Aircraft engine rotor journal disc cavity nut dismounting structure

Abstract

The application belongs to the technical field of dismounting the nut in the cavity of the aero-engine rotor journal disc, and particularly relates to a dismounting structure of the nut in the cavity of the aero-engine rotor journal disc, which comprises a support plate connected to a stator case and provided with a through hole, a connecting rod penetrating through the through hole and extending into the cavity of the rotor journal disc, a support base connected to one end of the connecting rod extending into the cavity of the rotor journal disc, a supporting cylinder connected to the support base, a wrench shaft penetrating through the supporting cylinder and connected to the supporting cylinder through a screw thread, a wrench head connected to one end of the wrench shaft and provided with a wrench hole, the wrench hole clamping the nut connected to the rotor journal end and the drum connecting edge, a hydraulic cylinder connected to the supporting cylinder, a transmission arm connected to the hydraulic rod of the hydraulic cylinder and hinged to the other end of the wrench shaft, a handle hinged to the other end of the connecting rod and provided with a strip-shaped hole, a support block connected to the support plate, and a roller rod arranged in the strip-shaped hole and connected to the support block.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of dismounting the nut in the cavity of the journal disc of the rotor shaft of an aero-engine, and particularly relates to a dismounting structure of the nut in the cavity of the journal disc of the rotor shaft of an aero-engine. BACKGROUND

[0002] The rotor part of an aero-engine is arranged in a stator casing, wherein the end of the journal of the rotor shaft is fixed with a screw rod, and the drum connection edge is connected through cooperation with the nut. Since the nut is located in the cavity of the journal disc of the rotor shaft, and the rotor shaft is overall slender and the internal space is narrow, it is difficult to dismount the nut.

[0003] The present application is proposed in view of the existence of the above technical defects.

[0004] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present patent application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0005] The purpose of the present application is to provide a dismounting structure of the nut in the cavity of the journal disc of the rotor shaft of an aero-engine to overcome or alleviate at least one aspect of the known technical defects.

[0006] The technical solution of the present application is:

[0007] A dismounting structure of the nut in the cavity of the journal disc of the rotor shaft of an aero-engine, comprising:

[0008] A support plate connected to the stator casing, having a through hole thereon;

[0009] A connecting rod arranged through the through hole and extending into the cavity of the journal disc of the rotor shaft;

[0010] A support base connected to one end of the connecting rod extending into the cavity of the journal disc of the rotor shaft;

[0011] A support cylinder connected to the support base;

[0012] A wrench shaft arranged through the support cylinder and connected to the support cylinder through a helical thread;

[0013] A wrench head connected to one end of the wrench shaft, having a wrench hole thereon; the wrench hole is clamped on the nut connected to the end of the journal of the rotor shaft and the drum connection edge;

[0014] A hydraulic cylinder connected to the support cylinder;

[0015] A transmission arm connected to the hydraulic rod of the hydraulic cylinder and hinged to the other end of the wrench shaft;

[0016] a handle, hinged at the other end of the connecting rod, having a slot on it;

[0017] a support block, connected to the support plate;

[0018] a roller, disposed in the slot, connected to the support block.

[0019] According to at least one embodiment of the present application, in the above-mentioned aviation engine rotor shaft neck disc cavity nut dismounting structure, the support plate is connected through bolts using bolt holes on the stator case connection edge.

[0020] According to at least one embodiment of the present application, in the above-mentioned aviation engine rotor shaft neck disc cavity nut dismounting structure, the support plate is connected through bolts using a screw sleeve to connect the screw rod of the rotor shaft neck front end rotor component.

[0021] According to at least one embodiment of the present application, in the above-mentioned aviation engine rotor shaft neck disc cavity nut dismounting structure, the perforation is a special-shaped hole.

[0022] According to at least one embodiment of the present application, in the above-mentioned aviation engine rotor shaft neck disc cavity nut dismounting structure, the support includes:

[0023] an upper wall plate, connected to one end of the connecting rod extending into the rotor shaft neck disc cavity;

[0024] a lower wall plate, connected to the upper wall plate, forming a cavity therebetween; the transmission arm is located in the cavity.

[0025] According to at least one embodiment of the present application, in the above-mentioned aviation engine rotor shaft neck disc cavity nut dismounting structure, the support cylinder is connected to the support through bolts using a flange plate.

