A multifunctional vibration isolator suitable for high temperature environment application of turboprop engines

Abstract

The application discloses a multifunctional vibration isolator suitable for high-temperature environment application of a turboprop engine, comprising a mounting seat used for being connected with a mounting joint of the engine and provided with a U-shaped double lug at an upper end, a cavity framework nested on the U-shaped double lug, metal support plates connected at two sides of the cavity framework, a limiting shaft sleeve arranged between the cavity framework and the metal support plates, a metal wire mesh block filled in a filling space, and a shear bearing shaft with one end passing through a through hole in the middle of the metal support plate and abutting against a framework counterbore in the middle of the cavity framework and the other end fixed on a mounting frame of the engine through a tension bolt; wherein the pre-pressing bolt penetrates through the limiting shaft sleeve. The vibration isolator for the turboprop engine is simple in structure, closely assembled, and made of full metal material, and can adapt to severe temperature and corrosion environment, and is especially suitable for vibration isolation and mounting in a high-temperature environment above 200 DEG C at a mounting joint of the turboprop engine. Therefore, the application is suitable for wide promotion and application.

Description

Technical Field

[0001] This invention belongs to the field of turboprop engine vibration isolation technology application, specifically, it relates to a multifunctional vibration isolator suitable for high-temperature environments of turboprop engines. Background Technology

[0002] The intense vibrations generated by the propeller during the operation of turboprop aircraft engines are the primary source of cabin vibration in these aircraft. Excessive engine vibration transmitted into the cabin inevitably reduces the reliability of aircraft equipment and also decreases passenger comfort. To improve the reliability of cabin equipment and passenger comfort, vibration damping designs are required for turboprop engines, i.e., installing vibration dampers on the engines.

[0003] Application No. 202110895201.2 discloses a vibration damping device and vibration damping installation system structure for a turboprop engine. This vibration damping device is mainly made of rubber. However, the rubber vibration dampers used in turboprop engine installation cannot meet the requirements of certain high-temperature environments. High-temperature environments accelerate the aging of rubber materials and reduce rubber stiffness, thus adversely affecting the vibration dampers and failing to meet the needs of engine installation system development. Furthermore, turboprop engine installation requires the combined use of biaxial and triaxial stiffness vibration isolators; this invention can simultaneously solve this problem. Summary of the Invention

[0004] The purpose of this invention is to provide a multifunctional vibration isolator suitable for high-temperature applications of turboprop engines, mainly to solve the problem that existing turboprop engine vibration dampers cannot adapt to high-temperature environments.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0006] A multifunctional vibration isolator suitable for high-temperature applications of turboprop engines includes a mounting base with U-shaped double ears at the upper end for connection to the engine mounting section, a hollow frame nested in the U-shaped double ears, a metal support plate that passes through the hollow frame and U-shaped double ears and is connected to both sides of the hollow frame by preload bolts, a limiting bushing disposed between the metal support plate and the U-shaped double ears to form a filling space between the hollow frame and the metal support plate, a metal wire mesh block filled in the filling space, and a shear shaft with one end passing through a through hole in the middle of the metal support plate and abutting against a countersunk hole in the middle of the hollow frame, and the other end being fixed to the vibration isolator on the engine mounting frame by tension bolts; wherein, the preload bolts pass through the limiting bushings.

[0007] Furthermore, in this invention, the mounting base includes a mounting flange, U-shaped double ears disposed on the mounting flange, a pair of ear holes opened on the U-shaped double ears, a countersunk hole disposed on the U-shaped double ears and coaxial with the ear holes for installing a limiting bushing, and a positioning boss disposed at the bottom of the mounting flange for positioning with the engine mounting section.

[0008] Furthermore, in this invention, the cavity skeleton is provided with a U-shaped groove for the insertion of the U-shaped double ears. The left and right sides of the front and rear surfaces of the cavity skeleton are provided with first grooves. The first grooves of the cavity skeleton and the two first grooves are provided with three first through holes penetrating the front and rear surfaces of the cavity skeleton. The two first through holes corresponding to the first grooves are referred to as the two side first through holes, and the first through hole between the two first grooves is referred to as the middle first through hole.

