CN104696427A - Large angular rigidity turboprop engine rubber vibration isolator - Google Patents
Large angular rigidity turboprop engine rubber vibration isolator Download PDFInfo
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- CN104696427A CN104696427A CN201310660639.8A CN201310660639A CN104696427A CN 104696427 A CN104696427 A CN 104696427A CN 201310660639 A CN201310660639 A CN 201310660639A CN 104696427 A CN104696427 A CN 104696427A
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- Prior art keywords
- mounting
- boss
- screw rod
- large angular
- mounting base
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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 provides a large angular rigidity turboprop engine rubber vibration isolator with failure protection measures. According to the technical scheme, the large-angle rigidity turboprop engine rubber vibration isolator comprises a base 1, a front cover plate 4, a rear cover plate 5, four mounting plates 2 and rubber blocks 3, wherein the four mounting pates 2 are connected with the mounting base through clamping grooves; the rubber blocks 3 are symmetrically arranged between the front cover plate 4 and the mounting plate 2 and between the rear cover plate 5 and the mounting plate 2 in an up and down manner; a sleeve 6 sleeves a connecting screw rod 7; the connecting screw rod 7 penetrates through the front cover plate 4 and the rear cover plate 5; a sealing screw cap 8 is screwed on one side, on the rear cover plate 5, of the connecting screw rod 7; a threaded protecting sleeve 9 is screwed at the end part, on the rear cover plate 5, of the screw rod 7.
Description
Technical field
The invention belongs to the vibration isolation buffering device that a kind of aeroengine is installed and used, the vibration isolation relating to Aeronautics and Astronautics and ship domain power plant is installed.
Background technique
The vibration that the work of aviation turbo oar engine produces can produce considerable influence to airplane complete machine vibration environment and riding comfort, effectively suppresses its vibration to the transmission of aircraft by engine vibration isolation installation system.In the vibrating isolation system be made up of multiple rubber vibration isolation device, the performance that each isolation mounting utilizes the superelasticity of rubber element and can produce moderate finite deformation provides stiffness characteristics for isolation mounting; Rubber material molecular chain and its expendable distortion dissipate vibrational energy is each other utilized to provide damping characteristic for isolation mounting; Metallic member in isolation mounting is then for isolation mounting provides upper and lower port to connect and structure support.
The vibrating isolation system be made up of turbo oar engine and multiple isolation mounting has three-dimensional six-degree of freedom vibration characteristic, respectively there is bigger difference motor joint to load simultaneously, especially mobilizing owner that joint place is installed, course load is larger compared with other directions, so the different stiffness characteristics of the specific three-dimensional of tool answered by isolation mounting herein, require and anti-vibration performance requirement with the posting of mating whole motor installation system.Meanwhile, due to the limitations of aeroengine erection joint position, its position not easily adjusts, and the distribution form of vibrating isolation system employing is at present poor at pitch orientation angular rigidity, is unfavorable for the suppression of pitch vibration.
Summary of the invention
Goal of the invention: the large angular rigidity turbo oar engine of the one with fail safe measure rubber vibration isolator is provided.
Technological scheme: a kind of turbo oar engine large angular rigidity rubber vibration isolation device, for the pedestal metal rubber structure of almost plane symmetry, comprise mounting base 1, front shroud 4, back shroud 5, four mounting plates 2 be connected by draw-in groove with mounting base, be symmetricly set between front shroud 4 and mounting plate 2 up and down, and the block rubber 3 between back shroud 5 and mounting plate 2, sleeve 6 is socketed in outside connecting screw rod 7, connecting screw rod 7 runs through front shroud 4 and back shroud 5, encapsulation nut 8 is screwed onto the side that connecting screw rod 7 is positioned at back shroud 5, protecting sleeve for thread 9 is screwed onto the end that connecting screw rod 7 is positioned at back shroud 5.