[0026] According to at least one embodiment of the present application, in the above-mentioned aviation engine rotor shaft neck disc cavity nut dismounting structure, the support cylinder and its corresponding wrench shaft, wrench head, hydraulic cylinder, and transmission arm have multiple groups.

[0027] According to at least one embodiment of the present application, in the above-mentioned aviation engine rotor shaft neck disc cavity nut dismounting structure, the handle has a slot on it; the slot has a slot-shaped hole on both sides of the side wall;

[0028] Each end of the roller corresponds to extending into one slot-shaped hole.

[0029] According to at least one embodiment of the present application, in the above-mentioned aviation engine rotor shaft neck disc cavity nut dismounting structure, the support block has two, located between the slots;

[0030] According to at least one embodiment of the present application, in the above-mentioned aviation engine rotor shaft neck disc cavity nut dismounting structure, it further includes:

[0031] The hinge shaft is hinged between the two side walls of the slot at the end of the connecting rod away from the support. BRIEF DESCRIPTION OF DRAWINGS

[0032] Fig. 1 Figure 1 is an application schematic diagram of the dismounting structure of the nut in the cavity of the aero-engine rotor journal disc provided by the embodiment of the present application;

[0033] Fig. 2 Figure 1 is an application schematic diagram of the dismounting structure of the nut in the cavity of the aero-engine rotor journal disc provided by the embodiment of the present application;

[0034] Fig. 3 Figure 1 is an application schematic diagram of the dismounting structure of the nut in the cavity of the aero-engine rotor journal disc provided by the embodiment of the present application;

[0035] Fig. 4 Figure 1 is an application schematic diagram of the dismounting structure of the nut in the cavity of the aero-engine rotor journal disc provided by the embodiment of the present application;

[0036] Wherein:

[0037] 1- support plate; 2- stator casing; 3- connecting rod; 4- rotor journal; 5- support; 6- support cylinder; 7- torsion shaft; 8- torsion head; 9- drum; 10- nut; 11- hydraulic cylinder; 12- transmission arm; 13- handle; 14- support block; 15- roller; 16- hinge shaft.

[0038] In order to better illustrate the 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 patent. DETAILED DESCRIPTION

[0039] 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 in detail below in combination with the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of the present application, which 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 usual design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0040] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as having the common meaning to those of ordinary skill in the art to which the present application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the description of the present application indicate relative directions or positional relationships and are not intended to imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and the relative positional relationship can change accordingly when the absolute position of the described object changes, and therefore cannot be understood as a limitation on the present application. The words "first", "second", "third" and the like used in the description of the present application are only for the purpose of description and are used to distinguish different components, and cannot be understood as indicating or implying relative importance. The words "one", "an" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the number, but should be understood as the presence of at least one. The words "including" or "containing" and the like used in the description of the present application mean that the elements or objects appearing before the words are encompassed by the elements or objects listed after the words and their equivalents, and other elements or objects are not excluded.

[0041] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the words "mounting", "connecting", "connecting" and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be a fixed connection, or a detachable connection, or an integral connection; can be a mechanical connection, or an electrical connection; can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements, and those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0042] The following will be described in conjunction with the accompanying drawings Figs. 1 to 4 The present application will be further described in detail.

[0043] An aviation engine rotor journal disc cavity nut dismounting structure, comprising:

[0044] A support plate 1 is connected to the stator casing 2, and has a through hole thereon;

[0045] A connecting rod 3 is arranged through the through hole and extends into the rotor journal 4 disc cavity;

[0046] A support base 5 is connected to one end of the connecting rod 3 extending into the rotor journal 4 disc cavity;

[0047] A support cylinder 6 is connected to the support base 5;

[0048] A wrench shaft 7 is arranged through the support cylinder 6 and connected with the support cylinder 6 through a helical thread cooperation;

[0049] The wrench head 8 is connected to one end of the wrench shaft 7, and has a wrench hole;

[0050] The hydraulic cylinder 11 is connected to the support cylinder 6;

[0051] The transmission arm 12 is connected to the hydraulic rod of the hydraulic cylinder 11, and is hinged to the other end of the wrench shaft 7.

[0052] The handle 13 is hinged to the other end of the connecting rod 3, and has a strip-shaped hole.

