Aircraft Engines

Abstract

The invention relates to an aircraft engine, comprising: a drum, provided with a tenon extending along its circumference; a blade, comprising a tenon matched with the tenon; a locking block assembly, fixedly installed in the tenon and abutting against the blade to limit the movement of the blade along the tenon, the locking block assembly comprising a locking block (10) arranged in the tenon and an elastic component (40) configured to make the locking block (10) abut against the inner surface of the tenon, the elastic component (40) pushes the locking block (10) to abut against the inner surface of the tenon, thereby improving the problem of easy failure of the locking structure existing in the related art.

Description

Technical Field

[0001] The present invention relates to the field of aviation equipment, and in particular to an aviation engine. Background Art

[0002] Combination Figures 1 to 4 As shown, the aircraft engine includes a drum 2 and a plurality of blades 1 arranged along the circumference of the drum 2. Figure 1 The schematic diagram of the structure of a typical meridional projection of a drum is shown. Among them, the commonly used drum 2 and the blade 1 are connected by a tenon, and a dovetail-shaped tenon groove is provided on the circumferential surface of the drum 2, and the tenon groove extends along the circumference of the drum 2. The root of the blade 1 is provided with a tenon matched with the tenon groove, and the width of the opening at the radial outer end of the tenon groove is smaller than the width inside the tenon groove to limit the blade 1 from moving radially outward. The tenon groove on the drum 2 is provided with an insertion port, and the tenon of the rotor blade 1 is inserted through the insertion port and moves circumferentially in the tenon groove to a predetermined installation position. The aircraft engine also includes a locking block assembly 3 for limiting the circumferential movement of the blade in the tenon groove, and the locking block assembly is fixedly installed in the tenon groove to limit the rotor blade 1 in the installation position.

[0003] Figure 5 and Figure 6 Figure 1 The structural diagram of a locking block assembly 3 is shown in FIG. 4 , wherein the locking block assembly 3 includes a locking block 4, a locking screw 5 and a self-locking thread sleeve 6.

[0004] Figure 7 and Figure 8 A structural schematic diagram of another locking block assembly is shown; Figures 9 to 12 The schematic diagram of the locking block structure of the locking block assembly 3 is shown. 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 mating structure 52 located at the end of the locking screw 5, and the wrench mating structure 52 can be a multi-deformed hole. The locking block 4 has a threaded hole adapted to the locking screw 5, and the threaded hole extends in the radial direction of the aircraft engine. In the process of rotating the locking screw 5 by a wrench, the locking block 4 moves radially outward under the drive of the locking screw, so that the working surface and / or mating surface of the locking block 4 abuts against the inner surface of the mortise, thereby fixing the locking block 4 in the mortise.

[0005] The locking block assembly works as follows:

[0006] 1. The working surface 42 of the locking block cooperates with the tenon groove of the drum 2 to bear the centrifugal force load;

[0007] 2. Assemble the locking screw 5 through the mounting groove structure. The outer thread of the locking screw 5 cooperates with the inner thread of the locking block 4 to radially raise the locking block 4, so that the mating surfaces at both ends of the locking block 4 cooperate with the working groove of the drum 2 to achieve circumferential positioning;

[0008] 3. Under the action of the two locking blocks 4 assemblies, the rotor blades are circumferentially positioned and fixed and cannot fall off from the drum, ensuring safe operation.

[0009] In order to prevent the locking screw 5 from loosening or falling off during operation, causing the rotor blades to fly out, damaging other blades, reducing engine efficiency, and failing to work normally, the locking screw 5 must be connected reliably. In the first structural form, the self-locking torque of the self-locking thread sleeve 6 is used to prevent the locking screw 5 from loosening or falling off; in the second structural form, the self-locking thread sleeve is not included, and the locking block 4 is deformed and punched during installation to provide a self-locking torque to meet the requirements.

