A driving connection structure for the assembly of the rotating and stationary components of an aeroengine core

Abstract

This application belongs to the technical field of on-line balancing of rotor components of aero-engine core engines, and specifically relates to a drive connection structure for the assembly of rotating and stationary components of an aero-engine core engine, including: a hollow shaft with a plurality of communication grooves thereon; each is distributed circumferentially along the hollow shaft and extends axially along the hollow shaft; a support ring sleeved on the hollow shaft; a plurality of support blocks, one end of which has a support protrusion; each support protrusion correspondingly passes through a communication groove and extends into the hollow shaft; a plurality of support sheets, each support sheet is correspondingly connected between a support block and the support ring; each support protrusion is subjected to a force along the axial direction of the hollow shaft in the hollow shaft, and can drive each support block to contract inwards against the elastic force of the corresponding support sheet. After the force along the axial direction of the hollow shaft is eliminated, each support block can expand outwards under the action of the elastic force of the corresponding support sheet.

Description

Technical Field

[0001] This application belongs to the technical field of on-line balancing of rotor components of an aero-engine core, and particularly relates to a driving connection structure for assembling and installing the rotating and static components of an aero-engine core. Background Art

[0002] The rotor components of an aero-engine core mainly include a high-pressure compressor and a high-pressure turbine, which need to be balanced before installation. Currently, for the balance of the rotor components of an aero-engine core, the following methods are mostly used:

[0003] Balance the high-pressure compressor and the high-pressure turbine separately;

[0004] Balance the combination of the high-pressure compressor and the high-pressure turbine.

[0005] After the balance of the rotor components of the aero-engine core is completed, the combination of the high-pressure compressor and the high-pressure turbine needs to be disassembled again before it can be assembled with the static components of the aero-engine core. During assembly, repeated assembly errors will inevitably be introduced, making it difficult to ensure the balance after assembly with the static components. Moreover, its unbalance amount, in the case of assembling the static components, is difficult to measure and adjust relying on the existing technology. Only after the aero-engine is installed and during bench testing can it be measured, and the adjustment can be carried out using the method of on-board balancing. It is easy to occur the situation that the vibration of the rotor components exceeds the limit, and it is necessary to conduct multiple bench tests to determine the unbalance amount of the rotor components, and the aero-engine needs to be disassembled multiple times to complete the adjustment of the balance of the rotor components. The process is cumbersome, time-consuming and laborious.

[0006] In addition, currently, when balancing the combination of the high-pressure compressor and the high-pressure turbine, a balance shaft sleeve is sleeved on the front journal of the high-pressure compressor, and a balancing machine is connected to drive the combination of the high-pressure compressor and the high-pressure turbine. The front support point of the rotor component is supported on the balancing machine through the balance shaft sleeve, as Figure 1 shown. In reality, the front support point of the rotor component is supported on the static component through a third support bearing sleeved on the front journal of the high-pressure compressor. There is a deviation between the front support point when balancing the combination of the high-pressure compressor and the high-pressure turbine and the position of the actual front support point. The existence of this deviation makes it difficult to ensure the balance after the assembly of the rotor components and the static components of the aero-engine core.

[0007] To overcome the defects of the above methods for balancing the rotor components of an aero-engine core, an on-line balancing structure for the rotor components of an aero-engine core is designed, as Figure 2 shown, including:

[0008] The rotor component 1, which is a combination of a high-pressure compressor and a high-pressure turbine;

[0009] The stator component 2 is assembled with the rotor component 1, where the casing is a split casing;

[0010] The semi-circular simulation casing 3 replaces half of the split casing for assembly, and it has a high-pressure compressor balance adjustment window thereon;

[0011] The front process support casing 4 is butted against the front end of the stator component 2, and its side wall has a front ring process support edge;

[0012] The rear process support casing 5 is butted against the rear end of the stator component 2, and it has a rear ring process support edge and a rear ring support edge at the rear end of the high-pressure turbine, and its side wall has a high-pressure turbine balance adjustment window;

[0013] The rear support bearing 6 of the high-pressure turbine is sleeved on the rear ring support edge at the rear end of the high-pressure turbine and is supported between the rear ring support edge at the rear end of the high-pressure turbine and the high-pressure turbine rear end;

[0014] The drive shaft 7 has one end extending into the front journal of the high-pressure compressor for connection;

[0015] The universal coupling 8 is connected to the other end of the drive shaft 7.

