CN105650198A - High-and-low-frequency vibration isolation rubber damper for turboprop engine - Google Patents
High-and-low-frequency vibration isolation rubber damper for turboprop engine Download PDFInfo
- Publication number
- CN105650198A CN105650198A CN201610185309.1A CN201610185309A CN105650198A CN 105650198 A CN105650198 A CN 105650198A CN 201610185309 A CN201610185309 A CN 201610185309A CN 105650198 A CN105650198 A CN 105650198A
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- CN
- China
- Prior art keywords
- hole
- low frequency
- eccentric disk
- fixing seat
- internal ring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
Abstract
The invention discloses a high-and-low-frequency vibration isolation rubber damper for a turboprop engine. The damper is characterized by comprising a fixed base, two damping blocks and a buffer pipe, the two damping blocks are arranged on the two sides of the fixed base respectively, each damping block comprises an inner eccentric plate and an outer eccentric plate parallel to the inner eccentric plate, each inner eccentric plate adheres to the corresponding outer eccentric plate through high-temperature vulcanization of rubber, a through hole penetrating through the corresponding inner eccentric plate, the corresponding outer eccentric plate and rubber in between is formed in each damping block, an inner ring is connected to the interior of each through hole from outside to inside in a penetrating mode, the outer end of each inner ring is connected to the corresponding outer eccentric plate in a pressing mode through a gasket, and the buffer pipe is connected to the fixed base in a penetrating mode and connected with inner-end excircles of the inner rings of the two damping blocks in a sleeved mode.
Description
Technical field
The present invention relates to rubber vibration isolation technical field, be specifically related to a kind of high and low frequency isolating technique rubber absorbers of turbo oar engine.
Background technology
Rise/stop at turbo oar engine and in work process, frequency under each adnexa of electromotor (propeller, motor and electromotor etc.) rotating speed can pass to aircraft ring frames, the vibration caused under unstable air-flow including aircraft ring frames in flight course passes to electromotor etc., directly or indirectly affects the safety of aircraft flight. In order to avoid influencing each other that the vibration of aircraft ring frames and electromotor brings, it will usually require mutually isolated between the operating frequency of aircraft ring frames and electromotor.
The implementation of the mutual vibration effect being generally insulated between aircraft ring frames and electromotor is: spring damping chip vibroshock and rubber shock absorber. Owing to rigidity and the damping ratio adjustability of spring damping chip vibroshock are poor, and structure, installation form are limited, thus spring damping chip vibroshock to apply this type of environment limited; Rubber shock absorber can according to different load distributions and mounting interface, the frequency band that vibroshock is isolated is adjusted by the rigidity and damping ratio adjusting rubber, and the structure of mould when adjusting structural member and the vulcanization of rubber according to framework and engine interface form, thus the frequency isolation met between aircraft ring frames and electromotor and interface dimensional requirement.
Summary of the invention
It is an object of the invention to provide a kind of new type rubber vibroshock, solve small-sized turbo oar engine and cause engine life to shorten and reliability reduction owing to adopting to be rigidly connected.
The technical solution adopted in the present invention is: a kind of turbo oar engine is high, low frequency vibration isolation rubber absorbers, it is characterized in that: include fixing seat, two snubber blocks and separator tube, two snubber blocks are respectively arranged at the both sides of fixing seat, in snubber block includes, outer eccentric disk, in, outer eccentric disk be arranged in parallel and between the two through the high temperature vulcanized bonding of rubber, in snubber block is provided with through, the through hole of outer eccentric disk and therebetween rubber, cross-under internal ring from outside to inside in through hole, internal ring outer end compresses through packing ring and is connected on outer eccentric disk, separator tube cross-under is on fixing seat and is socketed the internal ring the inner cylindrical connecting two snubber blocks.
Further, described through-hole diameter is more than internal ring the inner outside diameter.
Further, described through-hole diameter is more than separator tube outside diameter.
Further, described internal ring the inner cylindrical and through hole eccentric setting.
Further, described fixing seat connects on the end face of amortisseur and is provided with the alignment pin cooperated and hole, location fit structure on interior eccentric disk.
Further, described fixing seat bottom portion is provided with footing, and footing is provided with multiple fixing hole.
