Aero-engine bore-scope inspection low-pressure rotor swing structure

Abstract

The application belongs to the technical field of low-pressure rotor swing design for bore inspection of an aero-engine, and particularly relates to a bore inspection low-pressure rotor swing structure of an aero-engine, which mainly comprises a driving gear, a spring, a swing ring, a plug cap and a driving rod, and is organically combined with an existing air inlet casing, an adjustable blade inner ring and a fan primary rotor wheel disc of the aero-engine. The overall structure is simple and compact, and can be easily switched between a non-swing state and a swing state, thereby adapting to the working state of the aero-engine and the bore inspection condition.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of bore scope inspection low-pressure rotor swing design of an aero-engine, and particularly relates to a bore scope inspection low-pressure rotor swing structure of an aero-engine. BACKGROUND

[0002] The aero-engine on an airplane needs to be inspected every certain period of time, which includes bore scope inspection of a low-pressure rotor, specifically, a bore scope hole is arranged on a casing, and a bore scope instrument is arranged in the bore scope hole, and the low-pressure rotor is rotated for inspection.

[0003] At present, when the low-pressure rotor is inspected by bore scope, a swing worker usually crouches in an air inlet of the aero-engine, crosses the air inlet casing with arms, and rotates the low-pressure rotor fan primary rotor blade to drive the whole low-pressure rotor to rotate for inspection. This technical scheme has the following defects:

[0004] 1) The space in the air inlet of the aero-engine is narrow and the environment is harsh, so it is difficult for the swing worker to enter, and there is a great risk;

[0005] 2) The air inlet of the aero-engine is provided with a support plate, adjustable blades and other structures, so it is difficult for the swing worker to cross the air inlet casing with arms, and the movement range is limited, which is not convenient for quickly rotating the low-pressure rotor fan primary rotor blade;

[0006] 3) When the low-pressure rotor is inspected by bore scope, the swing worker and the bore scope worker need to cooperate, the swing worker rotates the low-pressure rotor, and the bore scope worker observes the low-pressure rotor on the outside by using the bore scope instrument, so it is inconvenient to communicate between them and difficult to well cooperate.

[0007] The present application is proposed in view of the existence of the above technical defects. SUMMARY

[0008] The purpose of the present application is to provide a bore scope inspection low-pressure rotor swing structure of an aero-engine to overcome or alleviate at least one aspect of the known technical defects.

[0009] The technical scheme of the present application is as follows:

[0010] A bore scope inspection low-pressure rotor swing structure of an aero-engine, comprising:

[0011] an air inlet casing, which has an operation hole thereon;

[0012] an adjustable blade inner ring, which is arranged on the inner side of the air inlet casing and has a mounting hole thereon;

[0013] a drive gear, which is arranged on the inner side of the adjustable blade inner ring and has a drive shaft connected thereto, the drive shaft extends into the mounting hole, and the drive shaft has a drive hole thereon;

[0014] a spring is arranged in the mounting hole and connected with the driving shaft, and the driving gear is abutted to the inner side of the adjustable vane inner ring by the elastic force of the spring;

[0015] a rocking ring is connected at the rear end to the front inner side of the outer edge of the fan primary rotor disc, and the front end of the rocking ring is provided with a toothed pattern;

[0016] a plug cap;

[0017] a driving rod has a rocking end at one end and a driving end at the other end;

[0018] The low-pressure rotor rocking structure for the bore probe inspection of the aero-engine has:

[0019] In the non-rocking state, the plug cap plugs the operation hole;

[0020] In the rocking state, the driving end of the driving rod passes through the operation hole, enters the mounting hole, extends into the driving hole, pushes the driving gear to move against the elastic force of the spring, makes the driving gear mesh with the front end of the rocking ring, and further rotates the rocking end of the driving rod to drive the driving gear and the rocking ring to rotate, thereby driving the fan primary rotor disc to rotate.

[0021] According to at least one embodiment of the present application, in the low-pressure rotor rocking structure for the bore probe inspection of the aero-engine, the rear end of the rocking ring is connected to the front inner side of the outer edge of the fan primary rotor disc through a connecting edge by means of a bolt fastener and a stop joint.

[0022] According to at least one embodiment of the present application, in the low-pressure rotor rocking structure for the bore probe inspection of the aero-engine, the outer side of the inlet casing is provided with an operation table surrounding the operation hole;

[0023] The rocking end of the driving rod is provided with a rocking handle and a stop boss.

[0024] When the low-pressure rotor rocking structure for the bore probe inspection of the aero-engine is in the rocking state, the stop boss is abutted to the operation table.

