CN113374856A - Reducer reaction torque force transmission vibration isolation device and installation method - Google Patents
Reducer reaction torque force transmission vibration isolation device and installation method Download PDFInfo
- Publication number
- CN113374856A CN113374856A CN202110771922.2A CN202110771922A CN113374856A CN 113374856 A CN113374856 A CN 113374856A CN 202110771922 A CN202110771922 A CN 202110771922A CN 113374856 A CN113374856 A CN 113374856A
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- vibration
- taper pin
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- casing
- taper
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- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 52
- 230000005540 biological transmission Effects 0.000 title claims abstract description 17
- 238000006243 chemical reaction Methods 0.000 title claims abstract description 17
- 238000000034 method Methods 0.000 title claims abstract description 9
- 238000002955 isolation Methods 0.000 title claims description 19
- 238000009434 installation Methods 0.000 title abstract description 9
- 238000013016 damping Methods 0.000 claims abstract description 30
- 229910052755 nonmetal Inorganic materials 0.000 claims description 4
- 239000007769 metal material Substances 0.000 claims description 2
- 230000000149 penetrating effect Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 3
- 230000009347 mechanical transmission Effects 0.000 abstract description 2
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 239000000725 suspension Substances 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 229910000861 Mg alloy Inorganic materials 0.000 description 1
- 241000555745 Sciuridae Species 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- SNAAJJQQZSMGQD-UHFFFAOYSA-N aluminum magnesium Chemical compound [Mg].[Al] SNAAJJQQZSMGQD-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- -1 polytetrafluoroethylene Polymers 0.000 description 1
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 1
- 239000004810 polytetrafluoroethylene Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/028—Gearboxes; Mounting gearing therein characterised by means for reducing vibration or noise
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/025—Support of gearboxes, e.g. torque arms, or attachment to other devices
Abstract
The invention discloses a device for resisting force transmission and isolating reaction torque of a speed reducer and an installation method, which relate to the technical field of mechanical transmission, comprise a main speed reducer casing and are characterized by comprising the following components: the damping wear-resistant ring comprises a plurality of case lugs, a machine body adapter, a taper pin and a damping wear-resistant ring, wherein a taper groove matched with the taper pin is formed in each case lug, the case lugs and the taper pin are installed in a taper surface centering mode, the upper part of the taper pin is axially locked by a locking nut, the outer ring of the damping wear-resistant ring is in centering fit with the inner hole of the taper pin, the inner hole of the damping wear-resistant ring is in centering fit with the outer diameter of the machine body adapter, and an axial vibration gap and a transverse vibration gap are formed between the bottom of the taper pin and the machine body adapter, so that stress concentration caused by bolt holes can be effectively avoided, the service life of parts is prolonged, and the number of parts is reduced; simple structure, high reliability, and good vibration damping and isolating effects.
Description
Technical Field
The invention relates to the technical field of mechanical transmission, in particular to a reducer reaction torque force transmission vibration isolation device and an installation method.
Background
The main reducer or rotor shaft assembly having a relatively large height to diameter ratio is typically mounted to the fuselage in a four-strut "hang" (Suspension) mounting (see figure 3) as a single unit. The axes of four support rods supporting the main speed reducer are intersected with the axis of the rotor shaft at one point (see the point O in figure 3), so that the main speed reducer becomes a pendulum bob, and the pneumatic loads such as the lift force, the bending moment and the like of the rotor are transmitted through the support rods. In view of the stress direction of the four support rods is crossed at one point, the main speed reducer overturns when working on the airplane, meanwhile, the reaction torque generated by the rotor wing can cause the main speed reducer to reversely rotate around the axis of the rotor wing shaft, in order to transmit the transverse force and the reaction torque generated at the lower part of the main speed reducer to the airplane body, the main speed reducer needs to be connected with the airplane body at the bottom by adopting a force transmission structure, the reaction torque and the transverse force are transmitted to the airplane body, meanwhile, the vibration generated by main vibration sources such as the excitation force and the moment of the rotor wing is transmitted to the airplane body through the main speed reducer, and the vibration reduction or vibration isolation design is needed to be adopted by the main speed reducer support rods and the force transmission connection structure of the bottom and the airplane body.