Further, it is crimped with heatproof pad bottom described reservation.
By adjusting formula proportion and the curing temperature of elastomeric material, the time, rubber quality was containing natural rubber 60%, white carbon black 30%, inorganic matter 7%, low molecule organic matter 3% thus changing rigidity and the damping ratio of elastomeric material. When engine start, operation, stopping and then being effectively isolated and weaken electromotor and pass to the vibration of aircraft ring frames and aircraft ring frames passes to the vibration of electromotor. The snubber block of fixing seat both sides is by vulcanizing the elastomeric material rigidity connected and damping ratio is effectively isolated or weakens electromotor and passes to aircraft ring frames and aircraft ring frames passes to the vibration of electromotor, the heatproof pad of combined fixed seat bottom end, is effectively improved service life of aeroengine and flight comfort level, reliability further.
Accompanying drawing explanation
Fig. 1 is present configuration schematic diagram.
In figure: fixing seat 1, bolt 2, footing 3, heatproof pad 4, the first internal ring 5, the first packing ring 6, first outer eccentric disk 7, eccentric disk 8 in first, the second internal ring 9, the second packing ring 10, the second outer eccentric disk 11, eccentric disk 12 in second, rubber 13, the first through hole 14, separator tube 15, alignment pin 16.
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described.
Shown in Fig. 1: a kind of turbo oar engine high and low frequency isolating technique rubber absorbers include in fixing seat 1, bolt 2, footing 3, heatproof pad the 4, first internal ring the 5, first packing ring the 6, first outer eccentric disk 7, first eccentric disk 12, rubber 13 and separator tube 15 in eccentric disk the 8, second internal ring the 9, second packing ring the 10, second outer eccentric disk 11, second. being connected to through multiple bolt 2 cross-under heatproof pads 4 on the footing 3 of fixing seat 1 and install and use occasion, the both sides of fixing seat 1 arrange first, two snubber blocks, the first snubber block includes in first, outer eccentric disk 8, 7, in first, outer eccentric disk 8, 7 be arranged in parallel and between the two through the high temperature vulcanized bonding of rubber 13, the first snubber block are provided with through in first, first through hole 14 of outer eccentric disk and therebetween rubber, the first internal ring of cross-under from outside to inside 5 in the first through hole 14, first internal ring 5 outer end the first packing ring 6 compresses and is connected on the first outer eccentric disk 7, and the second snubber block includes in second, outer eccentric disk 12, 11, in second, outer eccentric disk 12, 11 be arranged in parallel and between the two through the high temperature vulcanized bonding of rubber, the second snubber block are provided with through in second, second through hole of outer eccentric disk and therebetween rubber, the second internal ring of cross-under from outside to inside 9 in second through hole, second internal ring 9 outer end the second packing ring 10 compresses and is connected on the second outer eccentric disk 11, and separator tube 15 cross-under is on fixing seat 1 and is socketed the internal ring the inner cylindrical connecting two snubber blocks.
Improving further, through-hole diameter is more than internal ring the inner outside diameter.
Improving further, through-hole diameter is more than separator tube outside diameter.
Improvement further, internal ring the inner cylindrical and through hole eccentric setting.
Improving further, fixing seat connects on the end face of amortisseur and is provided with the alignment pin 16 cooperated and hole, location fit structure on interior eccentric disk.
Claims (7)
1. a turbo oar engine height, low frequency vibration isolation rubber absorbers, it is characterized in that: include fixing seat, two snubber blocks and separator tube, two snubber blocks are respectively arranged at the both sides of fixing seat, in snubber block includes, outer eccentric disk, in, outer eccentric disk be arranged in parallel and between the two through the high temperature vulcanized bonding of rubber, in snubber block is provided with through, the through hole of outer eccentric disk and therebetween rubber, cross-under internal ring from outside to inside in through hole, internal ring outer end compresses through packing ring and is connected on outer eccentric disk, separator tube cross-under is on fixing seat and is socketed the internal ring the inner cylindrical connecting two snubber blocks.
2. a kind of high and low frequency isolating technique rubber absorbers of turbo oar engine according to claim 1, is characterized in that: described through-hole diameter is more than internal ring the inner outside diameter.