[0025] According to at least one embodiment of the present application, in the low-pressure rotor rocking structure for the bore probe inspection of the aero-engine, the inner side of the adjustable vane inner ring is provided with a mounting table surrounding the mounting hole.

[0026] The low-pressure rotor rocking structure for the bore probe inspection of the aero-engine further comprises:

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

[0028] An adapter sleeve is arranged in the mounting hole, is threadedly connected between the driving shaft at one end, and has a stop boss at the other end.

[0029] The spring is sleeved at both ends of the mounting sleeve and the adapter sleeve, and abuts against the outwardly folded edge and the stop protrusion.

[0030] According to at least one of the embodiments of the present application, in the aero-engine bore inspection low-pressure rotor swing structure, the outer periphery of the stop protrusion has an anti-rotation protrusion.

[0031] The aero-engine bore inspection low-pressure rotor swing structure further comprises:

[0032] The fixing sleeve is arranged in the mounting hole and sleeved on the outer periphery of the adapter sleeve, and has an anti-rotation groove in the upper end.

[0033] The aero-engine bore inspection low-pressure rotor swing structure is in:

[0034] In the non-swing state, the stop protrusion is located at the upper end of the fixing sleeve, and the anti-rotation protrusion is clamped in the anti-rotation groove.

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

[0036] According to at least one of the embodiments of the present application, in the aero-engine bore inspection low-pressure rotor swing structure, the mounting hole is a stepped hole, and the large hole is outward.

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

[0038] When the aero-engine bore inspection low-pressure rotor swing structure is in the swing state, the stop protrusion abuts against the inward stop edge.

[0039] According to at least one of the embodiments of the present application, in the aero-engine bore inspection low-pressure rotor swing structure, a plurality of adjustable vanes are arranged circumferentially between the inlet casing and the inner ring of the adjustable vane, and the upper shaft diameter and the lower shaft diameter of each adjustable vane are arranged in the shaft diameter mounting hole arranged on the inlet casing and the inner ring of the adjustable vane.

[0040] A support inner ring is arranged in the inlet casing, the support inner ring is connected to the front end of the inner ring of the adjustable vane, and a plurality of support plates are arranged circumferentially between the inlet casing and the support inner ring.

[0041] According to at least one of the embodiments of the present application, in the aero-engine bore inspection low-pressure rotor swing structure, a plurality of fan primary rotor blades are arranged circumferentially on the outer edge of the fan primary rotor disc.

[0042] According to at least one of the embodiments of the present application, in the aero-engine bore inspection low-pressure rotor swing structure, the front side of the fan primary rotor disc has a front shaft neck, the front end of the front shaft neck extends into the support inner ring, and the support inner ring and the support inner ring are connected through a bearing.

[0043] According to at least one embodiment of the present application, in the aero-engine bore inspection low-pressure rotor swing structure described above, an oil collecting ring is arranged in the front end of the front journal, and the oil collecting ring, the front journal and the bearing are provided with corresponding oil holes. BRIEF DESCRIPTION OF DRAWINGS

[0044] Figure 1 is a schematic view of the aero-engine bore inspection low-pressure rotor swing structure in a non-swing state according to an embodiment of the present application;

[0045] Figure 2 is a partial schematic view of Figure 1 ;

[0046] Figure 3 is a schematic view of the aero-engine bore inspection low-pressure rotor swing structure in a swing state according to an embodiment of the present application;

[0047] Wherein:

[0048] 1 - air inlet casing; 2 - adjustable blade inner ring; 3 - drive gear; 4 - spring; 5 - swing ring; 6 - fan first-stage rotor wheel disc; 7 - plug cap; 8 - drive rod; 9 - mounting sleeve; 10 - adapter sleeve; 11 - fixing sleeve; 12 - adjustable blade; 13 - support plate inner ring; 14 - support plate; 15 - fan first-stage rotor blade; 16 - front journal; 17 - bearing; 18 - oil collecting ring.

[0049] In order to better illustrate the present embodiment, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0050] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described below in conjunction with the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design.

[0051] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the application shall be understood as having the common meaning to those of ordinary skill in the art to which the application belongs. The words indicating the orientation used in the description of the application are only used to indicate the relative direction or positional relationship, and the relative positional relationship may also change accordingly when the absolute position of the described object changes. The "includes" used in the description of the application indicates that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and does not exclude other elements or objects.

[0052] In addition, it should be further pointed out that, unless otherwise defined and limited, the "installation", "connection" and similar words used in the description of the application should be understood in a broad sense, for example, the connection can be fixed connection or detachable connection; can be mechanical connection or electrical connection; can be directly connected or indirectly connected through intermediate medium, and those skilled in the art can understand the specific meaning of the application according to the specific circumstances.