The existing main reducer supports the defects of the design scheme of force transmission and vibration isolation of the bottom of the upper focal point: the focus vibration isolation scheme on the SA321 'ultra-wasp' helicopter main speed reducer support is characterized in that the bottom of a main speed reducer casing is connected with the edge of a steel plate through 34 bolts; according to the combined vibration isolation installation scheme of the focus system and the double-flexible vibration isolation device on the support of the AS350 'squirrel' helicopter main speed reducer, the bottom of the main speed reducer is connected to a machine body through two pairs of flexible limiting blocks (vibration attenuation blocks) in the course and the side direction, the structure is complex, the number of special parts and standard parts is large, the weight is heavy, and meanwhile, the two structures can only reduce the axial vibration which cannot be completely isolated from the bottom of the main speed reducer.
The invention provides a novel helicopter main reducer reaction torque force transmission vibration isolation scheme aiming at the requirements of a main reducer bottom force transmission vibration isolation structure in an upper focus structural mode (extension lines of four support rods focus on one point (virtual focus) on a rotor shaft) and the defects of the prior art.
Disclosure of Invention
In order to solve the technical problems in the prior art, the invention provides a device for resisting torque, transmitting force and isolating vibration of a speed reducer and an installation method thereof.
The purpose of the invention can be realized by the following technical scheme:
a speed reducer reaction torque force transmission vibration isolation device and an installation method thereof are disclosed, wherein a main speed reducer casing, a plurality of casing lugs, a machine body adapter, a conical pin and a vibration reduction wear-resistant ring are arranged on the main speed reducer casing;
the bottom of the main speed reducer casing is provided with at least two casing lugs, each casing lug is internally provided with a tapered groove matched with a tapered pin, the lower part of the tapered pin is provided with an annular groove matched with a vibration-damping wear-resistant ring, the vibration-damping wear-resistant ring is arranged in the annular groove, and the vibration-damping wear-resistant ring is embedded with the tapered pin; the machine body adapter comprises an annular bulge positioned in the conical pin, and the vibration-damping wear-resisting ring is sleeved on the annular bulge;
the top of the taper pin penetrates through a lug of the casing to extend out, the taper pin is locked with the lug of the casing through a locking nut at the top, the interior of the taper pin is of a hollow structure, and the part of the top of the taper pin, which extends out of the lug of the casing, is of a hollow cylinder; an axial vibration gap and a transverse vibration gap are formed between the bottom of the conical pin and the machine body adapter.
Further: the part, extending out of the lug of the casing, of the top of the taper pin is sleeved with a gasket, the bottom of the gasket is attached to the lug of the casing and the taper pin, and the taper pin is in threaded connection with a lock nut and is used for fixedly connecting the taper pin with the lug of the casing.
Further: the upper part of the taper pin is a hollow cylinder, and the lower part of the taper pin is a hollow cone.
Further: the vibration-damping wear-resisting ring is made of a non-metal material with elasticity and wear-resisting characteristics, and the casing lug and the main speed reducer casing are integrally cast and formed.
Further: according to the mounting method of the vibration isolation device, S1, the lug of the casing and the taper pin are mounted in a conical surface centering mode, firstly, a locking nut penetrates through an upper through hole where the taper pin is located, and the locking nut is axially locked, so that the outer ring of the vibration-damping wear-resisting ring is in centering fit with the inner hole of the taper pin, and meanwhile, the inner hole of the vibration-damping wear-resisting ring is in centering fit with the outer diameter of the transfer seat of the machine body; s2, rigidly connecting the fuselage adapter with the helicopter platform through a stud; s3, a gap exists between the conical pin and the machine body adapter, an axial vibration gap is reserved between the bottom of the conical pin and the machine body adapter in the axial direction of the annular bulge, and a transverse vibration gap is reserved between the conical pin and the machine body adapter in the radial direction of the annular bulge.