[0053] The supporting block 14 is connected to the support plate 1.

[0054] The roller 15 is arranged in the strip-shaped hole and connected to the supporting block 14.

[0055] For the nut dismounting structure in the cavity of the aero-engine rotor shaft neck disc disclosed in the above embodiment, those skilled in the art can understand that the nut dismounting structure can realize the dismounting of the nut in the cavity of the aero-engine rotor shaft neck disc by stretching and retracting the hydraulic rod of the hydraulic cylinder 11, driving the wrench shaft 7 to stretch and retract through the transmission arm, rotating the wrench shaft 7 while stretching and retracting due to the threaded connection between the wrench shaft 7 and the support cylinder 6, and driving the wrench head 8 to screw the nut 10.

[0056] For the nut dismounting structure in the cavity of the aero-engine rotor shaft neck disc disclosed in the above embodiment, those skilled in the art can understand that when the hydraulic rod of the hydraulic cylinder 11 is stretched and retracted, the handle 13 can be pulled based on the lever principle to tighten the connecting rod 3, so that the wrench hole is kept clamped on the nut 10 connected to the end of the rotor shaft neck 4 and the connecting edge of the drum 9, avoiding disconnection. In this process, the roller 15 can roll in the strip-shaped hole to avoid jamming.

[0057] In some optional embodiments, the support plate 1 in the nut dismounting structure in the cavity of the aero-engine rotor shaft neck disc is connected through the bolt hole on the connecting edge of the stator case 2 by the bolt, without damaging the existing structure of the stator case 2.

[0058] In some optional embodiments, the support plate 1 in the nut dismounting structure in the cavity of the aero-engine rotor shaft neck disc is connected to the screw rod of the rotor part at the front end of the rotor shaft neck 4 through the bolt and the screw sleeve, without damaging the existing structure of the rotor part, and the position of the nut 10 connected to the end of the rotor shaft neck 4 and the connecting edge of the drum 9 is fixed relative to the rotor part at the front end of the rotor shaft neck 4. Connecting the support plate 1 to the rotor part at the front end of the rotor shaft neck 4 can ensure the positioning of the wrench head 8 and the nut 10 in the radial direction.

[0059] In some alternative embodiments of the above-mentioned aviation engine rotor shaft neck disc cavity inner nut dismounting structure, the through hole is a special-shaped hole, and the cross-sectional shape of the connecting rod 3 matched with the special-shaped hole is also special-shaped, which can be square, oval, flat, etc., so as to effectively constrain the rotation of the connecting rod 3 when the nut 10 in the aviation engine rotor shaft neck disc cavity is screwed, and effectively transmit the torque generated by screwing the nut 10 to the stator casing 2 for bearing.

[0060] In some alternative embodiments of the above-mentioned aviation engine rotor shaft neck disc cavity inner nut dismounting structure, the support 5 comprises:

[0061] The upper wall plate is connected to one end of the connecting rod 3 extending into the rotor shaft neck 4 disc cavity and is centered matched;

[0062] The lower wall plate is connected with the upper wall plate, and the space is formed between the upper wall plate and the lower wall plate. The transmission arm 12 is located in the space.

[0063] In some alternative embodiments of the above-mentioned aviation engine rotor shaft neck disc cavity inner nut dismounting structure, the support cylinder 6 is connected to the support 5 by a flange plate through a bolt.

[0064] In some alternative embodiments of the above-mentioned aviation engine rotor shaft neck disc cavity inner nut dismounting structure, the support cylinder 6 and its corresponding wrench shaft 7, wrench head 8, hydraulic cylinder 11, and transmission arm 12 have multiple groups, and the specific number and distribution position thereof can be determined according to the actual number of the connecting rotor shaft neck 4 end, drum 9 connecting edge nut 10, so as to realize the synchronous dismounting of multiple nuts in the aviation engine rotor shaft neck disc cavity, avoid uneven stress, and avoid the situation of large local deformation.

[0065] In some alternative embodiments of the above-mentioned aviation engine rotor shaft neck disc cavity inner nut dismounting structure, the handle 13 has a slot, and the side walls on both sides of the slot have a strip-shaped hole.

[0066] Each end of the roller 15 corresponds to a strip-shaped hole, so as to form stable support for the handle 13.