[0053] An aero-engine hole-probe inspection low-pressure rotor rocking structure, comprising:

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

[0055] An adjustable blade inner ring 2 provided inside the air inlet casing 1 and having a mounting hole thereon;

[0056] A driving gear 3 provided inside the adjustable blade inner ring 2 and connected with a driving shaft, the driving shaft extending into the mounting hole and having a driving hole on the driving shaft;

[0057] A spring 4 provided in the mounting hole and connected with the driving shaft, the spring making the driving gear 3 adhere to the inside of the adjustable blade inner ring 2 by elastic force;

[0058] A rocking ring 5 connected at the rear end to the front side inside the outer edge of a fan primary rotor disc 6 and having a toothed pattern at the front end, the fan primary rotor disc 6 being located behind the adjustable blade inner ring 2;

[0059] A plug cap 7;

[0060] A driving rod 8 having a rocking end at one end and a driving end at the other end;

[0061] The aero-engine hole-probe inspection low-pressure rotor rocking structure has:

[0062] A non-rocking state, the plug cap 7 plugging the operation hole, as shown in Figures 1-2 ;

[0063] In the rotating state, the driving rod 8 driving end passes through the operation hole, enters the installation hole, extends into the driving hole, pushes the driving gear 3 to overcome the elastic force of the spring 4, makes the driving gear 3 mesh with the front end of the rotating ring 5, and further rotates the driving rod 8 rotating end, which can drive the driving gear 3 and the rotating ring 5 to rotate, drive the fan primary rotor wheel disc 6 to rotate, and drive the low-pressure rotor. Figure 3

[0064] The above-mentioned embodiment discloses the low-pressure rotor rotating structure for the aero-engine borescope inspection, which can be set in the non-rotating state during the working of the aero-engine. At this time, the operation hole on the inlet casing 1 is plugged by the plug cap 7, the driving gear 3 is attached to the inner side of the adjustable blade inner ring 2 under the elastic force of the spring 4, the installation hole on the adjustable blade inner ring 2 is plugged, the sealing of the structure is ensured, and the aero-engine can work normally. When the low-pressure rotor of the aero-engine is inspected by the borescope, the plug cap 7 plugging the operation hole on the inlet casing 1 is removed, the driving rod 8 rotating end is rotated, the driving gear 3 and the rotating ring 5 are driven to rotate, the fan primary rotor wheel disc 6 is driven to rotate, and the low-pressure rotor is driven to rotate, so that the borescope inspection is performed. The rotating staff does not need to enter the inlet passage of the aero-engine, the arm crosses the inlet casing to drive the low-pressure rotor fan primary rotor blade, the low-pressure rotor is driven conveniently and quickly, the safety is high, the borescope staff is located outside the aero-engine, the communication is convenient, the cooperation is good, and after the borescope inspection of the low-pressure rotor is completed, the driving rod 8 is removed, the driving gear 3 is automatically reset under the elastic force of the spring 4, is separated from the rotating ring 5, and is set in the non-rotating state, so that the normal working of the aero-engine is not affected.

[0065] The above-mentioned embodiment discloses the low-pressure rotor rotating structure for the aero-engine borescope inspection, which is mainly designed to include the driving gear 3, the spring 4, the rotating ring 5, the plug cap 7, the driving rod 8, and is organically combined with the existing inlet casing 1, the adjustable blade inner ring 2 and the fan primary rotor wheel disc 6 of the aero-engine. The overall structure is simple and compact, can be easily switched between the non-rotating state and the rotating state, and is suitable for the working state of the aero-engine and the borescope inspection condition.

[0066] In some optional embodiments, the low-pressure rotor rotating structure for the aero-engine borescope inspection disclosed above, the rear end of the rotating ring 5 and the front side inside the outer edge of the fan primary rotor wheel disc 6 are connected through the connecting edge by the bolt fastener and are connected by the stop port.

[0067] In some optional embodiments, the low-pressure rotor rotating structure for the aero-engine borescope inspection disclosed above, the inlet casing 1 has an operation table surrounding the operation hole on the outer side;

[0068] The rotating end of the driving rod 8 has a rotating handle and a stop boss.

[0069] ​The aero-engine bore inspection low-pressure rotor rocking structure is in a rocking state, the stop protrusion is attached to the operation table, and a positioning reference is provided for engagement of the driving gear 3 and the front end of the rocking ring 5.