The invention has the beneficial effects that:
the bottom of the casing is connected with the machine body through the invention, so that the reaction torque and the transverse force are transmitted, and the purposes of vibration reduction and vibration isolation are achieved. The bottom casing of the main speed reducer is provided with two casing lugs, the casing lugs are provided with tapered grooves, the tapered grooves and the tapered pins are installed in a tapered surface centering mode, the upper portions of the tapered grooves and the tapered pins are axially locked by locking nuts, and the lower portions of the tapered pins are provided with nonmetal vibration reduction wear-resistant rings. Damping wear ring external diameter and taper pin hole centering cooperation, damping wear ring hole and fuselage adapter external diameter centering cooperation, the fuselage adapter passes through stud and helicopter platform rigid connection, form axial vibration clearance and transverse vibration clearance between taper pin bottom and the fuselage adapter, effective isolated and transverse vibration, and adorn the damping wear ring on main reducer and allow to have the free slip of certain limit along the axial, play isolated axial vibration's effect. Stress concentration caused by the bolt holes can be effectively avoided, the service life of parts is prolonged, and the number of the parts is reduced; the manufacturability and the economical efficiency of parts and engines are improved; the technical scheme has the advantages of simple structure, high reliability and good vibration damping and isolating effects.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is a schematic bottom view of a main reducer case according to the present invention;
FIG. 2 is a schematic sectional view taken along line A-A of FIG. 1;
fig. 3 is a basic principle schematic diagram of a four-strut suspension mounting of a main speed reducer.
In the figure: 1. a main reducer case; 10. a case lug; 20. a fuselage adapter; 21. an annular projection; 22. an axial vibration gap; 23. a lateral vibration gap; 30. a tapered pin; 31. a vibration-damping wear-resistant ring; 32. locking the nut; 33. a gasket; 40. a stay bar; 50. a main reducer; 60. an elastic connection structure; 70. a fuselage.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-3, a preferred embodiment of the present invention provides a device for isolating a reducer from transmission of reaction torque and vibration and a method for installing the same, comprising a casing lug 10, a body adapter 20, the bottom of a main speed reducer casing 1 is symmetrically provided with two casing lugs 10, each casing lug 10 is internally provided with a tapered groove matched with the tapered pin 30, the casing lugs 10 and the tapered pins 30 are installed in a tapered surface centering mode, the lower part of each tapered pin 30 is provided with an annular groove matched with the corresponding tapered wear-resistant ring 31, each annular groove is internally provided with a nonmetallic tapered wear-resistant ring 31, each tapered wear-resistant ring 31 is sleeved on an annular bulge 21 of a fuselage adapter 20, the outer ring of each tapered wear-resistant ring 31 is matched with the inner hole of the tapered pin 30 in a centering mode, the inner hole of each tapered wear-resistant ring 31 is matched with the outer diameter of the fuselage adapter 20 in a centering mode, and the fuselage adapter 20 is rigidly connected with a helicopter platform through a stud;
in this embodiment, in a normal assembly state, there is a gap between the taper pin 30 and the fuselage adapter 20, wherein an axial vibration gap 22 is formed between the bottom of the taper pin 30 and the fuselage adapter 20 in the axial direction of the annular protrusion 21, and a transverse vibration gap 23 is formed between the taper pin 30 and the fuselage adapter 20 in the radial direction of the annular protrusion 21;
referring to fig. 2, in the present embodiment, the top of the taper pin 30 extends out of the casing lug 10 and is sleeved with a washer 33 and a lock nut 32, the extending portion is cylindrical, preferably, the portion of the top of the taper pin 30 extending out of the casing lug 10 is hollow cylinder, the portion of the taper pin 30 not extending out of the casing lug 10 is consistent with the z-axis direction of the casing lug 10, the bottom of the washer 33 is abutted with the casing lug 10 and the taper pin 30, and the lock nut 32 is in threaded connection with the taper pin 30.
In this embodiment, the vibration-damping wear-resistant ring 31 is made of polytetrafluoroethylene or rubber, and the material of the vibration-damping wear-resistant ring 31 has elasticity and wear-resistant property; the casing lug 10 is made of aluminum alloy or magnesium alloy, or magnesium aluminum alloy, and the casing lug 10 and the main speed reducer casing 1 are integrally cast and formed; the fuselage adapter 20 and the tapered pin 30 are made of steel.