[0016] In the above rotor component on-line balancing structure of the aero-engine core engine, to balance the rotor component of the aero-engine core engine, the following steps can be carried out:

[0017] Balance the high-pressure compressor and the high-pressure turbine respectively;

[0018] Assemble any one of the above rotor component on-line balancing structures of the aero-engine core engine;

[0019] Support the front ring process support edge and the rear ring process support edge on the balancing machine, connect the balancing machine to the universal coupling 8, drive the rotor component 1 to rotate, and measure the unbalance of the rotor component 1;

[0020] Adjust the unbalance of the high-pressure compressor through the high-pressure compressor balance adjustment window, and adjust the unbalance of the high-pressure turbine through the high-pressure turbine balance adjustment window.

[0021] After balancing the rotor component of the aero-engine core using the above-mentioned on-line balancing structure for the rotor component of the aero-engine core, the front process support casing 4, the rear process support casing 5, and the high-pressure turbine rear-end support bearing 6 can be removed, and the semi-circular simulation casing 3 can be removed and replaced with a split casing to achieve the assembly of the rotor and stator components of the aero-engine core. During this process, it is not necessary to disassemble the combination of the high-pressure compressor and the high-pressure turbine again and then assemble it with the stator components, which will not introduce repeated assembly errors and can ensure the balance of the rotor and stator components of the aero-engine core after assembly. Moreover, the balance of the rotor component of the aero-engine core is achieved on-line by adjusting the imbalance of the high-pressure compressor through the high-pressure compressor balance adjustment window and adjusting the imbalance of the high-pressure turbine through the high-pressure turbine balance adjustment window. After assembling with the stator components, it can be directly installed on the engine, with a simple process, which can greatly improve the installation efficiency and can greatly reduce the possibility of the rotor component vibration exceeding the limit during the aero-engine bench test.

[0022] In addition, the above-mentioned on-line balancing structure for the rotor component of the aero-engine core is carried out under the condition of assembling with the stator component, and the position of its front support point is restored to the actual situation, which can effectively ensure the balance of the rotor and stator components of the aero-engine core after assembly.

[0023] Since the on-line balancing structure for the rotor component of the aero-engine core designed is to balance the rotor component under the condition of assembling with the stator component, the front support point of the rotor component is supported on the front journal of the high-pressure compressor on the stator component through the third support bearing sleeved on the front journal of the high-pressure compressor, and it is no longer possible to sleeve a balance shaft sleeve on it to connect the balance machine for driving. Therefore, it is designed that one end of the drive shaft 7 extends into the front journal of the high-pressure compressor for connection, and the other end is connected to the balance machine through the universal coupling 8 for driving. However, there are significant differences in the inner diameter sizes of the front journals of the high-pressure compressors of the rotor components of different aero-engine cores. When using the designed on-line balancing structure for the rotor component of the aero-engine core to balance the rotor components of different aero-engine cores, it is necessary to replace the drive shaft 7 with a corresponding size to enable radial positioning, and the universality is poor.

[0024] In view of the existence of the above technical defects, this application is proposed.

[0025] It should be noted that the disclosure of the above background technical content is only for assisting in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background technology should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0026] The purpose of this application is to provide a drive connection structure for the assembly of the rotating and stationary components of an aeroengine core, so as to overcome or mitigate at least one aspect of the known technical deficiencies.

[0027] The technical solution of this application is as follows:

[0028] A drive connection structure for the assembly of the rotating and stationary components of an aeroengine core, comprising:

[0029] A hollow shaft, which has a plurality of communicating grooves; each communicating groove is distributed circumferentially along the hollow shaft and extends axially along the hollow shaft;

[0030] A support ring, sleeved on the hollow shaft;

[0031] A plurality of support blocks, one end of which has a support protrusion; each support protrusion correspondingly passes through a communicating groove and extends into the hollow shaft;

[0032] A plurality of support sheets, each support sheet is correspondingly connected between a support block and the support ring; when the support protrusions are subjected to a force along the axial direction of the hollow shaft inside the hollow shaft, they can drive the respective support blocks to contract inwards against the elastic force of the corresponding support sheets, and after the force along the axial direction of the hollow shaft is eliminated, the respective support blocks can expand outwards under the action of the elastic force of the corresponding support sheets.