[0067] In some alternative embodiments of the above-mentioned aviation engine rotor shaft neck disc cavity inner nut dismounting structure, the support block 14 has two, which are located between the slots.

[0068] In some alternative embodiments of the above-mentioned aviation engine rotor shaft neck disc cavity inner nut dismounting structure, further comprising:

[0069] The hinge shaft 16 is hinged between one end of the connecting rod 3 away from the support 5 and the side walls of the slot.

[0070] The nut dismounting structure of the aero-engine rotor journal disc cavity disclosed in the above embodiments can be applied by referring to the following steps:

[0071] The support 5 is dismounted from the connecting rod 3, and the support cylinder 6 is dismounted from the support 5 together with the wrench shaft 7, the wrench head 8, the hydraulic cylinder 11 and the transmission arm 12;

[0072] The connecting rod 3 is inserted into the rotor journal 4 disc cavity, and the connecting plate 1 is connected with the stator casing 2 and the rotor journal 4 front end rotor component;

[0073] The support 5 is connected to the connecting rod 3, and the wrench hole is aligned with the nut 10 connected to the rotor journal 4 end and the drum cylinder 9 connecting edge;

[0074] The handle 13 pulls the connecting rod 3, and the wrench hole is clamped on the nut 10 connected to the rotor journal 4 end and the drum cylinder 9 connecting edge;

[0075] The extension and retraction of the hydraulic rod of the hydraulic cylinder 11 is controlled, the nut 10 is screwed, and the dismounting of the aero-engine rotor journal disc cavity nut is realized.

[0076] The 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 embodiments can be referred to each other.

[0077] The technical solution of the present 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 present application is obviously not limited to these specific embodiments. Without deviating from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the related technical features, and the technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. An aviation engine rotor journal disc cavity nut dismounting structure, characterized in that, It comprises: a support plate (1) connected to the stator case (2) and having a through hole; a connecting rod (3) passing through the through hole and extending into the disc cavity of the rotor journal (4); a support base (5) connected to one end of the connecting rod (3) extending into the disc cavity of the rotor journal (4); a support cylinder (6) connected to the support base (5); a wrench shaft (7) passing through the support cylinder (6) and connected to the support cylinder (6) through a threaded connection; a wrench head (8) connected to one end of the wrench shaft (7) and having a wrench hole; a hydraulic cylinder (11) connected to the support cylinder (6); a transmission arm (12) connected to the hydraulic rod of the hydraulic cylinder (11) and hinged to the other end of the wrench shaft (7); a handle (13) hinged to the other end of the connecting rod (3) and having a strip-shaped hole; a support block (14) connected to the support plate (1); a roller (15) arranged in the strip-shaped hole and connected to the support block (14); a hinge shaft (16); the support base (5) comprises: an upper wall plate connected to one end of the connecting rod (3) extending into the disc cavity of the rotor journal (4); a lower wall plate connected to the upper wall plate and forming a cavity therebetween, in which the transmission arm (12) is located; the handle (13) has a slot, and the side walls on both sides of the slot have strip-shaped holes; each end of the roller (15) corresponds to extend into one strip-shaped hole; the support block (14) has two and is located between the slot; the hinge shaft (16) is hinged between the side walls of the slot on the end of the connecting rod (3) away from the support base (5).

2. The aircraft engine rotor journal disc cavity nut dismounting structure according to claim 1, wherein the support plate (1) is connected to the stator case (2) through bolt holes on the connecting edge of the stator case (2) by bolts.

3. The aircraft engine rotor journal disc cavity nut dismounting structure according to claim 1, wherein the support plate (1) is connected to the screw rod of the rotor part at the front end of the rotor journal (4) by a screw sleeve through bolts.

4. The aircraft engine rotor journal disc cavity nut dismounting structure according to claim 1, wherein the through hole is a special-shaped hole.

5. The aircraft engine rotor journal disc cavity nut dismounting structure according to claim 1, wherein the support cylinder (6) is connected to the support base (5) by a flange through bolts.

6. The aircraft engine rotor journal disc cavity nut dismounting structure according to claim 1, wherein the support cylinder (6) and its corresponding wrench shaft (7), wrench head (8), hydraulic cylinder (11), and transmission arm (12) have multiple groups.

Images