[0010] The above-mentioned structural form for preventing the locking screw from falling off mainly has the following defects:

[0011] 1. The self-locking torque of the self-locking wire sleeve of the first structure is easy to fail and has low reliability;

[0012] 2. The second structural form uses the locking block to deform and punch, which is complicated to assemble and the locking block is easy to be damaged;

[0013] 3. During the assembly process of the two structural forms, due to the large self-locking torque, the locking screw installation slot is easily damaged when tightened, which increases the assembly time and cost;

[0014] 4. Assembly and replacement are difficult, and maintenance and repair costs increase. Summary of the invention

[0015] The present invention aims to provide an aircraft engine to improve the problem in the related art that a locking structure for limiting the circumferential movement of a blade along a tenon groove is prone to failure.

[0016] According to one aspect of an embodiment of the present invention, there is provided an aircraft engine, the aircraft engine comprising:

[0017] The drum is provided with a tenon groove extending along its circumference;

[0018] A blade including a tenon adapted to fit into the tenon groove;

[0019] The locking block assembly is fixedly installed in the tenon groove and abuts against the blade to limit the blade from moving along the tenon groove. The locking block assembly includes a locking block arranged in the tenon groove and an elastic component configured to make the locking block abut against the inner surface of the tenon groove.

[0020] In some embodiments, the aircraft engine also includes a rod-shaped component, the locking block is provided with a mounting hole adapted to the rod-shaped component, the first end of the rod-shaped component is inserted into the mounting hole, the elastic component is configured to push the rod-shaped component toward the outside of the locking block, and the second end of the rod-shaped component abuts against the bottom wall of the mortise.

[0021] In some embodiments,

[0022] The second end of the rod-shaped component located outside the mounting hole is provided with a flange;

[0023] The mounting hole comprises a first mounting hole and a second mounting hole with an 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;

[0024] One end of the elastic component abuts against the transition step surface, and the other end abuts against the flange.

[0025] In some embodiments, the aircraft engine further includes a limiting component for limiting a distance that the rod-shaped component moves toward the inside of the mounting hole.

[0026] In some embodiments, the limiting component includes a spring collar.

[0027] In some embodiments, the mounting hole is a through hole, and a first portion of the rod-shaped component is provided with a tool connection portion so as to move the rod-shaped component into the mounting hole when the locking block is installed in the tenon groove.

[0028] In some embodiments, the tool connection portion includes a threaded hole provided at the first end of the rod-shaped member.

[0029] In some embodiments, the mortise includes a mortise body, the radially outer end of the mortise body is open, and the width of the opening of the mortise is smaller than the width of at least a portion of the inner cavity of the mortise to limit the blade from radially disengaging from the mortise.

[0030] In some embodiments, the mortise and tenon further comprises an insertion opening communicated with the mortise and tenon body, and a width of the insertion opening is not less than a maximum width of the tenon.

[0031] By applying the technical solution of the present invention, the elastic component pushes the locking block to press against the inner surface of the tenon groove, thereby improving the problem of easy failure of the locking structure existing in the related art.

[0032] Further 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 attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the drawings required for use in the embodiments or related technical descriptions are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0034] Figure 1A schematic diagram showing the structure of a drum and blades of an aircraft engine of related art; and

[0035] Figure 2 Shows Figure 1 A side view structural schematic diagram of;

[0036] Figure 3 Shows Figure 1 The partial enlarged picture of E in the figure;

[0037] Figure 4 Shows Figure 2 Schematic diagram of the cross-sectional structure at CC in the middle;

[0038] Figure 5 A structural schematic diagram showing a first locking block assembly of an aircraft engine of the related art;

[0039] Figure 6 Shows Figure 5 Schematic diagram of the cross-sectional structure at AA in the middle;

[0040] Figure 7 A schematic structural diagram showing a second locking block assembly of an aircraft engine of the related art;

[0041] Figure 8 Shows Figure 7 Schematic diagram of the cross-sectional structure at BB in the middle;

[0042] Fig. 9 A schematic structural diagram of a locking block of a second locking block assembly of an aircraft engine in the related art is shown;

[0043] Fig.10 Shows Fig. 9 Schematic diagram of the cross-sectional structure at DD in the middle;