[0033] According to at least one embodiment of this application, in the above drive connection structure for the assembly of the rotating and stationary components of an aeroengine core, one end of each communicating groove extends to the end of the hollow shaft.

[0034] According to at least one embodiment of this application, in the above drive connection structure for the assembly of the rotating and stationary components of an aeroengine core, the outer wall of the hollow shaft has support protrusions;

[0035] The support ring is connected to the support protrusions through a plurality of connecting bolts;

[0036] Each support block has an anti-bolt connection interference hole at the position corresponding to each connecting bolt.

[0037] According to at least one embodiment of this application, in the above drive connection structure for the assembly of the rotating and stationary components of an aeroengine core, there are two groups of the support ring and its corresponding support blocks, support sheets, and communicating grooves, which are distributed at both ends of the hollow shaft.

[0038] According to at least one embodiment of this application, in the above drive connection structure for the assembly of the rotating and stationary components of an aeroengine core, it further comprises:

[0039] A stop cylinder, one end of which is connected to one end of the hollow shaft, and the outer wall has an annular stop protrusion.

[0040] According to at least one embodiment of the present application, in the driving connection structure assembled with the rotating and stationary components of the aero-engine core engine, it further includes:

[0041] A transmission end cover, connected to one end of the stop cylinder facing away from the hollow shaft, and having a transmission hole thereon;

[0042] A universal coupling, with one end extending into the transmission hole.

[0043] According to at least one embodiment of the present application, in the driving connection structure assembled with the rotating and stationary components of the aero-engine core engine, it further includes:

[0044] A housing, connected to one end of the hollow shaft, and having a plurality of stop holes thereon; each stop hole is circumferentially distributed along the hollow shaft;

[0045] A plurality of stop pins, with one end of each stop pin correspondingly passing through a stop hole and extending into the housing, and having a stop protrusion at this end;

[0046] A plurality of stop springs, arranged inside the housing; each stop spring is correspondingly sleeved on a stop pin and connected between the corresponding stop protrusion and the housing, and relies on its elastic force to make the corresponding stop pin retract inward;

[0047] A camshaft, with one end extending into the housing, and having a plurality of cams on the outer wall of this end; when the camshaft rotates, it can correspondingly press against each cam and the end of each stop pin extending into the housing, so that each stop pin overcomes the elastic force of the corresponding stop spring and extends outward.

[0048] According to at least one embodiment of the present application, in the driving connection structure assembled with the rotating and stationary components of the aero-engine core engine, it further includes:

[0049] A plurality of guide seats, connected inside the housing, and having guide grooves and guide holes communicating with their guide grooves; one end of each stop pin extending into the housing correspondingly passes through a guide groove and extends out from the corresponding guide hole, and the corresponding stop protrusion and stop spring are located in the corresponding guide groove.

[0050] According to at least one embodiment of the present application, on the outer wall of the camshaft, there is a limit groove, and the limit groove extends circumferentially along the camshaft;

[0051] The driving connection structure assembled with the rotating and stationary components of the aero-engine core engine further includes:

[0052] A limit pin, connected to the housing and extending into the limit groove;

[0053] When the camshaft rotates to make the limit pin abut against the side wall at one end of the limit groove, the tops of each cam deviate towards this end of the limit groove from the corresponding stop pin, so that the corresponding stop pin remains extended outward;

[0054] When the camshaft rotates to make the limit pin abut against the side wall at the other end of the limit groove, the tops of the respective cams deviate from the corresponding stop pins towards this end of the limit groove, and the corresponding stop pins remain retracted inward.

[0055] According to at least one embodiment of the present application, in the drive connection structure assembled with the rotating and static components of the aeroengine core, the outer wall of the camshaft extending into the housing has a protruding portion;

[0056] The drive connection structure assembled with the rotating and static components of the aeroengine core further includes:

[0057] A lock nut screwed onto the camshaft, having:

[0058] In the tightened state, it abuts against the housing and cooperates with the protruding portion to fix the camshaft to the housing;

[0059] In the loosened state, it is separated from the housing, and the camshaft can rotate. Description of the Drawings

[0060] Figure 1 is a schematic diagram of the existing balancing of the combination of the high-pressure compressor and the high-pressure turbine;

[0061] Figure 2 is a schematic diagram of the online balancing structure of the rotor components of the aeroengine core;

