Aero-engine borescope inspection low-pressure rotor rocking-turn structure

Abstract

The invention belongs to the technical field of aero-engine borescope inspection low-pressure rotor rocking-turn design, and particularly relates to an aero-engine borescope inspection low-pressure rotor rocking-turn structure which mainly comprises a driving gear, a spring, a rocking-turn ring, a plug cap and a driving rod. The air inlet casing of the aero-engine is organically combined with an existing air inlet casing, an adjustable blade inner ring and a fan first-stage rotor wheel disc of the aero-engine, the overall structure is simple and compact, switching between a non-rocking-turn state and a rocking-turn state can be easily achieved, and the air inlet casing is matched with the working state of the aero-engine and the borescope inspection situation of the aero-engine.

Description

Technical Field

[0001] The present application belongs to the technical field of design for low-pressure rotor shaking inspection of aircraft engines by borescope, and specifically relates to a low-pressure rotor shaking structure for aircraft engines by borescope inspection. Background Art

[0002] Aircraft engines on airplanes need to be inspected at regular intervals, including borescope inspection of the low-pressure rotor. Specifically, borescope holes are opened on the casing, the borescope is arranged, and the low-pressure rotor is moved for inspection.

[0003] At present, when conducting borescope inspection on the low-pressure rotor, most of the time, the operator squats in the air intake duct on the front side of the aircraft engine, crosses the air intake casing with his arm, moves the first-stage rotor blades of the low-pressure rotor fan, and drives the entire low-pressure rotor to rotate for inspection. This technical solution has the following defects:

[0004] 1) The space inside the aircraft engine inlet is small and the environment is harsh. It is difficult for the operators to enter and there is great danger.

[0005] 2) The aircraft engine air intake is equipped with support plates, adjustable blades and other structures. It is difficult for the staff to swing their arms across the air intake casing, and the range of movement is limited, making it inconvenient to quickly move the first-stage rotor blades of the low-pressure rotor fan;

[0006] 3) When conducting borescope inspection on the low-pressure rotor, the rocker staff and the borescope staff need to cooperate with each other. When the rocker staff moves the low-pressure rotor, the borescope staff observes the low-pressure rotor from the outside with a borescope. The communication between the two is inconvenient and it is difficult to coordinate well.

[0007] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0008] The purpose of the present application is to provide a method for inspecting the low-pressure rotor rocking structure of an aircraft engine through borescope, so as to overcome or alleviate at least one aspect of the known technical defects.

[0009] The technical solution of this application is:

[0010] A method for inspecting a low-pressure rotor rocking structure of an aircraft engine through borescope, comprising:

[0011] An air intake casing having an operating hole thereon;

[0012] An adjustable blade inner ring is arranged on the inner side of the air intake casing and has mounting holes thereon;

[0013] A driving gear is arranged inside the inner ring of the adjustable blade, and a driving shaft is connected thereto. The driving shaft extends into the mounting hole, and a driving hole is provided on the driving shaft;

[0014] A spring is arranged in the mounting hole and connected to the driving shaft, and relies on elastic force to make the driving gear abut against the inner side of the inner ring of the adjustable blade;

[0015] The swing ring, the rear end of which is connected to the front side of the outer edge of the fan's first-stage rotor disc, and the front end has a tooth pattern; the fan's first-stage rotor disc is located behind the inner ring of the adjustable blades;

[0016] plug cap;

[0017] A driving rod, one end of which is a swing end and the other end is a driving end;

[0018] The aircraft engine borescope inspection of the low-pressure rotor rocking structure has the following features:

[0019] In the non-shaking state, the plugging cap blocks the operating hole;

[0020] In the rocking state, the driving end of the driving rod passes through the operating hole, enters the mounting hole, and extends into the driving hole, pushing the driving gear to overcome the spring elastic force to move, so that the driving gear engages with the front end of the rocking ring, and then the rocking end of the driving rod is rotated, which can drive the driving gear and the rocking ring to rotate, drive the fan's first-stage rotor wheel to rotate, and move the low-pressure rotor.