[0070] In some optional embodiments of the aero-engine bore inspection low-pressure rotor rocking structure, the inner side of the adjustable blade inner ring 2 has a mounting table with a surrounding mounting hole;

[0071] The aero-engine bore inspection low-pressure rotor rocking structure further comprises:

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

[0073] The adapter sleeve 10 is arranged in the mounting hole, is threadedly connected between one end and the driving shaft, and has a stop protrusion at the other end;

[0074] The spring 4 is sleeved on the outer periphery of the mounting sleeve 9 and the adapter sleeve 10 at both ends and is abutted against the outwardly folded edge and the stop protrusion.

[0075] In the aero-engine bore inspection low-pressure rotor rocking structure disclosed in the above embodiments, the mounting sleeve 9 and the adapter sleeve 10 are further designed in the mounting hole and are cooperatively arranged with the driving gear 3 and the spring 4, so that the overall structure is simple and compact, easy to disassemble and assemble, and has good sealing performance.

[0076] In some optional embodiments of the aero-engine bore inspection low-pressure rotor rocking structure, the outer periphery of the stop protrusion has an anti-rotation protrusion;

[0077] The aero-engine bore inspection low-pressure rotor rocking structure further comprises:

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

[0079] The aero-engine bore inspection low-pressure rotor rocking structure is in:

[0080] A non-rocking state, the stop protrusion is at the upper end of the fixing sleeve 11, the anti-rotation protrusion is clamped in the anti-rotation groove, so as to prevent the driving gear 3 from rotating when the aero-engine is working, thereby affecting the normal working of the aero-engine;

[0081] A rocking state, the stop protrusion is at the lower end of the fixing sleeve 11, the anti-rotation protrusion is out of the anti-rotation groove, so that the low-pressure rotor can be rocked by rotating the rocking end of the driving rod 8.

[0082] In some optional embodiments of the aero-engine bore inspection low-pressure rotor rocking structure, the mounting hole is a stepped hole, and the large hole is outward.

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

[0084] When the aero-engine bore inspection low-pressure rotor swing structure is in a swing state, the stop protrusion abuts against the inward stop edge, thereby providing a positioning reference for the engagement of the drive gear 3 and the front end of the swing ring 5.

[0085] In some optional embodiments, the aero-engine bore inspection low-pressure rotor swing structure described above, a plurality of adjustable vanes 12 are arranged between the air inlet casing 1 and the adjustable vane inner ring 2 in the circumferential direction, and the upper shaft diameter and the lower shaft diameter of each adjustable vane 12 are arranged in the shaft diameter mounting hole arranged on the air inlet casing 1 and the adjustable vane inner ring 2.

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

[0087] In some optional embodiments, the aero-engine bore inspection low-pressure rotor swing structure described above, a plurality of fan primary rotor blades 15 are arranged on the outer edge of the fan primary rotor wheel disc 6 in the circumferential direction.

[0088] In some optional embodiments, the aero-engine bore inspection low-pressure rotor swing structure described above, the front side of the fan primary rotor wheel disc 6 has a front shaft neck 16, the front end of the front shaft neck 16 extends into the support inner ring 13, and the support inner ring 13 is connected to the support inner ring 13 through a bearing 17.

[0089] In some optional embodiments, the aero-engine bore inspection low-pressure rotor swing structure described above, an oil collecting ring 18 is arranged at the front end of the front shaft neck 16, and the oil collecting ring 18, the front shaft neck 16 and the bearing 17 are provided with corresponding oil holes.

[0090] Each embodiment in the specification is described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts of each embodiment can be referred to each other, and the embodiments and technical features in the application can be combined to obtain new embodiments without conflict.

[0091] So far, the technical scheme of the application has been described in combination with the preferred embodiments shown in the drawings. It should be understood by those skilled in the art that the protection scope of the application is obviously not limited to these specific embodiments. Without deviating from the principles of the application, those skilled in the art can make equivalent changes or replacements to the related technical features, and the technical scheme after the changes or replacements will fall within the protection scope of the application.