[0062] Figure 3 is a schematic diagram of the drive connection structure assembled with the rotating and static components of the aeroengine core provided by the embodiment of the present application;

[0063] Figure 4 is Figure 3 a partial view in the direction A of

[0064] Figure 5 is a schematic diagram of the support ring, support block and their support sheets provided by the embodiment of the present application;

[0065] Figure 6 is an application schematic diagram of the drive connection structure assembled with the rotating and static components of the aeroengine core provided by the embodiment of the present application;

[0066] Wherein:

[0067] 1 - Rotor component; 2 - Stator component; 3 - Semi-circular simulation casing; 4 - Front process support casing; 5 - Rear process support casing; 6 - High-pressure turbine rear-end support bearing; 7 - Drive shaft; 8 - Universal coupling; 9 - Hollow shaft; 10 - Support ring; 11 - Support block; 12 - Support sheet; 13 - Stop cylinder; 14 - Transmission end cover; 15 - Locking nut; 16 - Housing; 17 - Stop pin; 18 - Stop spring; 19 - Camshaft; 20 - Guide seat; 21 - Limit pin.

[0068] To better illustrate this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and cannot be construed as a limitation of this patent. Detailed implementation manners

[0069] To make the technical solutions and their advantages of this application clearer, the following will further clearly and completely describe the technical solutions of this application in conjunction with the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments and the technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0070] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the field to which this application belongs. The words indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application are only used to indicate relative directions or positional relationships, rather than implying that the device or component must have a specific orientation, 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. Therefore, it cannot be construed as a limitation of this application. The terms "first", "second", "third" and similar terms used in the description of this application are only for descriptive purposes to distinguish different components and cannot be understood as indicating or implying relative importance. The similar words such as "a", "an" or "the" used in the description of this application should not be understood as an absolute limitation of the quantity, but should be understood as having at least one. The similar words such as "including" or "comprising" used in the description of this application are intended to mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0071] In addition, it should be noted that unless otherwise clearly specified and defined, the similar terms such as "installed", "connected", and "linked" used in the description of this application should be understood in a broad sense. For example, the 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, and it can also be the communication inside two components. Those skilled in the art can understand its specific meaning in this application according to the specific situation.

[0072] The following will further elaborate on this application in conjunction with the attached Figures 1 to 6 drawings.

[0073] A drive connection structure for the assembly of the rotating and stationary components of an aeroengine core includes:

[0074] A hollow shaft 9 with a plurality of communicating grooves; each communicating groove is distributed circumferentially along the hollow shaft and extends axially along the hollow shaft 9.

[0075] A support ring 10 sleeved on the hollow shaft 9.

[0076] A plurality of support blocks 11, which can be designed in a fan shape and have support protrusions on the inner side; each support protrusion correspondingly passes through a communicating groove and extends into the hollow shaft 9.

[0077] A plurality of support plates 12, each support plate 12 is correspondingly connected between a support block 11 and the support ring 10; when the support protrusions in the hollow shaft 9 are subjected to a force along the axial direction of the hollow shaft 9, they can drive each support block 11 to contract inward against the elastic force of the corresponding support plate 12. After the force along the axial direction of the hollow shaft 9 is eliminated, each support block 11 can expand outward under the elastic force of the corresponding support plate 12.

[0078] When balancing the rotor component of the aeroengine core, the above drive connection structure for the assembly of the rotating and stationary components of the aeroengine core can be used to replace the drive shaft 7 extending into the front journal of the high-pressure compressor in the online balancing structure of the rotor component of the aeroengine core. The specific operation can be referred to as follows:

[0079] Apply a force along the axial direction to each support protrusion in the hollow shaft 9 to make each support block 11 contract inward.

[0080] Insert one end of the hollow shaft 9 together with each support block 11 into the front journal of the high-pressure compressor.

[0081] Eliminate the force along the axial direction applied to each support protrusion in the hollow shaft 9 to make each support block 11 expand outward and adaptively tighten against the inner wall of the front journal of the high-pressure compressor, realizing the radial positioning of the hollow shaft 9 in the front journal of the high-pressure compressor and completing the connection.

[0082] Connect a balancing machine to the other end of the hollow shaft 9. Specifically, it can be connected to a driving motor to drive the rotation of the rotor component 1.

