CN109026977A - A kind of small-sized aviation piston engine rises disconnected formula connecting rod - Google Patents
A kind of small-sized aviation piston engine rises disconnected formula connecting rod Download PDFInfo
- Publication number
- CN109026977A CN109026977A CN201811130724.2A CN201811130724A CN109026977A CN 109026977 A CN109026977 A CN 109026977A CN 201811130724 A CN201811130724 A CN 201811130724A CN 109026977 A CN109026977 A CN 109026977A
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- Prior art keywords
- connecting rod
- expansion
- hole
- small
- oil
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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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C7/00—Connecting-rods or like links pivoted at both ends; Construction of connecting-rod heads
- F16C7/02—Constructions of connecting-rods with constant length
- F16C7/023—Constructions of connecting-rods with constant length for piston engines, pumps or the like
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
Abstract
本发明公开了一种小型航空活塞发动机涨断式连杆，由连杆端盖和连杆组成；连杆结构简单，连杆一端为连杆大端头，另一端为连杆小端头，连杆小端头设有小圆孔，连杆大端头与连杆端盖通过螺栓连接成大圆孔。连杆端盖位于连杆大端头端部，连杆大端头的两侧对称有凸台，凸台上的涨断断面中间开有涨断孔，且位于涨断孔的对称位置设有引裂用的涨断槽，涨断槽相对于涨断断面对称设置，涨断槽在涨断加工时形成初始断裂源；涨断时无须对大圆孔施加机械力。连杆结构紧凑、工艺性好,优化的结构使连杆涨断后外表面缺损减少，实现调质合金钢连杆的涨断，连杆涨断合格率高、变形小且使用便捷，便于组织小型航空活塞发动机结构，拓宽使用范围。
The invention discloses a small-sized aviation piston engine expansion-break connecting rod, which is composed of a connecting rod end cover and a connecting rod; The small end of the connecting rod is provided with a small round hole, and the large end of the connecting rod and the end cover of the connecting rod are connected by bolts to form a large round hole. The connecting rod end cover is located at the end of the big end of the connecting rod. There are symmetrical bosses on both sides of the big end of the connecting rod. There is a splitting hole in the middle of the splitting section on the boss. The expansion groove used for cracking is set symmetrically with respect to the expansion section, and the expansion groove forms the initial fracture source during the expansion process; there is no need to apply mechanical force to the large round hole when the expansion is broken. The connecting rod has a compact structure and good workmanship. The optimized structure reduces the defects of the outer surface after the connecting rod is broken, and realizes the breaking of the quenched and tempered alloy steel connecting rod. Aviation piston engine structure, broaden the scope of use.
Description
Technical field
The present invention relates to aviation piston engine technical fields, specifically, being related to a kind of small-sized aviation piston engine
Rise disconnected formula connecting rod.
Background technique
Connecting rod is one of the critical moving components of small-sized piston formula aero-engine, carries the direction of transfer for changing power
With the function of mode.Opposite ordinary piston engine, the operating condition of aviation piston engine connecting rod is more harsh, worked
Subject continuous up to more than 90~120 times high-frequency periodic shock power, inertia force and bending forces per second in journey, it is necessary to have
Have high reliability, stability, fatigue performance and rigidity, intensity, toughness and it is light-weight, structure is simple, craftsmanship is good
Good condition.20 discipline the nineties, connecting rod cracking technology grow up as a new process in auto industry developed country,
Fundamentally change conventional linkage processing method.But the technology is routinely only used for non-hardened and tempered steel material, reason is
It is difficult to control the structure of plane of disruption when quenched steel alloy rises disconnected；Meanwhile sliding axle is used with the large and small head bore of common engine connecting rod
It is different to hold i.e. bearing bush structure, small-sized piston formula aero-engine generally uses rolling bearing, and the large and small head bore of connecting rod will also be as rolling
The outer ring raceway of dynamic bearing, thus have requirements at the higher level to form accuracy and strong, hardness, i.e., large and small head bore inner wall requires high hard
Degree is high-intensitive, on the outside of large and small head bore then as connecting rod shank, it is desirable that soft high tenacity and rigidity.Therefore, traditionally small
Type piston aviation engine uses always monoblock type connecting rod to combine with split type crankshaft, and still, this crankshaft structure makes crankshaft
Bearing capacity, shear resistance are poor so that engine is difficult to carry the impact of 3g or more acceleration, seriously limit it is all kinds of nobody
The landing mode and use scope of aircraft.
