CN114810219A - Aircraft engine - Google Patents

Abstract

The invention relates to an aero-engine. The aero-engine comprises: a drum, which is provided with a tenon and groove extending along its circumferential direction; a blade includes a tenon matched with the tenon and groove; a locking block assembly is fixedly installed in the tenon and groove and is Abutting with the blade to limit the movement of the blade along the tongue and groove, the locking block assembly includes a locking block (10) provided in the tongue and groove and an elastic member (10) configured to make the locking block (10) abut against the inner surface of the tongue groove ( 40), the elastic component (40) pushes the locking block (10) against the inner surface of the tongue and groove, which improves the problem that the locking structure is easy to fail in the related art.

Description

Aircraft engine

technical field

The present invention relates to the field of aviation equipment, in particular, to an aeroengine.

Background technique

1 to 4 , the aero-engine includes a drum 2 and a plurality of blades 1 arranged along the circumference of the drum 2 . FIG. 1 shows a schematic structural diagram of a typical meridian projection surface of the drum. Among them, the commonly used drum 2 and the blade 1 are connected by tenon, the peripheral surface of the drum 2 is provided with a dovetail type tenon and groove, the tenon and groove extend along the circumferential direction of the drum 2, and the root of the blade 1 is provided with a tongue and groove suitable for the tenon and groove. With the matching tenon, the width of the opening at the radially outer end of the tenon groove is smaller than the width of the inside of the tenon groove, so as to restrict the movement of the blade 1 toward the outside in the radial direction. The tongue groove on the drum 2 is provided with an insertion opening, and the tenon of the rotor blade 1 is inserted through the insertion opening and then moves to a predetermined installation position in the tongue groove in the circumferential direction. The aero-engine also includes a locking block assembly 3 that restricts the circumferential movement of the blade in the tongue and groove, and the locking block assembly is fixedly installed in the tongue and groove to confine the rotor blade 1 in the installation position.

FIGS. 5 and 6 are schematic structural diagrams of a locking block assembly 3 . The locking block assembly 3 includes a locking block 4 , a locking screw 5 and a self-locking wire sleeve 6 .

FIG. 7 and FIG. 8 show a schematic structural diagram of another locking block assembly; FIGS. 9 to 12 show a schematic structural diagram of the locking block of the locking block assembly 3 . The locking block assembly 3 includes a locking block 4 and a locking screw 5 . The locking block 4 includes a mating surface 41 and a working surface 42 . The locking screw 5 has an external thread 51 and a wrench fitting structure 52 located at the end of the locking screw 5 , and the wrench fitting structure 52 may be a multi-deformation hole. The locking block 4 has a threaded hole adapted to the locking screw 5, and the threaded hole extends along the radial direction of the aero-engine. During the process of turning the locking screw 5 by a wrench, the locking block 4 is driven by the locking screw. It moves radially outward so that the working surface and/or the mating surface of the locking block 4 abuts against the inner surface of the tongue groove, thus fixing the locking block 4 in the tongue groove.

The locking block assembly works as follows:

1. The working surface 42 of the locking block cooperates with the tenon and groove of the drum 2 to bear the centrifugal force load;

2. Assemble the locking screw 5 through the installation groove structure, and the outer thread of the locking screw 5 and the inner thread of the locking block 4 cooperate to raise the locking block 4 radially, so that the two ends of the locking block 4 are matched with the drum 2. The working groove is matched to realize the circumferential positioning;

3. Under the action of the two locking blocks 4 components, the rotor blades are fixed in the circumferential direction and cannot fall off from the drum to ensure safe work.

In order to prevent the locking screw 5 from loosening or falling off during the working process, causing the rotor blades to fly out, injuring other blades, reducing the efficiency of the engine, and failing to work normally, the connection of the locking screw 5 must be reliable. In the first structural form, the locking screw 5 is prevented from loosening or falling off by the self-locking torque of the self-locking screw sleeve 6; Dead provides self-locking torque to meet the requirements.