[0009] Furthermore, in this invention, the metal support plate has three second through holes that penetrate the metal support plate and correspond to the positions of the three first through holes on the cavity skeleton; wherein, the second through holes corresponding to the first through holes on both sides are denoted as the second through holes on both sides, and the second through hole corresponding to the first through hole in the middle is denoted as the second through hole in the middle; the second through holes on both sides have inner countersunk holes coaxial with the second through holes on the side facing the U-shaped double ears, and the second through holes on both sides have outer countersunk holes coaxial with the second through holes on the side away from the U-shaped double ears; the inner side of the metal support plate has a second groove corresponding to the first groove.

[0010] Furthermore, in this invention, a joint bearing is provided inside the ear canal of the U-shaped ears.

[0011] Furthermore, in this invention, the shear shaft is provided with an annular limiting boss at one end located on the outer side of the metal support plate.

[0012] Furthermore, in this invention, the metal wire mesh block is configured as a square, cylindrical, or elliptical cylinder with a central through hole.

[0013] Furthermore, in this invention, all parts of the vibration isolator, including the metal wire mesh block, are made of high-temperature resistant metal materials.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] (1) The vibration isolator for turboprop engine of the present invention has a simple structure, tight assembly, and is made of all-metal materials, which can adapt to harsh temperature and corrosive environment, and is especially suitable for vibration isolation installation at the turboprop engine mounting section where the temperature reaches above 200°C.

[0016] (2) The stiffness of the vibration isolator of the present invention is easy to design. It can be designed as a two-dimensional stiffness vibration isolator or a three-dimensional stiffness vibration isolator as needed, and has a good application prospect in the field of vibration isolation installation of turboprop aircraft engines. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of one embodiment of the present invention.

[0018] Figure 2 for Figure 1 A schematic diagram of the cross-sectional structure.

[0019] Figure 3 for Figure 1 Another cross-sectional structural diagram.

[0020] Figure 4 This is a schematic diagram of one embodiment of the hollow skeleton in this invention.

[0021] Figure 5 This is a schematic diagram of one embodiment of the metal support plate in this invention.

[0022] Figure 6 This is a schematic diagram of one embodiment of the mounting base in this invention.

[0023] Figure 7 This is a schematic diagram of another embodiment of the metal wire mesh block of the present invention.

[0024] The names corresponding to the reference numerals in the attached figures are as follows:

[0025] 1-Hollow skeleton, 2-Metal support plate, 3-Metal wire mesh block, 4-Mounting base, 5-Shear bearing shaft, 6-Tension bolt, 7-Limiting bushing, 8-Spherical bearing, 9-Preload bolt, 10-Screw, 11-U-shaped groove, 12-First groove, 13-First through holes on both sides, 14-First through hole in the middle, 21-Second through holes on both sides, 22-Second through hole in the middle, 23-Inner countersunk hole, 24-Outer countersunk hole, 25-Second groove, 41-Mounting flange, 42-U-shaped double ears, 43-Ear hole, 44-Countersunk hole, 45-Positioning boss, 51-Annular limiting boss. Detailed Implementation

[0026] The present invention will be further described below with reference to the accompanying drawings and embodiments. The embodiments of the present invention include, but are not limited to, the following embodiments.

[0027] like Figures 1-3As shown, the present invention discloses a multifunctional vibration isolator suitable for high-temperature applications of turboprop engines, comprising a mounting base 4 for connecting to the engine mounting section and having a U-shaped double lug 42 at the upper end, a hollow frame 1 nested on the U-shaped double lug 42, a metal support plate 2 passing through the hollow frame 1 and the U-shaped double lug 42 and connected to both sides of the hollow frame 1 by a preload bolt 9, a limiting bushing 7 disposed between the metal support plate 2 and the U-shaped double lug 42 to form a filling space between the hollow frame 1 and the metal support plate 2, a metal wire mesh block 3 filling the filling space, and a shear shaft 5 having one end passing through a through hole in the middle of the metal support plate 2 and abutting against a countersunk hole in the middle of the hollow frame 1, and the other end being fixed to the vibration isolator on the engine mounting frame by a tension bolt 6; wherein, the preload bolt 9 passes through the limiting bushing 7. The vibration isolator achieves vibration isolation through the filled metal wire mesh block 3. In this embodiment, the metal wire mesh block 3 is set as a square block with a central through hole. The stiffness of the vibration isolator can be adjusted by adjusting the density of the metal wire mesh block 3. High density results in high stiffness, while low density results in low stiffness.