When the main reducer 50 is assembled to the body 70, only the length of the stay bar 40 and the position of the body adapter 20 on the x-y plane need to be adjusted, and the adjustment of the base of the main reducer casing 1 in the z-axis direction is not needed to be added with a gasket 33 and the like, so that the adjustment-free installation in the z-direction is realized when the main reducer casing 1 is assembled with the body 70.
The invention is used for the configuration of a four-brace rod 40 Suspension installation (Suspension) main reducer 50, the main reducer 50 is installed on a machine body 70 through four brace rods 40, the bottom of the main reducer 50 is connected with the machine body 70 through a force transmission structure, and the force transmission structure is an elastic connection structure 60. The bottom of the main speed reducer casing 1 is connected with the machine body 70 through the scheme, so that the reaction torque and the transverse force are transmitted, and the purposes of vibration reduction and vibration isolation are achieved. According to the scheme of the invention, the main speed reducer casing 1 is provided with two casing lugs 10, the casing lugs 10 are provided with tapered grooves, the tapered grooves and a tapered pin 30 are installed in a tapered surface centering mode, the upper part is axially locked by a locking nut 32, and the lower part of the tapered pin 30 is provided with a non-metal vibration-damping wear-resisting ring 31. The outer diameter of the vibration-damping wear-resisting ring 31 is matched with the inner hole of the taper pin 30 in a centering mode, the inner hole of the vibration-damping wear-resisting ring 31 is matched with the outer diameter of the fuselage adapter 20 in a centering mode, the fuselage adapter 20 is rigidly connected with a helicopter platform through a stud, and an axial vibration gap 22 exists between the taper pin 30 and the fuselage adapter 20 in a normal assembly state. Aerodynamic loads such as rotor lift force, bending moment and the like are transmitted to the fuselage 70 through the stay 40 of the main speed reducer 50, and reaction torque and transverse force are transmitted to the fuselage adapter 20 through the two casing lugs 10 at the bottom of the main speed reducer casing 1 and then transmitted to the fuselage 70. When the helicopter runs, main vibration sources such as rotor exciting force, torque and the like generate vibration in three directions (the x direction: the transverse direction, the y direction: the course, the z direction: the direction perpendicular to a main reducer body mounting platform).
The foregoing is merely exemplary and illustrative of the present invention and various modifications, additions and substitutions may be made by those skilled in the art to the specific embodiments described without departing from the scope of the invention as defined in the following claims.
Claims (5)
1. The utility model provides a reduction gear reaction torque passes power vibration isolation device, includes main reducer machine casket (1), its characterized in that still includes: the structure comprises a plurality of casing lugs (10), a body adapter (20), a tapered pin (30) and a vibration-damping wear-resisting ring (31);
the bottom of the main speed reducer casing (1) is provided with at least two casing lugs (10), each casing lug (10) is internally provided with a tapered groove matched with a tapered pin (30), the lower part of each tapered pin (30) is provided with an annular groove matched with a vibration-damping wear-resistant ring (31), each vibration-damping wear-resistant ring (31) is arranged in the annular groove, and each vibration-damping wear-resistant ring (31) is embedded with the tapered pin (30);
the fuselage adapter (20) comprises an annular bulge (21) positioned in a tapered pin (30), and the vibration-damping wear-resisting ring (31) is sleeved on the annular bulge (21);
the top of the taper pin (30) penetrates through the casing lug (10), the taper pin (30) is locked with the casing lug (10) through a locking nut (32) at the top, the interior of the taper pin (30) is of a hollow structure, and the part of the top of the taper pin (30) extending out of the casing lug (10) is of a hollow cylinder;
an axial vibration gap (22) and a transverse vibration gap (23) are formed between the bottom of the conical pin (30) and the machine body adapter (20).