Patent of invention CN103939454B discloses " a kind of engine cracking connection rod and its processing method "；In patent CN
205101383 U propose " a kind of engine cracking connection rod "；Disclose that " one kind rises disconnection in 203585055 U of patent CN
Bar ".What above-mentioned patent was proposed rise, and cracking connecting rod is all by way of big end hole and its end face open up and rise by fault trough, and in major part
Apply mechanical force in hole outward, make the fault trough fracture of rising that connecting rod is concentrated from stress and intensity is minimum, which is suitable in connecting rod
The structure type of bearing shell, bushing is set in big end hole, and crank pin end pore bus is incomplete continuous cylindrical surface, Bu Nengzuo
For needle bearing outer rollaway nest；And the material of connecting rod is also Micro Alloying alloy steel material.Connect provided by above-mentioned patented technology
Rod structure will make tie rod holes be also easy to produce shape distortion and mechanical stress by imposing mechanical external force to major part hole wall when rising disconnected,
To influence the reliability used and durability.
Summary of the invention
In order to avoid the shortcomings of the prior art, the present invention proposes that a kind of rise disconnected formula of small-sized aviation piston engine connects
Bar；This rises, and disconnected formula link mechanism is simple, intensity is high, connecting rod tip head is provided with cracking hole, and setting, which is drawn, in cracking hole splits
Rise fault trough, need not apply mechanical force to big hole when rising disconnected；Link mechanism is rigidly strong, light-weight and good manufacturability, rise disconnected qualification
Rate is high, deformation is small and easy to use.
The technical solution adopted by the present invention to solve the technical problems is: including connecting rod end cap, connecting rod, cracking hole, rise it is disconnected
Slot, bolt, oil groove, reinforcing rib, big end oilhole, small end oilhole, described connecting rod one end are connecting rod tip head, and the other end is that connecting rod is small
End, wrist-pin end of connecting rod head are provided with small sircle hole, and composition big hole, connecting-rod head is bolted in connecting rod tip head and connecting rod end cap
Lid is located at connecting rod tip cephalic par, and symmetrically there are boss, rising absolutely on connecting rod tip head boss in the two sides of the connecting rod tip head
Face intermediate symmetry is provided with cracking hole, and the symmetric position for being located at cracking hole is equipped with several fault troughs that rise, and the fault trough that rises is relative to rising absolutely
Face is symmetrical arranged, and the fault trough that rises forms initial collapse source when rising by disconnected processing；
The cracking hole of the connecting rod tip head is symmetrical arranged with link centerline, and the cracking hole on connecting rod tip head is cone
Hole or straight hole, cracking hole radius is consistent with the disconnected section width that rises, the center line and connecting rod tip head two of the connecting rod tip head
The center line of the cracking hole of side, the center line for the fault trough that rises and the face absolutely of rising is overlapped；
Big end oilhole and small end oilhole, roundlet are respectively equipped with close to the opposite side of small sircle hole and big hole on the connecting rod
Hole and big hole top are respectively equipped with the oil groove with small end oilhole and the perforation of big end oilhole；The connecting rod is connect with connecting rod tip head
Position is equipped with reinforcing rib.
The fault trough that rises is v-shaped structure, and the fault trough angle that rises is 40~60 °, and the fault trough groove depth that rises is 0.4~0.9mm.
Multiple oil grooves are respectively arranged on the end face of the connecting rod tip head and connecting rod end cap, oil groove is equal with big hole center
Cloth, one of them is located on the center line of connecting rod tip head, and oil groove section is arc, and the central angle of oil groove is 120 °, and oil groove is wide
Degree is 4~5mm, and oil groove depth is 0.5~0.8mm.
The material of the connecting rod and connecting rod end cap is quenched steel alloy, and connecting rod and connecting rod end cap locally use carburizing or nitriding
Processing.
The connecting rod cross section is I-shaped.