[0021] According to at least one embodiment of the present application, in the above-mentioned aircraft engine borescope inspection low-pressure rotor rocking structure, the rear end of the rocking ring and the front inner side of the outer edge of the fan first-stage rotor disk are connected by bolt fasteners through a connecting edge and are connected by a stopper.

[0022] According to at least one embodiment of the present application, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, the outside of the air intake casing is provided with an operating platform surrounding the operating hole;

[0023] The driving rod has a crank handle and a stop boss at the crank end;

[0024] When the low-pressure rotor rocking structure of the aircraft engine borescope is in a rocking state, the stop boss abuts against the operating table.

[0025] According to at least one embodiment of the present application, in the above-mentioned aircraft engine borescope inspection low-pressure rotor rocking structure, the inner side of the adjustable blade inner ring has a mounting platform surrounding the mounting hole;

[0026] The aircraft engine borescope inspection of the low-pressure rotor rocking structure also includes:

[0027] A mounting sleeve is arranged in the mounting hole, sleeved on the outer periphery of the driving shaft, and has an outward folded edge at one end facing the driving gear, and the outward folded edge is threadedly connected to the mounting platform;

[0028] An adapter sleeve is arranged in the mounting hole, one end of which is threadedly connected to the drive shaft and the other end of which has a stop protrusion;

[0029] The two ends of the spring are sleeved on the outer periphery of the installation sleeve and the adapter sleeve, and abut against the outward folded edge and the stop protrusion.

[0030] According to at least one embodiment of the present application, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, the outer periphery of the stop protrusion has an anti-rotation protrusion;

[0031] The aircraft engine borescope inspection of the low-pressure rotor rocking structure also includes:

[0032] A fixed sleeve is arranged in the mounting hole, sleeved on the outer circumference of the adapter sleeve, and has an anti-rotation groove in the upper end;

[0033] The aircraft engine borescope inspection of the low-pressure rotor rocking structure is:

[0034] In the non-shaking state, the stop protrusion is located at the upper end of the fixed sleeve, and the anti-rotation protrusion is stuck in the anti-rotation groove;

[0035] In the shaking state, the stop protrusion is located at the lower end of the fixing sleeve, and the anti-rotation protrusion escapes from the anti-rotation groove.

[0036] According to at least one embodiment of the present application, in the above-mentioned aircraft engine borescope inspection low-pressure rotor rocking structure, the mounting hole is a stepped hole with the large hole facing outward;

[0037] The fixing sleeve is arranged in the large hole of the mounting hole, and the lower end thereof abuts against the step portion of the mounting hole and has an inward stop edge;

[0038] When the low-pressure rotor rocking structure of the aircraft engine borescope is in a rocking state, the stop protrusion abuts against the inward stop edge.

[0039] According to at least one embodiment of the present application, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, a plurality of adjustable blades are arranged circumferentially between the air intake casing and the adjustable blade inner ring, and the upper shaft diameter and the lower shaft diameter of each adjustable blade are installed in the shaft diameter installation hole opened on the air intake casing and the adjustable blade inner ring;

[0040] A support plate inner ring is arranged in the air intake casing, the support plate inner ring is connected to the front end of the adjustable blade inner ring, and a plurality of support plates are arranged between the air intake casing and the support plate inner ring along the circumferential direction.

[0041] According to at least one embodiment of the present application, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, a plurality of fan first-stage rotor blades are circumferentially arranged on the outer edge of the fan first-stage rotor disk.

[0042] According to at least one embodiment of the present application, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, the front side of the fan first-stage rotor disk has a front shaft neck, the front end of the front shaft neck extends into the inner ring of the support plate, and is connected to the inner ring of the support plate through a bearing.