Beneficial effect:
1, according to turbo oar engine mounting structure feature and performance characteristic, require that engine vibration isolation installation system has larger angular rigidity at pitch plane, to suppress pitch vibration, when mounting arrangement not easily adjusts, specialized designs of the present invention has the isolation mounting of larger angular rigidity to improve whole vibrating isolation system angular rigidity characteristic, the pitch vibration of motor can be effectively reduced, improve whole vibrating isolation system performance;
2, the isolation mounting that aeroengine, auxiliary power unit etc. are installed should be designed with fail safe measure, to ensure that power equipment is because of the reliable installation after the inefficacy of isolation mounting accidental destruction, i.e. the fail safety measure at aircraft key joints position.Isolation mounting involved in the present invention utilizes closed type metal assembly structure, elastic element is packaged into isolation mounting interior location, even if rubber element is torn, come off, isolation mounting still can ensure the secure connection of whole system, belongs to a kind of effective safety measure;
3, isolation mounting overall structure adopts mounting base to add the distribution form of elastic component, enhance convertibility and the maintainalbility of vibration isolation element, utilize the mode of multiple small size rubber element parallel connection to replace large scale rubber element to realize high bearing capacity simultaneously, reduce die size, reduce die sinking cost;
4, the mounting base of this isolation mounting is provided with multiple pass structure and trench structure simultaneously, both the positioning requirements that rubber assembly is installed had been met, also for the connection of isolation mounting and Engine torque compensation device is provided with special purpose interface, adopt structural Topology Optimization simultaneously, alleviate structure weight;
5, because airplane engine surrounding work temperature is higher, require that the rubber element resistance to heat in isolation mounting will be got well, simultaneously in order to ensure the environmental suitability of aircraft in extremely cold region, isolation mounting rubber element also should possess good resistance to low temperature, therefore isolation mounting involved in the present invention selects high and low temperature-resistant rubber with high damping to prepare rubber element, effectively improves the environmental suitability of isolation mounting.
Accompanying drawing explanation
Fig. 1 a is schematic diagram one of the present invention;
Fig. 1 b is schematic diagram two of the present invention;
Fig. 2 is sectional drawing of the present invention;
Fig. 3 is mounting base 1 of the present invention and elastic component (comprising in mounting plate 2, block rubber 3 and front shroud 4 or lower back shroud 5) schematic diagram;
Wherein, 1-mounting base, 2-mounting plate, 3-block rubber; 4-front shroud, 5-back shroud, 6-sleeve, 7-connecting screw rod; 8-encapsulates nut, 9-protecting sleeve for thread, 10-annular boss; 11-⊥ type boss, 12-notch, 13-rectangular boss; 14-stiffening rib, 15-inclined-plane boss, 16-bottom boss; 17-circular hole, 18-thread section, 19-opening manhole.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Below in conjunction with accompanying drawing, the present invention is described in further detail, refers to Fig. 1 to Fig. 3.
A kind of turbo oar engine large angular rigidity rubber vibration isolation device, for the pedestal metal rubber structure of almost plane symmetry, comprise mounting base 1, front shroud 4, back shroud 5, four mounting plates 2 be connected by draw-in groove with mounting base, be symmetricly set between front shroud 4 and mounting plate 2 up and down, and the block rubber 3 between back shroud 5 and mounting plate 2, sleeve 6 is socketed in outside connecting screw rod 7, connecting screw rod 7 runs through front shroud 4 and back shroud 5, encapsulation nut 8 is screwed onto the side that connecting screw rod 7 is positioned at back shroud 5, protecting sleeve for thread 9 is screwed onto the end that connecting screw rod 7 is positioned at back shroud 5.
Described mounting base 1 is ⊥ type boss 11 structure of base band four opening manholes; The bottom of mounting base 1 is provided with the annular boss 10 that an external diameter is 80mm, and annular boss 10 and base are provided with the through hole that internal diameter is 60mm; Described mounting base 1 utilizes bottom annular boss 10 and four bolts to fix on the engine through base four U-shaped holes 19, wherein mounting base 1 bottom annular boss 10 coordinates with bolt-clearance with the circular groove drive fit of starting on owner's mounting platform face, each through hole, to ensure that shearing load and tension load are born by different parts.
⊥ type boss 11 top of described mounting base 1 is symmetrically set with two circular ports along screw rod, and is provided with the special purpose interface such as groove, hole structure for connecting engine torque compensator in ⊥ type boss 11 inside; ⊥ type boss 11 plane is set side by side with the rectangular through-hole of square through hole that a length of side is 90mm and the wide 40mm of a long 90mm up and down; After having assembled, connecting screw rod 7 and sleeve 6 run through this square opening, and the two diameter dimension is all less than square opening sectional dimension, to meet the requirement of isolation mounting vibration displacement.