[0028] like Figure 7 As shown, in other embodiments, the wire mesh block 3 can also be configured as a cylindrical or elliptical cylinder with a central through hole.

[0029] like Figure 6 As shown, the mounting base 4 includes a mounting flange 41, U-shaped double ears 42 disposed on the mounting flange 41, a pair of ear holes 43 opened on the U-shaped double ears 42, a countersunk hole 44 disposed on the U-shaped double ears 42 and coaxial with the ear holes 43 for installing the limiting bushing 7, and a positioning boss 45 disposed at the bottom of the mounting flange 41 for positioning with the engine mounting section. When the mounting base 4 is installed with the engine mounting section, it is first positioned and connected with the engine mounting section by the positioning boss 45, and then fixedly connected by screws 10 through the mounting flange 41. All parts of the vibration isolator, including the metal wire mesh block, are made of high-temperature resistant metal materials. In particular, the mounting base 4 and screws 10, which are in direct contact with the engine mounting section, should be made of high-temperature resistant materials, such as GH4169 material.

[0030] like Figure 4 As shown, the cavity frame 1 is provided with a U-shaped groove 11 for the U-shaped double ears 42 to extend into. The cavity frame 1 has a first groove 12 on both the left and right sides of the front and rear sides. The cavity frame 1 has three first through holes that penetrate the front and rear sides of the cavity frame 1 between the first groove 12 and between the two first grooves. The two first through holes corresponding to the first grooves are called the two side first through holes 13, and the first through hole between the two first grooves is called the middle first through hole 14.

[0031] Correspondingly, such as Figure 5As shown, the metal support plate 2 has three second through holes that penetrate the metal support plate and correspond to the positions of the three first through holes on the cavity frame; wherein, the second through holes corresponding to the first through holes 13 on both sides are designated as the second through holes 21 on both sides, and the second through hole corresponding to the first through hole 14 in the middle is designated as the second through hole 22 in the middle; the second through holes 21 on both sides have inner countersunk holes 23 coaxial with the second through holes 23 on the side facing the U-shaped double ears, and the second through holes 21 on both sides have outer countersunk holes 24 coaxial with the second through holes 24 on the side away from the U-shaped double ears; the inner side of the metal support plate 2 has a second groove 25 corresponding to the first groove 12. In specific assembly, the preload bolt 9 passes through the second through holes 21 on both sides of the metal support plate 2, the limiting bushing, and the first through holes 13 on both sides of the cavity frame 1 to connect the metal support plate to the cavity frame 1, wherein the two ends of the limiting bushing 7 abut against the first groove and the inner countersunk hole 23 respectively, and the outer countersunk hole 24 is used to accommodate the bolt head of the preload bolt 9.

[0032] In this embodiment, a spherical bearing 8 is provided inside the ear hole 43 of the U-shaped double ear 42, and the spherical bearing is held in place by the limiting bushings 7 at both ends. This makes the vibration isolator only have biaxial stiffness, with almost zero axial stiffness along the tension bolt 6. In other embodiments, when the spherical bearing 8 is not installed in the ear hole 43, the vibration isolator has triaxial stiffness.

[0033] In this embodiment, the shear shaft 5 is provided with an annular limiting boss 51 at one end of the outer side of the metal support plate 2 to prevent excessive fit between the shear shaft 5 and the metal support plate 2.

[0034] Through the above design, the vibration isolator for turboprop engines of the present invention has a simple structure, tight assembly, and is made of all-metal materials, enabling it to withstand harsh temperature and corrosive environments. It is particularly suitable for vibration isolation installation at turboprop engine mounting points where temperatures exceed 200°C. Therefore, compared with the prior art, the present invention has outstanding substantive features and significant progress.