[0044] Fig.11 A schematic structural diagram of a locking block of a second locking block assembly of an aircraft engine in the related art is shown;

[0045] Fig.12 Shows Fig.11 Schematic diagram of the cross-sectional structure at EE in the middle;

[0046] Fig.13 A schematic structural diagram of a locking block assembly of an aircraft engine according to an embodiment of the present invention is shown;

[0047] Fig.14 Shows Fig.11 Schematic diagram of the cross-sectional structure at FF in the middle;

[0048] Fig.15 A schematic structural diagram showing a locking screw of a locking block assembly of an aircraft engine according to an embodiment of the present invention;

[0049] Fig.16 Shows Fig.15 A schematic diagram of the cross-sectional structure of the locking screw shown;

[0050] Fig.17 A schematic structural diagram showing a locking block assembly (not assembled) of an aircraft engine according to an embodiment of the present invention; and

[0051] Fig.18 Shows Fig.17 Schematic diagram of the cross-sectional structure at HH in the figure. DETAILED DESCRIPTION

[0052] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0053] The aircraft engine of this embodiment includes a drum and a blade, wherein the drum is provided with a tenon extending along its circumference; the blade includes a tenon matched with the tenon;

[0054] The tenon groove comprises a tenon groove body, the outer end of the tenon groove body along the radial direction of the drum is open, and the width of the opening of the tenon groove is smaller than the width of at least a part of the inner cavity of the tenon groove to limit the blade from radially escaping from the tenon groove.

[0055] In some embodiments, the mortise and tenon groove is a dovetail groove. In other embodiments, the cross section of the mortise and tenon groove is generally triangular, and the apex angle of the triangle is farther from the axis of the drum than the base opposite to the apex angle.

[0056] The tenon groove includes a tenon groove body and an insertion opening connected to the tenon groove body, and the width of the insertion opening is not less than the maximum width of the tenon. When installing the blade on the drum, the tenon of the blade is first inserted into the tenon groove through the insertion opening, and then the tenon of the blade is moved in the tenon groove along the circumference of the drum, so as to move the blade to a predetermined installation position.

[0057] The aircraft engine further comprises a locking block assembly configured to limit the blade from moving in the tenon groove along the circumferential direction of the drum, wherein the locking block assembly is fixedly installed in the tenon groove and abuts against the blade to limit the blade from moving along the tenon groove.

[0058] like Fig.13 and 14As shown, the locking block assembly includes a locking block 10 disposed in the tenon groove and an elastic component 40 configured to force the locking block 10 to press against the inner surface of the tenon groove.

[0059] The aircraft engine also includes a rod-shaped component 20, and the locking block 10 is provided with a mounting hole adapted to the rod-shaped component 20. The first end of the rod-shaped component 20 is inserted into the mounting hole, and the elastic component 40 is configured to push the rod-shaped component 20 toward the outside of the locking block 10, and the second end of the rod-shaped component 20 abuts against the bottom wall of the mortise.

[0060] Combination Figures 14 to 18 As shown, the second end of the rod-shaped component 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, 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 abuts against the transition step surface, and the other end abuts against the flange 60. In this embodiment, the elastic component 40 is a spring sleeved on the rod-shaped component 20.

[0061] The aircraft engine further includes a limiting component 30 for limiting the distance that the rod-shaped component 20 moves toward the inside of the mounting hole.

[0062] In some embodiments, the limiting component 30 includes a spring collar.

[0063] The mounting hole is a through hole, and a tool connecting portion 50 is provided at the first end of the rod-shaped component 20 so as to move the rod-shaped component 20 into the mounting hole when the locking block 10 is installed in the tenon groove.

[0064] In some embodiments, the tool connection portion 50 includes a threaded hole disposed at a first end of the rod-shaped component 20 .

[0065] In this embodiment, the locking block assembly includes a locking block 10 , a rod-shaped component 20 , an elastic component 40 and a limiting component 30 . Fig.15 and 16 As shown, the first end of the rod-shaped component 20 has an internal thread structure to form a tool connecting portion 50 , and the first end of the rod-shaped component 20 has no external thread structure.