Described mounting base 1 is provided with the connection part of mounting plate 2 notch 12 matched, the fixing on mounting base 1 for mounting plate 2 and elastic component; The ⊥ type boss 11 of mounting base 1, after topological optimization, is provided with the hole of different cross section size, to alleviate the weight of mounting base 1 and whole isolation mounting in vertical plane, side.
Described four pieces of mounting plates 2 are the rectangular plate on a side plane, opposite side inclined-plane, and side, inclined-plane is provided with the rectangular boss 13 of symmetrical rectangular recess structure and rear and front end symmetry; For notch 12 location fit with mounting base 1, boss is utilized can effectively to improve the reliability be connected between elastic component with mounting base with the fit form of draw-in groove.
Described four block rubbers 3 are certain thickness rectangular block, wherein one group of block rubber 3 side of screw tip side are provided with stiffening rib 14, for improving himself rigidity, to meet the load bearing requirements along side, motor power direction; Described block rubber 3 is made in the sulfuration of certain process conditions dip mold for high temperature and high damping resistant rubber material, can keep good mechanical property in the temperature range of-50 DEG C-100 DEG C;
Described front shroud 4 and back shroud 5 are a side plane, opposite side is provided with slab construction along center line symmetrical inclined-plane boss 15, plane side is provided with equally distributed four rectangle grooves, inclined-plane one middle side part is the rectangle groove of one fixed width, being respectively arranged with diameter in the middle part of front shroud 4 and back shroud 5 bottom surface is 16mm, 24mm manhole, to meet the installation requirement of sleeve 6 and connecting screw rod 7, after installation, sleeve top boss is concordant with bottom front shroud 4, connecting screw rod 7 exceeds sleeve 6 about 20mm; Described connecting screw rod 7 stage casing is smooth round bar; end has length to be the thread section 18 of 25mm; by encapsulation nut 8, whole isolation mounting is encapsulated again; during actual use; after protecting sleeve for thread 9 and encapsulation nut 8 are laid down; by thread section 18, this isolation mounting is fixed in the bolt hole of erection joint place of engine stand, and with torque-indicating wrencg, pretightening force is controlled according to certain requirement.
The described block rubber 3 be arranged between mounting plate 2 and back shroud 5 adopts adhesive specially sulfuration at 170 DEG C to form with the connection of the two;
Described sleeve 6 outside is each section of boss with different-diameter, and sleeve 6 and back shroud 5 are by bottom boss 16 and circular hole 17 location and installation; Described connecting screw rod stage casing is smooth round bar, and there is certain length screw thread end, and encapsulated by whole isolation mounting by encapsulation nut, be loaded on protecting sleeve for thread 9, in transportation process, double thread section 18 is protected;
Described protecting sleeve for thread 9 is top seal, bottom opening, be about the telescoping structure of 25mm, and downward 5-10mm place, top is provided with outer six side's boss, tightening during for installing; During the actual use of isolation mounting, after protecting sleeve for thread 9 and encapsulation nut 8 being laid down successively, isolation mounting is connected with the main erection joint of engine stand by the thread section 18 of connecting screw rod 7;
Described mounting base 1 is matched with the mountion plate on attachment face before motor by base four U-shaped holes 19 and bottom annular boss 10 structure, is fixed on the engine by this type isolation mounting, and takes certain locking measure.For the connection of motor and motor mounts, jointly isolate the transmission of engine luggine to aircraft with other isolation mountings in vibrating isolation system.
Concrete installation steps are as follows:
1, the mould of first design specialized, mounting plate 2 and front shroud 4, back shroud 5, after surface sand-blasting process, smear special rubber and metal binding agent at the surface uniform bonding with block rubber 3.Again two of metal material pieces of mounting plates 2, cover plate and two block rubbers 3 to be filled in mould and to carry out high temperature vulcanized under specific process conditions, making the channel rubber metal plate structure be jointly made up of three, in this specification, be referred to as elastic component;
2, mounting plate 2 in two pieces of above-mentioned elastic components is matched by boss and groove structure with mounting base 1;
3, by the square opening of sleeve 6 through mounting base 1 boss plane, be arranged between front shroud 4 and back shroud 5, have larger diameter round platform one end to match with the bottom outlet of front shroud 4, outside sleeve 6 round platform, cylindrical section is through the bottom outlet of back shroud 5, and round platform exterior edge face is concordant with bottom back shroud 5.