[0043] According to at least one embodiment of the present application, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, an oil collecting ring is arranged inside the front end of the front journal, and corresponding oil holes are opened on the oil collecting ring, the front journal and the bearing. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 It is a schematic diagram of an aircraft engine borescope inspection of a low-pressure rotor rocking structure in a non-rocking state provided in an embodiment of the present application;

[0045] Figure 2 yes Figure 1 A partial schematic diagram of

[0046] Figure 3 It is a schematic diagram of an aircraft engine borescope inspection of a low-pressure rotor rocking structure in a rocking state provided in an embodiment of the present application;

[0047] in:

[0048] 1-intake casing; 2-inner ring of adjustable blades; 3-driving gear; 4-spring; 5-rocking ring; 6-first stage rotor disc of fan; 7-blocking cap; 8-driving rod; 9-mounting sleeve; 10-adapter sleeve; 11-fixed sleeve; 12-adjustable blades; 13-inner ring of support plate; 14-support plate; 15-first stage rotor blades of fan; 16-front journal; 17-bearing; 18-oil collecting ring.

[0049] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0050] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0051] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0052] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable 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. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0053] A method for inspecting a low-pressure rotor rocking structure of an aircraft engine through borescope, comprising:

[0054] An air intake casing 1 having an operation hole thereon;

[0055] An adjustable blade inner ring 2 is arranged on the inner side of the air intake casing 1 and has a mounting hole thereon;

[0056] A driving gear 3 is arranged inside the adjustable blade inner ring 2, and a driving shaft is connected thereto. The driving shaft extends into the mounting hole, and a driving hole is provided on the driving shaft;

[0057] The spring 4 is arranged in the mounting hole and connected to the driving shaft, and relies on the elastic force to make the driving gear 3 abut against the inner side of the adjustable blade inner ring 2;

[0058] The swing ring 5 has a rear end connected to the front side of the outer edge of the fan's first-stage rotor disc 6, and a front end having tooth patterns; the fan's first-stage rotor disc 6 is located behind the adjustable blade inner ring 2;

[0059] Plug cap 7;

[0060] A driving rod 8, one end of which is a swing end and the other end is a driving end;

[0061] The aircraft engine borescope inspection of the low-pressure rotor rocking structure has the following features:

[0062] In the non-shaking state, the blocking cap 7 blocks the operating hole. Figure 1-Figure 2 As shown;

[0063] In the rocking state, the driving end of the driving rod 8 passes through the operating hole, enters the mounting hole, and extends into the driving hole, pushing the driving gear 3 to overcome the elastic force of the spring 4 to move, so that the driving gear 3 is meshed with the front end of the rocking ring 5, and then the rocking end of the driving rod 8 is rotated, which can drive the driving gear 3 and the rocking ring 5 to rotate, drive the fan's first-stage rotor wheel 6 to rotate, and move the low-pressure rotor, such as Figure 3 shown.

[0064] The aircraft engine borescope for inspecting the low-pressure rotor rocking structure disclosed in the above-mentioned embodiment can be set in a non-rocking state when the aircraft engine is working. At this time, the operating hole on the air intake casing 1 is blocked by the plugging cap 7, and the gear 3 is pressed against the inner side of the adjustable blade inner ring 2 by the elastic force of the spring 4, so that the mounting hole on the adjustable blade inner ring 2 can be blocked to ensure the sealing of the structure and enable the aircraft engine to work normally. When performing a borescope inspection on the low-pressure rotor of an aircraft engine, the plugging cap 7 that blocks the operating hole on the air intake casing 1 can be removed, and the rocking end of the driving rod 8 can be rotated to drive the driving gear 3 and the rocking ring 5 to rotate, thereby driving the fan's first-stage rotor wheel 6 to rotate, thereby moving the low-pressure rotor for a borescope inspection. There is no need for the rocking staff to enter the aircraft engine air intake duct. The arm crosses the air intake casing to move the first-stage rotor blades of the low-pressure rotor fan. Moving the low-pressure rotor is convenient, quick, and safe. The borescope staff is on the outside of the aircraft engine, so communication is convenient and good coordination can be carried out. After the borescope inspection of the low-pressure rotor is completed, the driving rod 8 can be taken out, and the driving gear 3 is automatically reset under the elastic force of the spring 4, separated from the rocking ring 5, and set in a non-rocking state, which will not hinder the normal operation of the aircraft engine.