[0083] Regarding the driving connection structure for the assembly of the rotating and static components of the aero-engine core disclosed in the above embodiments, those skilled in the art can understand that it can radially position the hollow shaft 9 within the front journal of the high-pressure compressor by the respective support blocks 11 provided outside the hollow shaft 9 adaptively pressing against the front journal of the high-pressure compressor, and it can be applied to the connection of the front journal of the high-pressure compressor of different aero-engine core rotor components, having high versatility.

[0084] In some alternative embodiments, in the driving connection structure for the assembly of the rotating and static components of the aero-engine core described above, one end of each communication groove extends to the end of the hollow shaft 9. During assembly, the support protrusions on each support block 11 can be aligned with the corresponding communication grooves at this end and slid in axially, which is convenient and fast.

[0085] In some alternative embodiments, in the driving connection structure for the assembly of the rotating and static components of the aero-engine core described above, the outer wall of the hollow shaft 9 has support protrusions;

[0086] The support ring 10 is connected to the support protrusions by a plurality of connecting bolts, which is convenient for connection and can effectively support each support piece 12 and its support block 11;

[0087] Each support block 11 has anti-bolt connection interference holes corresponding to the respective connecting bolts. During assembly, a screwdriver can pass through each anti-bolt connection interference hole to tighten each connecting bolt to avoid interference.

[0088] In some alternative embodiments, in the driving connection structure for the assembly of the rotating and static components of the aero-engine core described above, there are two sets of the support ring 10 and its corresponding support blocks 11, support pieces 12, and communication grooves, which are distributed at both ends of the hollow shaft 9. One end of each set of communication grooves extends to the corresponding end of the hollow shaft 9, so that when it is applied to the connection of the front journal of the high-pressure compressor of the aero-engine core rotor component, two supports can be formed within the front journal of the high-pressure compressor, thereby ensuring the radial positioning effect of the hollow shaft 9 within the front journal of the high-pressure compressor.

[0089] In some alternative embodiments, in the driving connection structure for the assembly of the rotating and static components of the aero-engine core described above, it further includes:

[0090] The stop cylinder 13 is connected to the other end of the hollow shaft 9 at one end, and has an annular stop protrusion on its outer wall. When applied to the connection of the front journal of the high-pressure compressor of the aero-engine core engine rotor component, the other end of the hollow shaft 9 can extend forward into the front journal of the high-pressure compressor, and the annular stop protrusion abuts against the end face of the front journal of the high-pressure compressor to achieve axial positioning of the hollow shaft 9. The other end of the stop cylinder 13 can be connected to a balancing machine to drive the rotor component 1.

[0091] In some alternative embodiments, in the drive connection structure assembled with the aero-engine core engine rotor-stator component described above, it further includes:

[0092] The drive end cover 14 is connected to the end of the stop cylinder 13 facing away from the hollow shaft 9, and has a drive hole thereon;

[0093] The universal coupling 8 has one end extending into the drive hole and the other end can be connected to a balancing machine to drive the rotor component 1 of the aero-engine.

[0094] In some alternative embodiments, in the drive connection structure assembled with the aero-engine core engine rotor-stator component described above, it further includes:

[0095] The housing 16 is connected to one end of the hollow shaft 9, and has a plurality of stop holes thereon; each stop hole is circumferentially distributed along the hollow shaft 9;

[0096] A plurality of stop pins 17, one end of each stop pin 17 correspondingly passes through a stop hole and extends into the housing 16, and this end has a stop protrusion;

[0097] A plurality of stop springs 18 are arranged in the housing 16; each stop spring 18 is correspondingly sleeved on a stop pin 17 and is connected between the corresponding stop protrusion and the housing 16, and relies on its elastic force to make the corresponding stop pin 17 retract inwards;

[0098] The camshaft 19 has one end extending into the housing 16, and a plurality of cams are provided on the outer wall of this end; when the camshaft 19 rotates, it can correspondingly press against each cam and the end of each stop pin 17 extending into the housing 16, so that each stop pin 17 extends outwards against the elastic force of the corresponding stop spring 18.