2. A reducer reaction torque force transmission vibration isolation device according to claim 1, wherein a gasket (33) is sleeved on the part, extending out of the casing lug (10), of the top of the taper pin (30), the bottom of the gasket (33) is attached to the casing lug (10) and the taper pin (30), and a lock nut (32) is screwed on the taper pin (30) for fixedly connecting the taper pin (30) with the casing lug (10).
3. A decelerator reaction torque force transmission vibration isolation device according to claim 1, wherein the upper part of the taper pin (30) is a hollow cylinder, and the lower part of the taper pin (30) is a hollow cone.
4. A decelerator reaction torque force transmission vibration isolation device according to claim 1, characterized in that the vibration damping wear-resisting ring (31) is made of non-metal material with elasticity and wear-resisting property, and the casing lug (10) is cast and formed integrally with the main decelerator casing (1).
5. The mounting method of the anti-torque force transmission vibration isolation device of the speed reducer is characterized in that:
s1, mounting the casing lug (10) and the taper pin (30) in a taper surface centering mode, firstly, penetrating and mounting a locking nut (32) in an upper through hole where the taper pin (30) is located, and axially locking to ensure that the outer ring of the vibration-damping wear-resisting ring (31) is in centering fit with the inner hole of the taper pin (30), and simultaneously, the inner hole of the vibration-damping wear-resisting ring (31) is in centering fit with the outer diameter of the machine body adapter (20);
s2, the fuselage adapter (20) is rigidly connected with the helicopter platform through a stud;
s3, a gap exists between the conical pin (30) and the machine body adapter (20), an axial vibration gap (22) is reserved between the bottom of the conical pin (30) and the machine body adapter (20) in the axial direction of the annular protrusion (21), and a transverse vibration gap (23) is reserved between the conical pin (30) and the machine body adapter (20) in the radial direction of the annular protrusion (21).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110771922.2A CN113374856A (en) | 2021-07-08 | 2021-07-08 | Reducer reaction torque force transmission vibration isolation device and installation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110771922.2A CN113374856A (en) | 2021-07-08 | 2021-07-08 | Reducer reaction torque force transmission vibration isolation device and installation method |
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| Publication Number | Publication Date |
|---|---|
| CN113374856A true CN113374856A (en) | 2021-09-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110771922.2A Pending CN113374856A (en) | 2021-07-08 | 2021-07-08 | Reducer reaction torque force transmission vibration isolation device and installation method |
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| CN (1) | CN113374856A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108591239A (en) * | 2018-05-02 | 2018-09-28 | 中国航发湖南动力机械研究所 | Rotor shaft assembly, main reducing gear and aircraft |
| CN110296171A (en) * | 2019-05-24 | 2019-10-01 | 南京航空航天大学 | A kind of Helicopter Main with helical structure subtracts period strut |
| CN209506105U (en) * | 2018-11-06 | 2019-10-18 | 中国直升机设计研究所 | A kind of mounting device of Helicopter Main Reducer |
| CN111038694A (en) * | 2019-12-04 | 2020-04-21 | 中国直升机设计研究所 | Novel anti-resonance main vibration reduction and isolation device |
| CN111457075A (en) * | 2020-03-31 | 2020-07-28 | 中国航发湖南动力机械研究所 | Antifriction device and aircraft transmission system main reducer |
-
2021
- 2021-07-08 CN CN202110771922.2A patent/CN113374856A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108591239A (en) * | 2018-05-02 | 2018-09-28 | 中国航发湖南动力机械研究所 | Rotor shaft assembly, main reducing gear and aircraft |
| CN209506105U (en) * | 2018-11-06 | 2019-10-18 | 中国直升机设计研究所 | A kind of mounting device of Helicopter Main Reducer |
| CN110296171A (en) * | 2019-05-24 | 2019-10-01 | 南京航空航天大学 | A kind of Helicopter Main with helical structure subtracts period strut |
| CN111038694A (en) * | 2019-12-04 | 2020-04-21 | 中国直升机设计研究所 | Novel anti-resonance main vibration reduction and isolation device |
| CN111457075A (en) * | 2020-03-31 | 2020-07-28 | 中国航发湖南动力机械研究所 | Antifriction device and aircraft transmission system main reducer |
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Application publication date: 20210910 |
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