4, connecting screw rod 7 is inserted sleeve 6 inner, along sleeve 6 axis, pass the bottom outlet of front shroud 4, the square opening of mounting base 1 boss plane and the bottom outlet of back shroud 5 from top to bottom successively, connecting screw rod 7 exceeds sleeve 6 about 20mm;
5, encapsulation nut 8 is screwed onto on connecting screw rod 7, when being screwed onto concordant with back shroud 5 top bottom encapsulation nut 8, then nut 8 stubborn 1mm downwards will be encapsulated, and make isolation mounting bear certain pretightening force;
6, protecting sleeve for thread 9 is screwed onto on the connecting screw rod 7 assembled, its thread section 18 is protected;
7, assembled.
8, when this isolation mounting is installed on the engine, mounting base 1 bottom annular boss 10 is matched with engine mounting stand face circular groove, four bolts are screwed to by four U-shaped holes 19 in four bolts hole installed and table top corresponds again, realize the connection of isolation mounting and motor;
When 9, isolation mounting being fixed in aircraft engine frame together with motor; first protecting sleeve for thread 9, encapsulation nut 8 are unloaded successively; adopt torque-indicating wrencg to be screwed onto on engine stand in corresponding bolt hole by connecting screw rod again, and apply certain pretightening force by torque-indicating wrencg to isolation mounting by technical requirements.
10, install.
Claims (10)
1. a large angular rigidity turbo oar engine rubber vibration isolation device, for the pedestal metal rubber structure of almost plane symmetry, it is characterized in that, comprise mounting base [1], front shroud [4], back shroud [5], four mounting plates [2] be connected by draw-in groove with mounting base, be symmetricly set between front shroud [4] and mounting plate [2] up and down, and the block rubber [3] between back shroud [5] and mounting plate [2], sleeve [6] is socketed in connecting screw rod [7] outward, connecting screw rod [7] runs through front shroud [4] and back shroud [5], encapsulation nut [8] is screwed onto the side that connecting screw rod [7] is positioned at back shroud [5], protecting sleeve for thread [9] is screwed onto the end that connecting screw rod [7] is positioned at back shroud [5].
2. large angular rigidity turbo oar engine rubber vibration isolation device according to claim 1, is characterized in that, described mounting base [1] is ⊥ type boss [11] structure of base [12] band four opening manholes.
3. large angular rigidity turbo oar engine rubber vibration isolation device according to claim 2, is characterized in that,
The bottom of described mounting base [1] is provided with annular boss [10] structure that an external diameter is 80mm, and annular boss [10] and base [12] are provided with the through hole that internal diameter is 60mm;
⊥ type boss [11] top of described mounting base [1] is symmetrically set with two circular ports along screw axis, and the groove be provided with in ⊥ type boss [11] inside for connecting engine torque compensator and hole structure;
⊥ type boss [11] plane of described mounting base [1] is set side by side with the rectangular through-hole of square through hole that a length of side is 90mm and the wide 40mm of a long 90mm up and down.
4. large angular rigidity turbo oar engine rubber vibration isolation device according to claim 1, it is characterized in that, the position that described mounting base [1] is connected with mounting plate [2] is provided with the notch [12] matched.
5. large angular rigidity turbo oar engine rubber vibration isolation device according to claim 2, is characterized in that, the ⊥ type boss [11] of described mounting base [1] is provided with the hole of different cross section size in vertical plane, side.
6. large angular rigidity turbo oar engine rubber vibration isolation device according to claim 4, it is characterized in that, described four pieces of mounting plates [2] are the rectangular plate on a side plane, opposite side inclined-plane, side, inclined-plane is provided with the rectangular boss [13] of laterally zygomorphic rectangular recess structure and two ends, left and right symmetry, coordinates with the notch [12] of mounting base [1].