The above-mentioned structural form for preventing the locking screw from falling off mainly has the following defects:

1. The self-locking torque of the first structural form is easy to fail and the reliability is low;

2. In the second structural form, the assembly is complicated and the locking block is easily damaged by the way of deformation and punching of the locking block;

3. During the assembly process of the two structural forms, due to the large self-locking torque, the locking screw installation groove is easily damaged when tightened, the assembly time increases, and the cost increases;

4. Assembly and replacement are more difficult, and maintenance and repair costs increase.

SUMMARY OF THE INVENTION

The present invention aims to provide an aero-engine to improve the problem in the related art that the locking structure for limiting the circumferential movement of the blade along the tongue and groove is prone to failure.

According to an aspect of the embodiments of the present invention, an aero-engine is provided, and the aero-engine includes:

The drum is provided with a tongue and groove extending along its circumferential direction;

a blade, including a tenon that fits into a tenon and groove;

The locking block assembly is fixedly installed in the tongue groove and abuts with the blade to limit the movement of the blade along the tongue groove, the locking block assembly includes a locking block arranged in the tongue groove and a locking block configured to make the locking block abut against the tongue groove. Resilient components on the inner surface.

In some embodiments, the aero-engine further includes a rod-shaped member, the locking block is provided with a mounting hole adapted to the rod-shaped member, the first end of the rod-shaped member is inserted into the mounting hole, and the elastic member is configured to attach the rod-shaped member to the mounting hole. The component is pressed toward the outside of the locking block, and the second end of the rod-shaped component is in contact with the bottom wall of the tongue groove.

In some embodiments,

a second end of the rod-shaped member located outside the mounting hole is provided with a flange;

The installation hole includes a first installation hole and a second installation hole with an inner diameter smaller than the first installation hole, and a transition step surface is formed at the junction of the first installation hole and the second installation hole;

One end of the elastic member is in contact with the transition step surface, and the other end is in contact with the flange.

In some embodiments, the aero-engine further includes a limiting member for limiting the distance that the rod-shaped member moves toward the inside of the mounting hole.

In some embodiments, the stop member includes a spring collar.

In some embodiments, the mounting hole is a through hole, and the first part of the rod-shaped member is provided with a tool connecting portion, so as to move the rod-shaped member into the mounting hole when the locking block is installed in the tongue groove.

In some embodiments, the tool attachment portion includes a threaded hole provided at the first end of the rod-shaped member.

In some embodiments, the tongue and groove comprises a tongue and groove body, the outer end of the tongue and groove body along the radial direction of the drum is open, and the width of the opening of the tongue and groove is smaller than the width of at least a part of the inner cavity of the tongue and groove, so as to The limiting vanes are radially out of the tongue and groove.

In some embodiments, the tongue and groove further includes an insertion opening communicated with the tongue and groove body, and the width of the insertion opening is not less than the maximum width of the tenon.

By applying the technical solution of the present invention, the elastic component pushes the locking block against the inner surface of the tongue groove, which improves the problem that the locking structure is easy to fail in the related art.

Other features and advantages of the present invention will become apparent from the following detailed description of exemplary embodiments of the present invention with reference to the accompanying drawings.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the following briefly introduces the accompanying drawings used in the description of the embodiments or related technologies. Obviously, the drawings in the following description are only the For some embodiments of the invention, for those of ordinary skill in the art, other drawings can also be obtained from these drawings without any creative effort.

FIG. 1 shows a schematic structural diagram of a drum and a blade of an aero-engine of the related art; and

Fig. 2 shows the side view structure schematic diagram of Fig. 1;

Fig. 3 shows the partial enlarged view of E in Fig. 1;

Fig. 4 shows the schematic cross-sectional structure at C-C in Fig. 2;

Fig. 5 shows the structural schematic diagram of the first locking block assembly of the aero-engine of the related art;

Fig. 6 shows the cross-sectional structure schematic diagram at A-A in Fig. 5;

FIG. 7 shows a schematic structural diagram of a second locking block assembly of an aero-engine of the related art;

Fig. 8 shows the schematic diagram of the cross-sectional structure at B-B in Fig. 7;

FIG. 9 shows a schematic structural diagram of a locking block of a second locking block assembly of an aero-engine of the related art;