[0066] The assembly process of this patented structure:

[0067] 1. Remove the spring collar (limiting component 30) before assembly, use a tool to cooperate with the internal thread of the rod-shaped rod-shaped component 20, lift the rod-shaped component upward, and the spring is in a compressed state, such as Fig.18 As shown;

[0068] 2. After completing the assembly of the locking block assembly and the drum, remove the tooling, assemble the spring retaining ring, and complete the assembly.

[0069] The working principle of this patent is as follows:

[0070] 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 achieve assembly;

[0071] 2. In the working state, the spring is in a compressed state, providing radial force to make the locking block fit tightly with the drum. The spring clamp further limits the radial displacement of the rod-shaped component to ensure normal operation and achieve the circumferential positioning requirements of the rotor blades.

[0072] The invented blade locking block assembly has a simple structure, is easy to install, has high reliability, and can well meet the requirements of structural assembly and positioning. Its main feature lies in the design of the spring and spring retaining ring. The implementation scheme of this patent is a specific example of the locking block assembly structure. The spring structure and quantity, spring retaining ring, and locking block structure should all be within the scope of protection of this patent.

[0073] The locking block assembly of this embodiment has the following technical effects:

[0074] This embodiment provides a novel rotor blade locking block assembly, which has the following beneficial effects:

[0075] 1. Simple structure, reduced failure rate of locking block assembly, improved engine reliability;

[0076] 2. Easy to assemble, saving assembly time and reducing assembly costs;

[0077] 3. The locking block and rod-shaped parts are not easy to be damaged, and the maintenance and repair costs are low.

[0078] The above are merely exemplary embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft engine, characterized in that: include: The drum is provided with a tenon groove extending along its circumference; The blade includes a tenon matched with the tenon groove; A locking block assembly is fixedly installed in the tenon groove and abuts against the blade to limit the blade from moving along the tenon groove. The locking block assembly comprises a locking block (10) arranged in the tenon groove and an elastic component (40) configured to make the locking block (10) abut against the inner surface of the tenon groove. The rod-shaped component (20) is provided with a mounting hole matched with the rod-shaped component (20), the first end of the rod-shaped component (20) is inserted into the mounting hole, the elastic component (40) is configured to push the rod-shaped component (20) toward the outside of the locking block (10), and the second end of the rod-shaped component (20) abuts against the bottom wall of the mortise. The elastic component (40) is a spring sleeved on the rod-shaped component (20).

2. The aircraft engine according to claim 1, characterized in that: A flange (60) is provided at the second end of the rod-shaped component (20) located outside the mounting hole; The mounting hole comprises a first mounting hole and a second mounting hole with an 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) abuts against the transition step surface, and the other end abuts against the flange (60).

3. The aircraft engine according to claim 1, characterized in that: It also includes a limiting component (30) for limiting the distance that the rod-shaped component (20) moves toward the inside of the mounting hole.

4. The aircraft engine according to claim 3, characterized in that: The limiting component (30) comprises a spring collar.

5. The aircraft engine according to claim 3, characterized in that: The mounting hole is a through hole, and the first portion of the rod-shaped component (20) is provided with a tool connection portion (50) so as to move the rod-shaped component (20) into the mounting hole when the locking block (10) is mounted in the mortise and tenon groove.

6. The aircraft engine according to claim 5, characterized in that: The tool connecting portion (50) comprises a threaded hole provided at a first end of the rod-shaped component (20).

7. The aircraft engine according to claim 1, characterized in that: The mortise and tenon comprises a mortise and tenon body, the radial outer end of the mortise and tenon body being open, the width of the opening of the mortise and tenon being smaller than the width of at least a part of the inner cavity of the mortise and tenon, so as to limit the blade from radially disengaging from the mortise and tenon.

8. The aircraft engine according to claim 7, characterized in that: The mortise and tenon further comprises an insertion opening communicated with the mortise and tenon body, and a width of the insertion opening is not less than a maximum width of the tenon.

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