[0099] For the drive connection structure assembled for the rotating and stationary components of the aero-engine core as disclosed in the above embodiments, those skilled in the art can understand that when it is applied to the connection of the front journal of the high-pressure compressor of the aero-engine core rotor component, one end of the hollow shaft 9 connecting the housing 16 can be inserted into the front journal of the high-pressure compressor. By rotating the camshaft 19, each stop pin 17 extends outward and correspondingly inserts into the anti-twist groove in the front journal of the high-pressure compressor, thereby achieving reliable circumferential positioning of the hollow shaft 9 and the front journal of the high-pressure compressor. After connecting the balancing machine, it can effectively drive the rotor component 1 to rotate. After completing the balancing of the rotor component 1, by rotating the camshaft 19, each stop pin 17 can be retracted inward, disengaging from the corresponding anti-twist groove, and disassembling from the front journal of the high-pressure compressor.

[0100] In some alternative embodiments, in the drive connection structure assembled for the rotating and stationary components of the aero-engine core as described above, it further includes:

[0101] A plurality of guide seats 20, connected inside the housing 16, having guide grooves and guide holes communicating with the guide grooves; one end of each stop pin 17 extending into the housing 16 correspondingly passes through a guide groove and extends out from the corresponding guide hole, and the corresponding stop protrusions and stop springs 18 are located in the corresponding guide grooves.

[0102] In some alternative embodiments, in the drive connection structure assembled for the rotating and stationary components of the aero-engine core as described above, the outer wall of the camshaft 19 has a limit groove, and the limit groove extends circumferentially along the camshaft 19;

[0103] The drive connection structure assembled for the rotating and stationary components of the aero-engine core further includes:

[0104] A limit pin 21, connected to the housing 16 and extending into the limit groove;

[0105] When the camshaft 19 rotates so that the limit pin 21 abuts against the side wall at one end of the limit groove, the tops of the respective cams deviate from the corresponding stop pins 17 towards this end of the limit groove, and the deviation angle can be 5° - 10°, so that the corresponding stop pins 17 remain extended outward and can be inserted into the corresponding anti-twist grooves in the front journal of the high-pressure compressor. At this time, the position of the camshaft 19 is locked and will not rotate back under the action of no external force, effectively ensuring that each stop pin 17 will not retract due to the rotation of the camshaft 19 and disengage from the corresponding anti-twist groove;

[0106] When the camshaft 19 rotates so that the limit pin 21 abuts against the side wall at the other end of the limit groove, the tops of the respective cams deviate from the corresponding stop pins 17 towards this end of the limit groove, and the corresponding stop pins 17 remain retracted inward and can disengage from the corresponding anti-twist grooves.

[0107] In some alternative embodiments, in the driving connection structure assembled with the rotating and stationary components of the aeroengine core engine, there are a plurality of limit pins 21 and their corresponding limit slots, which are circumferentially distributed along the camshaft 19.

[0108] In some alternative embodiments, in the driving connection structure assembled with the rotating and stationary components of the aeroengine core engine, the outer wall of the camshaft 19 extending into the housing 16 has a protruding portion;

[0109] The driving connection structure assembled with the rotating and stationary components of the aeroengine core engine further includes:

[0110] A lock nut 15, screwed onto the camshaft 19, having:

[0111] In the tightened state, it abuts against the housing 16 and cooperates with the protruding portion to fix the camshaft 19 to the housing 16, suitable for the situation where each stop pin 17 extends outwards and is inserted into the corresponding anti-twist groove in the front journal of the high-pressure compressor of the aeroengine core engine, and the hollow shaft 9 is circumferentially positioned with the front journal of the high-pressure compressor;

[0112] In the loosened state, it is separated from the housing 16, and the camshaft 19 can rotate so that each stop pin 17 can extend outwards and be inserted into the corresponding anti-twist groove in the front journal of the high-pressure compressor of the aeroengine core engine, or retract inwards and disengage from the corresponding anti-twist groove.

[0113] The embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. The same or similar parts among the embodiments can be referred to each other.

[0114] So far, the technical solutions of the present application have been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle 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 all fall within the protection scope of the present application.

