7, thereby causing the fan rotor blades 6 of each stage to rotate for inspection.

[0045] After inspecting the fan rotor blades of the aircraft engine, the drive rod 8 can be removed and the stepped hole on the intake casing 2 can be sealed with a plug.

[0046] Regarding the aero-engine fan rotor rotation structure disclosed in the above embodiments, those skilled in the art will understand that its design involves the toothed drive rod 8, which passes through a stepped hole in the intake casing 2 and a through hole in the intake inner ring 3, engaging with the teeth of the adapter ring 7 connected to the front side of the first-stage fan rotor disc 5. The drive rod 8 drives the first-stage fan rotor disc 5 to rotate through the adapter ring 7, causing the fan rotor blades 6 of each stage to rotate, allowing for individual inspection. This is convenient and quick, avoiding the defects caused by manually rotating the fan rotor blades through the aero-engine intake duct or by using tools.

[0047] In some alternative embodiments, in the above-described aircraft engine fan rotor rotation structure, the end face of the drive rod 8 exposed at one end of the air intake casing 2 is cross-shaped, so as to apply load and cause the drive rod 8 to rotate.

[0048] In some optional embodiments, in the above-described aircraft engine fan rotor rocking structure, the front side of the first-stage fan rotor disk 5 has an inward annular folded edge.

[0049] The adapter ring 7 has an outward-facing annular fold at its rear end;

[0050] The inward and outward circular flanges are connected by multiple bolt fasteners.

[0051] In some optional embodiments, in the above-described aircraft engine fan rotor rocking structure, the inward annular fold and the outward annular fold are centered and positioned by a stop.

[0052] 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.

[0053] 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 rotor rotation structure for an aircraft engine fan, characterized in that, include: The adapter ring (7) is set inside the intake inner ring (3), and its rear end is connected to the front side of the fan rotor disc (5) of the first stage, and its front end has teeth. The drive rod (8) is set through a stepped hole on the intake casing (2) and a through hole on the intake inner ring (3) at one end. The outer wall of this end has a sleeve tooth, and the outer wall of the other end has a stepped guide protrusion. in, The stepped guide protrusion on the drive rod (8) is inserted into the stepped hole opened on the intake casing (2); The teeth on the drive rod (8) mesh with the teeth on the adapter ring (7); The front side of the first-stage fan rotor disc (5) has an inwardly folded ring. The adapter ring (7) has an outward-facing annular fold at its rear end; The inward and outward circular flanges are connected by multiple bolt fasteners.

2. The aircraft engine fan rotor rocking structure according to claim 1, characterized in that, The end face of the drive rod (8) exposed at one end of the intake casing (2) is cross-shaped.

3. The aircraft engine fan rotor rocking structure according to claim 1, characterized in that, The inward and outward circular folds are centered and positioned by a stop.

Images