[0065] The above-mentioned embodiment discloses a low-pressure rotor rocking structure for borescope inspection of an aircraft engine. The design mainly includes a driving gear 3, a spring 4, a rocking ring 5, a plugging cap 7, and a driving rod 8. It is organically combined with the existing air intake casing 1, the adjustable blade inner ring 2, and the fan first-stage rotor disc 6 of the aircraft engine. The overall structure is simple and compact, and can be easily switched between a non-rocking state and a rocking state, adapting to the working state of the aircraft engine and its borescope inspection situation.

[0066] In some optional embodiments, in the above-mentioned aircraft engine borescope inspection low-pressure rotor rocking structure, the rear end of the rocking ring 5 and the front inner side of the outer edge of the fan first-stage rotor disk 6 are connected by bolt fasteners through the connecting edge and are connected by stopper fitting.

[0067] In some optional embodiments, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, the outside of the air intake casing 1 has an operating table surrounding the operating hole;

[0068] The driving rod 8 has a crank handle at its crank end and a stop boss;

[0069] When the low-pressure rotor rocking structure of the aircraft engine borescope is in a rocking state, the stop boss is pressed against the operating table to provide a positioning reference for the meshing of the driving gear 3 and the front end of the rocking ring 5.

[0070] In some optional embodiments, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, the inner side of the adjustable blade inner ring 2 has a mounting platform surrounding the mounting hole;

[0071] The aircraft engine borescope inspection of the low-pressure rotor rocking structure also includes:

[0072] A mounting sleeve 9 is arranged in the mounting hole, sleeved on the outer periphery of the driving shaft, and has an outwardly folded edge at one end facing the driving gear 3, and the outwardly folded edge is threadedly connected to the mounting platform;

[0073] The adapter sleeve 10 is arranged in the mounting hole, one end of which is threadedly connected to the drive shaft, and the other end of which has a stop protrusion;

[0074] The two ends of the spring 4 are sleeved on the outer periphery of the mounting sleeve 9 and the adapter sleeve 10, and abut against the outward folded edge and the stop protrusion.

[0075] In the aircraft engine borescope inspection low-pressure rotor shaking structure disclosed in the above embodiment, a mounting sleeve 9 and an adapter sleeve 10 are further designed to cooperate with the mounting hole and the drive gear 3 and the spring 4. The overall structure is simple and compact, easy to disassemble and assemble, and has good sealing performance.

[0076] In some optional embodiments, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, the outer periphery of the stop protrusion has an anti-rotation protrusion;

[0077] The aircraft engine borescope inspection of the low-pressure rotor rocking structure also includes:

[0078] A fixing sleeve 11 is arranged in the mounting hole, sleeved on the outer circumference of the adapter sleeve 10, and has an anti-rotation groove in the upper end;

[0079] The aircraft engine borescope inspection of the low-pressure rotor rocking structure is:

[0080] In the non-shaking state, the stop protrusion is located at the upper end of the fixing sleeve 11, and the anti-rotation protrusion is stuck in the anti-rotation groove to prevent the driving gear 3 from rotating when the aircraft engine is working, thereby affecting the normal operation of the aircraft engine;

[0081] In the rocking state, the stop protrusion is located at the lower end of the fixed sleeve 11, and the anti-rotation protrusion escapes from the anti-rotation groove, so that the low-pressure rotor can be moved by rotating the rocking end of the driving rod 8.