7. large angular rigidity turbo oar engine rubber vibration isolation device according to claim 1, it is characterized in that, described block rubber [3] is certain thickness rectangular block, wherein one group of block rubber [3] side of bolt head side is provided with stiffening rib [14].
8. large angular rigidity turbo oar engine rubber vibration isolation device according to claim 1, it is characterized in that, described front shroud [4] and back shroud [5] are a side plane, opposite side is provided with slab construction along symmetrical inclined-plane boss [15] of center line, plane side is provided with equally distributed four rectangle grooves, and being respectively arranged with diameter in the middle part of front shroud [4] and back shroud [5] bottom surface is 16mm, 24mm manhole;
Be arranged between mounting plate [2] and front shroud [4], and the block rubber [3] between mounting plate [2] and back shroud [5] adopts adhesive specially to be formed in the high temperature vulcanized process of 170 DEG C with the connection of mounting plate [2], front shroud [4], back shroud [5];
Described sleeve [6] outside is each section of boss with different-diameter, and sleeve [6] and back shroud [5] carry out location and installation by bottom boss [16] and circular hole [17].
9. want the large angular rigidity turbo oar engine rubber vibration isolation device described in 1 according to right, it is characterized in that, described connecting screw rod [7] stage casing is smooth round bar, there is certain length thread section [18] end, by encapsulation nut, whole isolation mounting is encapsulated, during the actual use of isolation mounting, after protecting sleeve for thread [9] and encapsulation nut [8] being laid down successively, isolation mounting is connected with the main erection joint of engine stand by the thread section [18] of connecting screw rod [7];
Described protecting sleeve for thread [9] is top seal, bottom opening, be about the telescoping structure of 25mm, and downward 5-10mm place, top is provided with outer six side's boss.
10. want the large angular rigidity turbo oar engine rubber vibration isolation device described in 1 according to right, it is characterized in that, described mounting base [1] is installed table top by bottom annular boss [10] and four fixing bolts through attachment face side direction major joint before base four U-shaped holes [19] and turbo oar engine and is matched, and is fixed on the engine by this type isolation mounting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310660639.8A CN104696427B (en) | 2013-12-06 | 2013-12-06 | A kind of big angular rigidity turbo oar engine rubber shock absorber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310660639.8A CN104696427B (en) | 2013-12-06 | 2013-12-06 | A kind of big angular rigidity turbo oar engine rubber shock absorber |
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| CN104696427A true CN104696427A (en) | 2015-06-10 |
| CN104696427B CN104696427B (en) | 2017-12-12 |
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| CN201310660639.8A Active CN104696427B (en) | 2013-12-06 | 2013-12-06 | A kind of big angular rigidity turbo oar engine rubber shock absorber |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105650198A (en) * | 2016-03-29 | 2016-06-08 | 江苏晟楠电子科技股份有限公司 | High-and-low-frequency vibration isolation rubber damper for turboprop engine |
| CN105673773A (en) * | 2014-11-20 | 2016-06-15 | 北京自动化控制设备研究所 | Damper structure used for long and narrow space |
| CN111981069A (en) * | 2020-07-20 | 2020-11-24 | 中国船舶重工集团有限公司第七一0研究所 | Rubber vibration isolation device suitable for underwater propeller |
| CN112594327A (en) * | 2020-12-16 | 2021-04-02 | 中国船舶重工集团有限公司第七一0研究所 | Rubber vibration isolation device |
| 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 |
| CN115750679A (en) * | 2023-01-10 | 2023-03-07 | 西安航弓机电科技有限公司 | Vibration absorber for turboprop engine and performance detection method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105673773A (en) * | 2014-11-20 | 2016-06-15 | 北京自动化控制设备研究所 | Damper structure used for long and narrow space |
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| CN111981069B (en) * | 2020-07-20 | 2022-04-12 | 中国船舶重工集团有限公司第七一0研究所 | Rubber vibration isolation device suitable for underwater propeller |
| CN112594327A (en) * | 2020-12-16 | 2021-04-02 | 中国船舶重工集团有限公司第七一0研究所 | Rubber vibration isolation device |
| 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 |
| CN115750679A (en) * | 2023-01-10 | 2023-03-07 | 西安航弓机电科技有限公司 | Vibration absorber for turboprop engine and performance detection method thereof |
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| CN104696427B (en) | 2017-12-12 |
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