[0035] The above embodiments are merely one of the preferred embodiments of the present invention and should not be used to limit the scope of protection of the present invention. Any modifications or refinements made to the main design concept and spirit of the present invention that are not of substantial significance, but solve the same technical problem as the present invention, should be included within the scope of protection of the present invention.

Claims

1. A multifunctional vibration isolator suitable for high-temperature applications in turboprop engines, characterized in that, The device includes a mounting base (4) for connecting to the mounting section of the engine and having U-shaped double ears (42) at the upper end; a hollow frame (1) nested in the U-shaped double ears (42); a metal support plate (2) that passes through the hollow frame (1) and the U-shaped double ears (42) and is connected to both sides of the hollow frame (1) by a preload bolt (9); a limiting bushing (7) that is set between the metal support plate (2) and the U-shaped double ears (42) to form a filling space between the hollow frame (1) and the metal support plate (2); a metal wire mesh block (3) that fills the filling space; and a shear shaft (5) that passes through a through hole in the middle of the metal support plate (2) and abuts against a countersunk hole in the middle of the hollow frame (1) and has the other end fixed to the vibration isolator on the engine mounting frame by a tension bolt (6); wherein the preload bolt (9) passes through the limiting bushing (7). The cavity skeleton (1) is provided with a U-shaped groove (11) for the U-shaped double ears (42) to be inserted. The cavity skeleton (1) has a first groove (12) on both the left and right sides of the front and rear sides. The cavity skeleton (1) has three first through holes that penetrate the front and rear sides of the cavity skeleton between the first groove (12) and the two first grooves. The two first through holes corresponding to the first groove are called the two side first through holes (13), and the first through hole between the two first grooves is called the middle first through hole (14).

2. The multifunctional vibration isolator suitable for high-temperature environments of turboprop engines according to claim 1, characterized in that, The mounting base (4) includes a mounting flange (41), a U-shaped double lug (42) provided on the mounting flange (41), a pair of ear holes (43) opened on the U-shaped double lug (42), a countersunk hole (44) provided on the U-shaped double lug (42) and coaxial with the ear holes (43) for installing the limiting bushing (7), and a positioning boss (45) provided at the bottom of the mounting flange (41) for positioning with the mounting section of the engine.

3. A multifunctional vibration isolator suitable for high-temperature environments of turboprop engines according to claim 2, characterized in that, The metal support plate (2) is provided with three second through holes that penetrate the metal support plate and correspond to the positions of the three first through holes on the cavity skeleton; wherein, the second through holes corresponding to the first through holes (13) on both sides are referred to as the second through holes (21) on both sides, and the second through hole corresponding to the first through hole (14) in the middle is referred to as the second through hole (22) in the middle; the second through holes (21) on both sides are provided with an inner countersunk hole (23) coaxial with the second through holes on both sides on the side facing the U-shaped double ears, and the second through holes (21) on both sides are provided with an outer countersunk hole (24) coaxial with the second through holes on both sides on the side away from the U-shaped double ears; the metal support plate (2) is provided with a second groove (25) corresponding to the first groove (12) on the inner side.

4. A multifunctional vibration isolator suitable for high-temperature environments of turboprop engines according to claim 3, characterized in that, The ear holes (43) of the U-shaped double ears (42) are provided with joint bearings (8).

5. A multifunctional vibration isolator suitable for high-temperature environments of turboprop engines according to claim 4, characterized in that, The shear shaft (5) is provided with an annular limiting boss (51) at one end of the outer side of the metal support plate.

6. A multifunctional vibration isolator suitable for high-temperature environments of turboprop engines according to claim 5, characterized in that, The metal wire mesh block (3) is configured as a square, cylindrical, or elliptical cylinder with a central through hole.

7. A multifunctional vibration isolator suitable for high-temperature environments of turboprop engines according to claim 6, characterized in that, All components of the vibration isolator, including the wire mesh block, are made of high-temperature resistant metal materials.

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