Claims

1. A driving connection structure for the assembly of a rotating and stationary component of an aeroengine core, characterized in that Comprising: A hollow shaft (9) having a plurality of connecting grooves thereon; each of the connecting grooves is circumferentially distributed along the hollow shaft and extends axially along the hollow shaft (9); A support ring (10) sleeved on the hollow shaft (9); A plurality of support blocks (11), one end of which has a support protrusion; each of the support protrusions correspondingly passes through one of the connecting grooves and extends into the hollow shaft (9); A plurality of support pieces (12), each of the support pieces (12) is correspondingly connected between one of the support blocks (11) and the support ring (10); when the support protrusions are subjected to a force along the axial direction of the hollow shaft (9) inside the hollow shaft (9), they can drive each of the support blocks (11) to contract inwards against the elastic force of the corresponding support piece (12), and after the force along the axial direction of the hollow shaft (9) is eliminated, each of the support blocks (11) can expand outwards under the action of the elastic force of the corresponding support piece (12); A housing (16) connected to one end of the hollow shaft (9) and having a plurality of stop holes thereon; each of the stop holes is circumferentially distributed along the hollow shaft (9); A plurality of stop pins (17), one end of each of the stop pins (17) correspondingly passes through one of the stop holes and extends into the housing (16), and this end has a stop protrusion; A plurality of stop springs (18) arranged inside the housing (16); each of the stop springs (18) is correspondingly sleeved on one of the stop pins (17) and is connected between the corresponding stop protrusion and the housing (16), and relies on its elastic force to retract the corresponding stop pin (17) inwards; A camshaft (19), one end of which extends into the housing (16), and the outer wall of this end has a plurality of cams; when the camshaft (19) rotates, it can correspondingly press against each of the cams and one end of each of the stop pins (17) extending into the housing (16), so that each of the stop pins (17) extends outwards against the elastic force of the corresponding stop spring (18); A stop cylinder (13), one end of which is connected to the other end of the hollow shaft (9), and the outer wall has an annular stop protrusion; A transmission end cover (14) connected to the end of the stop cylinder (13) facing away from the hollow shaft (9) and having a transmission hole thereon; A universal coupling (8), one end of which extends into the transmission hole and the other end is connected to a balancing machine to drive the rotor component (1) of the aero-engine.

2. The drive connection structure for assembling the rotating and static components of the core engine of an aero-engine according to claim 1, wherein One end of each of the connecting grooves extends to the end of the hollow shaft (9).

3. The drive connection structure for assembling the rotating and static components of the core engine of an aero-engine according to claim 1, wherein The outer wall of the hollow shaft (9) has support protrusions; The support ring (10) is connected to the support protrusions through a plurality of connecting bolts; Each of the support blocks (11) has anti-bolt connection interference holes at positions corresponding to the connecting bolts.

4. The drive connection structure for assembling the rotating and static components of the core engine of an aero-engine according to claim 1, wherein The said support ring (10) and its corresponding support blocks (11), support sheets (12), and communication grooves are in two groups and are distributed at both ends of the hollow shaft (9).

5. The drive connection structure for assembling the rotating and static components of the aero-engine core engine according to claim 1, characterized in that further comprising: a plurality of guide seats (20) connected inside the housing (16), having guide grooves and guide holes communicating with the guide grooves; one end of each of the said stop pins (17) extending into the housing (16) correspondingly passes through one of the said guide grooves and extends out from the corresponding guide hole, and the corresponding stop protrusions and stop springs (18) are located in the corresponding guide grooves.

6. The drive connection structure for assembling the rotating and static components of the aero-engine core engine according to claim 1, characterized in that the outer wall of the camshaft (19) has a limit groove which extends circumferentially along the camshaft (19); the drive connection structure for assembling the rotating and static components of the aero-engine core engine further comprises: a limit pin (21) connected to the housing (16) and extending into the limit groove; when the camshaft (19) rotates to make the limit pin (21) abut against the side wall at one end of the limit groove, the tops of the respective cams deviate towards this end of the limit groove from the corresponding stop pins (17), so that the corresponding stop pins (17) remain extended outwards; when the camshaft (19) rotates to make the limit pin (21) abut against the side wall at the other end of the limit groove, the tops of the respective cams deviate towards this end of the limit groove from the corresponding stop pins (17), and the corresponding stop pins (17) remain retracted inwards.

7. The drive connection structure for assembling the rotating and static components of the aero-engine core engine according to claim 1, characterized in that the outer wall of the camshaft (19) extending into the housing (16) has a protruding part; the drive connection structure for assembling the rotating and static components of the aero-engine core engine further comprises: a lock nut (15) screwed onto the camshaft (19), having: in the tightened state, pressing against the housing (16) and cooperating with the protruding part to fix the camshaft (19) to the housing (16); in the loosened state, separated from the housing (16), and the camshaft (19) can rotate.

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