Figure 10 shows a schematic diagram of the cross-sectional structure at D-D in Figure 9;

FIG. 11 shows a schematic structural diagram of the locking block of the second locking block assembly of the related art aero-engine;

Fig. 12 shows the schematic cross-sectional structure at E-E in Fig. 11;

13 shows a schematic structural diagram of a locking block assembly of an aero-engine according to an embodiment of the present invention;

Figure 14 shows a schematic diagram of the cross-sectional structure at F-F in Figure 11;

15 shows a schematic structural diagram of a locking screw of a locking block assembly of an aero-engine according to an embodiment of the present invention;

Fig. 16 shows a schematic cross-sectional structure diagram of the locking screw shown in Fig. 15;

FIG. 17 shows a schematic structural diagram of a locking block assembly (unassembled) of an aero-engine according to an embodiment of the present invention; and

FIG. 18 shows a schematic diagram of the cross-sectional structure at H-H in FIG. 17 .

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

The aero-engine of this embodiment includes a drum and a blade, the drum is provided with a tongue and groove extending along the circumferential direction thereof; the blade includes a tenon matched with the tongue and groove;

The tongue and groove includes a tongue and groove body, and the outer end of the tongue and groove body along the radial direction of the drum is open, and the width of the opening of the tongue and groove is smaller than the width of at least a part of the inner cavity of the tongue and groove, so as to limit the radial separation of the blade tongue and groove.

In some embodiments, the tongue and groove are dovetail grooves. In other embodiments, the cross-section of the tongue and groove is substantially triangular, and the apex angle of the triangle is farther from the axis of the drum than the bottom edge opposite to the apex angle.

The tongue-and-groove includes a tongue-and-groove body and an insertion port communicated with the tongue-and-groove body, and the width of the insertion hole is not less than the maximum width of the tenon. When installing the blade on the drum, firstly insert the tenon of the blade into the tenon groove through the above-mentioned insertion port, and then move the tenon of the blade in the tenon groove along the circumferential direction of the drum, so as to move the blade to a predetermined position installation location.

The aero-engine also includes a locking block assembly configured to limit circumferential movement of the blade in the tongue and groove along the drum, the locking block assembly is fixedly mounted in the tongue and groove and abuts the blade to limit movement of the blade along the tongue and groove.

As shown in Figures 13 and 14, the locking block assembly includes a locking block 10 disposed in a tongue and groove and an elastic member 40 configured to abut the locking block 10 against the inner surface of the tongue and groove.

The aero-engine further includes a rod-shaped member 20, the locking block 10 is provided with a mounting hole adapted to the rod-shaped member 20, the first end of the rod-shaped member 20 is inserted into the mounting hole, and the elastic member 40 is configured to attach the rod-shaped member 20 is pushed toward the outside of the locking block 10, and the second end of the rod-shaped member 20 is in contact with the bottom wall of the tongue groove.

14 to 18, the second end of the rod-shaped member 20 located outside the mounting hole is provided with a flange 60; the mounting hole includes a first mounting hole and a second mounting hole with an inner diameter smaller than the first mounting hole, the first mounting hole A transition step surface is formed at the junction of the installation hole and the second installation hole; one end of the elastic member 40 is in contact with the transition step surface, and the other end is in contact with the flange 60 . In this embodiment, the elastic member 40 is a spring sleeved on the rod-shaped member 20 .

The aero-engine further includes a limiting member 30 for limiting the distance that the rod-shaped member 20 moves to the inside of the mounting hole.

In some embodiments, the stop member 30 includes a spring collar.

The installation hole is a through hole, and the first end of the rod-shaped member 20 is provided with a tool connecting portion 50 to move the rod-shaped member 20 into the installation hole when the locking block 10 is installed in the tongue groove.

In some embodiments, the tool attachment portion 50 includes a threaded hole provided at the first end of the rod-like member 20 .

In this embodiment, the locking block assembly includes a locking block 10 , a rod-shaped member 20 , an elastic member 40 and a limiting member 30 . As shown in FIGS. 15 and 16 , the first end of the rod-shaped member 20 has an internal thread structure to form the tool connecting portion 50 , and the first end of the rod-shaped member 20 has no external thread structure.