[0082] In some optional embodiments, in the above-mentioned aircraft engine borescope inspection low-pressure rotor rocking structure, the mounting hole is a stepped hole with the large hole facing outward;

[0083] The fixing sleeve 11 is arranged in the large hole of the mounting hole, and the lower end thereof abuts against the step portion of the mounting hole and has an inward stop edge;

[0084] When the low-pressure rotor rocking structure of the aircraft engine borescope is in a rocking state, the stop protrusion abuts against the inner stop edge, providing a positioning reference for the meshing of the driving gear 3 and the front end of the rocking ring 5.

[0085] In some optional embodiments, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, a plurality of adjustable blades 12 are arranged circumferentially between the air intake casing 1 and the adjustable blade inner ring 2, and the upper shaft diameter and the lower shaft diameter of each adjustable blade 12 are installed in the shaft diameter installation holes opened on the air intake casing 1 and the adjustable blade inner ring 2;

[0086] A support plate inner ring 13 is arranged in the air intake casing 1 , and the support plate inner ring 13 is connected to the front end of the adjustable blade inner ring 2 . A plurality of support plates 14 are arranged between the air intake casing 1 and the support plate inner ring 13 along the circumferential direction.

[0087] In some optional embodiments, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, a plurality of fan first-stage rotor blades 15 are circumferentially arranged on the outer edge of the fan first-stage rotor disk 6.

[0088] In some optional embodiments, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, the front side of the fan first-stage rotor disk 6 has a front shaft neck 16, and the front end of the front shaft neck 16 extends into the support plate inner ring 13 and is connected to the support plate inner ring 13 through a bearing 17.

[0089] In some optional embodiments, in the above-mentioned aircraft engine borescope inspection low-pressure rotor shaking structure, an oil collecting ring 18 is arranged in the front end of the front journal 16, and corresponding oil holes are opened on the oil collecting ring 18, the front journal 16 and the bearing 17.

[0090] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0091] So far, the technical solution of the present 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 the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present 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 fall within the scope of protection of the present application.

Claims

1. A method for inspecting the low-pressure rotor rocking structure of an aircraft engine through a borescope, characterized in that: include: An air intake casing (1) having an operation hole thereon; An adjustable blade inner ring (2) is arranged on the inner side of the air intake casing (1) and has a mounting hole thereon; A driving gear (3) is arranged inside the adjustable blade inner ring (2) and is connected to a driving shaft, the driving shaft extends into the mounting hole, and a driving hole is provided on the driving shaft; A spring (4) is arranged in the mounting hole and connected to the drive shaft, and relies on elastic force to make the drive gear (3) abut against the inner side of the adjustable blade inner ring (2); The swing ring (5) has a rear end connected to the front side of the outer edge of the fan's first-stage rotor disc (6), and a front end having tooth patterns; the fan's first-stage rotor disc (6) is located behind the adjustable blade inner ring (2); Plug cap (7); A driving rod (8), one end of which is a swing end and the other end of which is a driving end; The aircraft engine borescope inspection of the low-pressure rotor rocking structure has the following features: In the non-shaking state, the blocking cap (7) blocks the operating hole; In the swing state, the driving end of the driving rod (8) passes through the operating hole, enters the mounting hole, and extends into the driving hole, pushing the driving gear (3) to overcome the elastic force of the spring (4) to move, so that the driving gear (3) is meshed with the front end of the swing ring (5), and then the swing end of the driving rod (8) is rotated, which can drive the driving gear (3) and the swing ring (5) to rotate, drive the fan's first-stage rotor wheel (6) to rotate, and move the low-pressure rotor.

2. The aircraft engine borescope inspection of the low-pressure rotor rocking structure according to claim 1, characterized in that: The rear end of the swing ring (5) and the front inner side of the outer edge of the fan first-stage rotor wheel disc (6) are connected by bolt fasteners through the connecting edge and are connected by stopper fit.