3. a kind of high and low frequency isolating technique rubber absorbers of turbo oar engine according to claim 1, is characterized in that: described through-hole diameter is more than separator tube outside diameter.
4. the high and low frequency isolating technique rubber absorbers of a kind of turbo oar engine according to claim 1 or 2 or 3, is characterized in that: described internal ring the inner cylindrical and through hole eccentric setting.
5. a kind of high and low frequency isolating technique rubber absorbers of turbo oar engine according to claim 1, is characterized in that: described fixing seat connects on the end face of amortisseur and is provided with the alignment pin cooperated and hole, location fit structure on interior eccentric disk.
6. a kind of high and low frequency isolating technique rubber absorbers of turbo oar engine according to claim 1, is characterized in that: described fixing seat bottom portion is provided with footing, and footing is provided with multiple fixing hole.
7. a kind of high and low frequency isolating technique rubber absorbers of turbo oar engine according to claim 1, is characterized in that: be crimped with heatproof pad bottom described reservation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610185309.1A CN105650198A (en) | 2016-03-29 | 2016-03-29 | High-and-low-frequency vibration isolation rubber damper for turboprop engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610185309.1A CN105650198A (en) | 2016-03-29 | 2016-03-29 | High-and-low-frequency vibration isolation rubber damper for turboprop engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105650198A true CN105650198A (en) | 2016-06-08 |
Family
ID=56494794
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610185309.1A Pending CN105650198A (en) | 2016-03-29 | 2016-03-29 | High-and-low-frequency vibration isolation rubber damper for turboprop engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105650198A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106989816A (en) * | 2017-06-02 | 2017-07-28 | 中国航发南方工业有限公司 | Turbo oar engine vibration-measuring sensor is calibrated and measurement apparatus |
| CN113482778A (en) * | 2021-08-03 | 2021-10-08 | 中国航发湖南动力机械研究所 | Vibration damping device and vibration damping mounting system structure of turboprop engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1871457A (en) * | 2002-07-17 | 2006-11-29 | 特雷里博格汽车技术中心有限责任公司 | Hydraulic damping bush |
| WO2009020525A1 (en) * | 2007-08-03 | 2009-02-12 | The Gates Corporation | Rubber composition and vibration damper using the rubber composition |
| CN102177362A (en) * | 2008-10-09 | 2011-09-07 | 株式会社普利司通 | Vibration damping device |
| CN103615497A (en) * | 2013-12-04 | 2014-03-05 | 中国飞机强度研究所 | Support type engine rubber vibration insulation device |
| CN104696427A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Large angular rigidity turboprop engine rubber vibration isolator |
| CN205654775U (en) * | 2016-03-29 | 2016-10-19 | 江苏晟楠电子科技股份有限公司 | Whirlpool oar engine is high, Rubber shock absorber ware is kept apart in low frequency vibration |
-
2016
- 2016-03-29 CN CN201610185309.1A patent/CN105650198A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1871457A (en) * | 2002-07-17 | 2006-11-29 | 特雷里博格汽车技术中心有限责任公司 | Hydraulic damping bush |
| WO2009020525A1 (en) * | 2007-08-03 | 2009-02-12 | The Gates Corporation | Rubber composition and vibration damper using the rubber composition |
| CN102177362A (en) * | 2008-10-09 | 2011-09-07 | 株式会社普利司通 | Vibration damping device |
| CN103615497A (en) * | 2013-12-04 | 2014-03-05 | 中国飞机强度研究所 | Support type engine rubber vibration insulation device |
| CN104696427A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Large angular rigidity turboprop engine rubber vibration isolator |
| CN205654775U (en) * | 2016-03-29 | 2016-10-19 | 江苏晟楠电子科技股份有限公司 | Whirlpool oar engine is high, Rubber shock absorber ware is kept apart in low frequency vibration |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106989816A (en) * | 2017-06-02 | 2017-07-28 | 中国航发南方工业有限公司 | Turbo oar engine vibration-measuring sensor is calibrated and measurement apparatus |
| CN113482778A (en) * | 2021-08-03 | 2021-10-08 | 中国航发湖南动力机械研究所 | Vibration damping device and vibration damping mounting system structure of turboprop engine |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160608 |