The assembly process of this patented structure:

1. Before assembly, remove the spring clip (limiting part 30), use the tool to cooperate with the inner thread of the rod-shaped rod-shaped part 20, lift the rod-shaped part upward, and the spring is in a compressed state, as shown in Figure 18;

2. After completing the assembly of the locking block assembly and the drum, remove the tooling, assemble the spring clip, and complete the assembly of the assembly.

The working principle of this patent is as follows:

1. During the assembly process, the radial distance between the rod-shaped component and the locking block is reduced by compressing the spring, and the locking block assembly moves in the drum to realize assembly;

2. In the working state, the spring is in a compressed state, providing radial force to make the locking block fit closely with the drum, and the spring collar further restricts the radial displacement of the rod-shaped component to ensure normal operation and achieve the circumferential positioning requirements of the rotor blades.

The invented blade locking block assembly has the advantages of simple structure and device, easy installation and high reliability, and can well meet the structural assembly and positioning requirements. Its main feature is the spring and spring collar design. The embodiment of this patent is a specific case of the structure of the locking block assembly, and the structure and quantity of the springs, the spring collar and the structural form of the locking block shall all be within the protection scope of this patent.

The locking block assembly of this embodiment has the following technical effects:

This embodiment provides a novel rotor blade locking block assembly, which has the following beneficial effects:

1. The structure is simple, the failure rate of the locking block assembly is reduced, and the reliability of the engine is improved;

2. Easy to assemble, save assembly time and reduce assembly cost;

3. The locking block and rod-shaped parts are not easy to be damaged, and the maintenance and repair costs are low.

The above are only exemplary embodiments of the present invention, and are not intended to limit the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention. Inside.

Claims (9)

1. An aircraft engine, comprising:

a drum provided with a tongue-and-groove extending in a circumferential direction thereof;

the blade comprises a tenon matched with the mortise;

the locking block assembly is fixedly installed in the mortise and abutted to the blade to limit the blade to move along the mortise, and comprises a locking block (10) arranged in the mortise and an elastic component (40) configured to enable the locking block (10) to abut against the inner surface of the mortise.

2. An aircraft engine according to claim 1, characterised in that it further comprises a rod-shaped part (20), the locking block (10) being provided with a mounting hole adapted to the rod-shaped part (20), into which mounting hole a first end of the rod-shaped part (20) is inserted, the elastic part (40) being configured to push the rod-shaped part (20) towards the outside of the locking block (10), a second end of the rod-shaped part (20) abutting against the bottom wall of the mortise.

3. The aircraft engine of claim 2,

a second end of the rod-shaped member (20) located outside the mounting hole is provided with a flange (60);

the mounting holes comprise a first mounting hole and a second mounting hole with the inner diameter smaller than that of the first mounting hole, and a transition step surface is formed at the junction of the first mounting hole and the second mounting hole;

one end of the elastic component (40) is abutted against the transition step surface, and the other end of the elastic component is abutted against the flange (60).

4. An aircraft engine according to claim 2, further comprising a limiting member (30) for limiting the distance of movement of the rod-like member (20) towards the inside of the mounting hole.

5. An aircraft engine according to claim 4, characterised in that the stop means (30) comprise a spring collar.

6. An aircraft engine according to claim 4, characterised in that the mounting hole is a through hole and the first of the rod-shaped members (20) is provided with a tool attachment portion (50) to move the rod-shaped member (20) into the mounting hole when the locking block (10) is mounted in the mortise slot.

7. An aircraft engine according to claim 6, characterised in that the tool attachment portion (50) comprises a threaded hole provided at a first end of the rod-like member (20).

8. The aircraft engine of claim 1, wherein said tongue and groove includes a tongue and groove body, an outer end of said tongue and groove body in a radial direction of said drum being open, a width of said tongue and groove opening being less than a width of at least a portion of said tongue and groove internal cavity to limit radial escape of said blade from said tongue and groove.

9. The aircraft engine of claim 8 wherein said mortise slot further comprises an insert opening in communication with said mortise slot body, said insert opening having a width no less than a maximum width of said tenon.

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