3. The aircraft engine borescope inspection of the low-pressure rotor rocking structure according to claim 2, characterized in that: The outside of the air intake casing (1) is provided with an operating platform surrounding the operating hole; The swing end of the driving rod (8) is provided with a swing handle and a stop boss; When the low-pressure rotor rocking structure of the aircraft engine borescope is in a rocking state, the stop boss abuts against the operating table.

4. The aircraft engine borescope inspection of the low-pressure rotor rocking structure according to claim 1, characterized in that: The inner side of the adjustable blade inner ring (2) is provided with a mounting platform surrounding the mounting hole; The aircraft engine borescope inspection of the low-pressure rotor rocking structure also includes: A mounting sleeve (9) is arranged in the mounting hole, sleeved on the outer periphery of the driving shaft, and has an outwardly folded edge at one end facing the driving gear (3), and the outwardly folded edge is threadedly connected to the mounting platform; An adapter sleeve (10) is arranged in the mounting hole, one end of which is threadedly connected to the drive shaft and the other end of which has a stop protrusion; The two ends of the spring (4) are sleeved on the outer periphery of the installation sleeve (9) and the adapter sleeve (10), and abut against the outward folded edge and the stop protrusion.

5. The aircraft engine borescope inspection of the low-pressure rotor rocking structure according to claim 4, characterized in that: The outer periphery of the stop protrusion is provided with an anti-rotation protrusion; The aircraft engine borescope inspection of the low-pressure rotor rocking structure also includes: A fixing sleeve (11) is arranged in the mounting hole, sleeved on the outer circumference of the adapter sleeve (10), and has an anti-rotation groove in the upper end; The aircraft engine borescope inspection of the low-pressure rotor rocking structure is: In the non-rotating state, the stop protrusion is located at the upper end of the fixing sleeve (11), and the anti-rotation protrusion is stuck in the anti-rotation groove; In the shaking state, the stop protrusion is located at the lower end of the fixing sleeve (11), and the anti-rotation protrusion escapes from the anti-rotation groove.

6. The aircraft engine borescope inspection of the low-pressure rotor rocking structure according to claim 5, characterized in that: The mounting hole is a stepped hole with the large hole facing outwards; The fixing sleeve (11) is arranged in the large hole of the mounting hole, and the lower end of the fixing sleeve abuts against the step portion of the mounting hole and has an inward stop edge; When the low-pressure rotor rocking structure of the aircraft engine borescope is in a rocking state, the stop protrusion abuts against the inward stop edge.

7. The aircraft engine borescope inspection of the low-pressure rotor rocking structure according to claim 1, characterized in that: A plurality of adjustable blades (12) are arranged along the circumferential direction between the air intake casing (1) and the adjustable blade inner ring (2), and the upper shaft diameter and the lower shaft diameter of each adjustable blade (12) are installed in shaft diameter installation holes opened on the air intake casing (1) and the adjustable blade inner ring (2); A support plate inner ring (13) is arranged inside the air intake casing (1), the support plate inner ring (13) is connected to the front end of the adjustable blade inner ring (2), and a plurality of support plates (14) are arranged between the air intake casing (1) and the support plate inner ring (13) along the circumferential direction.

8. The aircraft engine borescope inspection of the low-pressure rotor rocking structure according to claim 7, characterized in that: A plurality of fan first-stage rotor blades (15) are arranged in the circumferential direction on the outer edge of the fan first-stage rotor wheel disc (6).

9. The aircraft engine borescope inspection of the low-pressure rotor rocking structure according to claim 8, characterized in that: The front side of the fan first-stage rotor wheel (6) is provided with a front shaft journal (16), the front end of which extends into the support plate inner ring (13) and is connected to the support plate inner ring (13) via a bearing (17).

10. The aircraft engine borescope inspection of the low-pressure rotor rocking structure according to claim 1, characterized in that: An oil collecting ring (18) is arranged inside the front end of the front journal (16), and corresponding oil holes are provided on the oil collecting ring (18), the front journal (16) and the bearing (17).

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