Claims

1. An aeroengine bore- scope inspection low pressure rotor swing structure, characterized by, The invention relates to an aero-engine hole-probe inspection low-pressure rotor rocking structure, comprising: an air intake casing (1) having an operation hole; an adjustable blade inner ring (2) arranged inside the air intake casing (1) and having a mounting hole; a driving gear (3) arranged inside the adjustable blade inner ring (2) and having a driving shaft connected thereto, the driving shaft extending into the mounting hole and having a driving hole; a spring (4) arranged in the mounting hole and connected to the driving shaft, the spring (4) making the driving gear (3) adhere to the inside of the adjustable blade inner ring (2) by elastic force; a rocking ring (5) having a toothed front end and being connected to the front inside of the outer edge of a fan primary rotor disc (6) behind the adjustable blade inner ring (2); a plug cap (7); a driving rod (8) having a rocking end and a driving end; the aero-engine hole-probe inspection low-pressure rotor rocking structure has: a non-rocking state, in which the plug cap (7) blocks the operation hole; a rocking state, in which the driving end of the driving rod (8) passes through the operation hole, enters the mounting hole, extends into the driving hole, pushes the driving gear (3) to move against the elastic force of the spring (4), makes the driving gear (3) engage with the front end of the rocking ring (5), and further rotates the rocking end of the driving rod (8) to drive the driving gear (3) and the rocking ring (5) to rotate, thereby driving the fan primary rotor disc (6) to rotate and rock the low-pressure rotor; the outside of the air intake casing (1) has an operation table surrounding the operation hole; the rocking end of the driving rod (8) has a rocking handle and a stop protrusion; when the aero-engine hole-probe inspection low-pressure rotor rocking structure is in the rocking state, the stop protrusion adheres to the operation table; the inside of the adjustable blade inner ring (2) has a mounting table surrounding the mounting hole; the aero-engine hole-probe inspection low-pressure rotor rocking structure further comprises: a mounting sleeve (9) arranged in the mounting hole and sleeved on the outer periphery of the driving shaft, one end of the mounting sleeve (9) having an outward folding edge facing the driving gear (3) and being threadedly connected to the mounting table; an adapter sleeve (10) arranged in the mounting hole and threadedly connected between the driving shaft and the other end of the adapter sleeve (10), the other end of the adapter sleeve (10) having a stop protrusion; the spring (4) is sleeved on the outer periphery of the mounting sleeve (9) and the adapter sleeve (10) and abuts against the outward folding edge and the stop protrusion.

2. The aero-engine hole-probe inspection low-pressure rotor rocking structure according to claim 1, wherein: the rear end of the rocking ring (5) and the front inside of the outer edge of the fan primary rotor disc (6) are connected by a connecting edge through bolt fasteners and are connected by a stop joint.

3. The aero-engine hole-probe inspection low-pressure rotor rocking structure according to claim 2, wherein: the outer periphery of the stop protrusion has an anti-rotation protrusion; the aero-engine hole-probe inspection low-pressure rotor rocking structure further comprises: a fixing sleeve (11) arranged in the mounting hole and sleeved on the outer periphery of the adapter sleeve (10), the upper end of the fixing sleeve (11) having an anti-rotation groove; when the aero-engine hole-probe inspection low-pressure rotor rocking structure is in: the non-rocking state, the stop protrusion is on the upper end of the fixing sleeve (11) and the anti-rotation protrusion is clamped in the anti-rotation groove; the rocking state, the stop protrusion is on the lower end of the fixing sleeve (11) and the anti-rotation protrusion is out of the anti-rotation groove.

4. The aero-engine bore inspection low-pressure rotor swing structure according to claim 3, characterized in that, the mounting hole is a stepped hole with a large hole outward; the fixing sleeve (11) is arranged in the large hole of the mounting hole and abuts against the lower end of the stepped part of the mounting hole and has an inward stop edge; when the aero-engine bore inspection low-pressure rotor swing structure is in the swing state, the stop protrusion abuts against the inward stop edge.

5. The aero-engine bore inspection low-pressure rotor swing structure according to claim 4, characterized in that, a plurality of adjustable blades (12) are arranged circumferentially between the inlet 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 arranged in the shaft diameter mounting hole of the inlet casing (1) and the adjustable blade inner ring (2); the support plate inner ring (13) is arranged in the inlet casing (1) and connected to the front end of the adjustable blade inner ring (2), and a plurality of support plates (14) are arranged circumferentially between the inlet casing (1) and the support plate inner ring (13).

6. The aero-engine bore inspection low-pressure rotor swing structure according to claim 5, characterized in that, a plurality of fan primary rotor blades (15) are arranged circumferentially on the outer edge of the fan primary rotor disc (6).

7. The aero-engine bore inspection low-pressure rotor swing structure according to claim 6, characterized in that, the fan primary rotor disc (6) has a front shaft journal (16) on the front side, and the front end of the front shaft journal (16) extends into the support plate inner ring (13) and is connected to the support plate inner ring (13) through the bearing (17).

8. The aero-engine bore inspection low-pressure rotor swing structure according to claim 7, characterized in that, an oil collecting ring (18) is arranged at the front end of the front shaft journal (16), and the oil collecting ring (18), the front shaft journal (16), and the bearing (17) are provided with corresponding oil holes.

Images