Beneficial effect
A kind of small-sized aviation piston engine proposed by the present invention rises disconnected formula connecting rod, and the disconnected formula link mechanism that rises is simple, strong
Degree is high, efficiently solves the broken face structure problem absolutely that rises of quenched alloyed steel linkage rod, connecting rod tip head is provided with cracking hole,
The fault trough that rises split is drawn in setting in cracking hole, need not apply mechanical force to big hole when rising disconnected；So that connecting rod cracking becomes more
It is easy, the structure of optimization reduces outer surface defect after connecting rod cracking, realizes that rising for quenched alloyed steel linkage rod is disconnected, convenient for group hair-weaving
Motivation structure has widened the use scope of small-sized aviation piston engine.
The small-sized aviation piston engine of the present invention rises disconnected formula connecting rod, and the frame mode of cracking hole and the fault trough that rises, which reduces, to rise
Face forced area absolutely makes disconnected power reduction of rising, so that defect size reduction of having no progeny of rising；When rising disconnected due to connecting rod big hole not by
Power reduces the deformation of connecting rod tip head, improves the quality on joint surface, makes connecting rod bearing capacity, anti-shear ability and assembly matter
Amount increases substantially；The inner hole lubricant effect of the large and small end of connecting rod enhances, and improves efficiency.
The small-sized aviation piston engine of the present invention rises disconnected formula connecting rod, and link mechanism is compact, intensity is high, rigidity is good, light-weight
And good manufacturability, the disconnected qualification rate of rising are high, deformation is small and easy to use, and product reliability is effectively promoted.
Detailed description of the invention
A kind of small-sized aviation piston engine of the present invention disconnected formula connecting rod that rises is made into one with embodiment with reference to the accompanying drawing
Step is described in detail.
Fig. 1 is that the small-sized aviation piston engine of the present invention rises disconnected formula connecting rod schematic diagram.
Fig. 2 is connecting rod of the invention and connecting rod end cap structural schematic diagram.
Fig. 3 is connecting rod tip head and cracking hole cross-sectional view of the structure of the invention.
Fig. 4 be connecting rod tip head of the invention, bolt hole, cracking hole partial structural diagram.
Fig. 5 is connecting rod cross section view of the invention.
In figure
1. 5. small sircle hole of connecting rod end cap 2. connecting rod tip head, 3. connecting rod, 4. wrist-pin end of connecting rod head, 6. big hole 7. rises disconnected
9. bolt of fault trough, 10. oil groove 11. that rises of hole 8. rises 12. reinforcing rib of face, 13. big end oilhole, 14. small end oilhole absolutely
Specific embodiment
The present embodiment is that a kind of small-sized aviation piston engine rises disconnected formula connecting rod；It is to be provided for small-sized aviation piston engine
A kind of quenched alloy steel material the disconnected formula link mechanism that rises.
Refering to fig. 1~Fig. 5, the small-sized aviation piston engine of the present embodiment rise disconnected formula connecting rod, big by connecting rod end cap 1, connecting rod
End 2, connecting rod 3, wrist-pin end of connecting rod head 4, small sircle hole 5, big hole 6, cracking hole 7, the fault trough 8 that rises, bolt 9, oil groove 10, face absolutely of rising
11, reinforcing rib 12, big end oilhole 13, small end oilhole 14 form；Wherein, 3 one end of connecting rod is connecting rod tip head 2,3 other end of connecting rod
For wrist-pin end of connecting rod head 4, wrist-pin end of connecting rod head 4 is provided with small sircle hole 5, and connecting rod tip head 2 and connecting rod end cap 1 pass through 9 connection group of bolt
At big hole 6, connecting rod end cap 1 is located at 2 end of connecting rod tip head.Symmetrically there are boss, connecting rod tip head in the two sides of connecting rod tip head 2
11 intermediate symmetry of face absolutely that rises on 2 boss is provided with cracking hole 7, and the symmetric position for being located at cracking hole 7 is equipped with several fault troughs that rise
8, the fault trough 8 that rises is symmetrical arranged relative to face 11 absolutely of rising, and the fault trough 8 that rises forms initial collapse source when rising by disconnected processing.Connecting rod tip
First 2 cracking hole 7 is symmetrical arranged with link centerline；Cracking hole 7 on connecting rod tip head 2 is processed as taper hole or straight hole, rises
Disconnected 7 radius of hole is consistent with 11 width of face absolutely that rises；The intensity that will not influence connecting rod tip head 2 is arranged in the size, and can optimize
Rise section, reduces the basal area that rises, reduces the disconnected difficulty that rises, guarantees the disconnected effect that rises.The center line and connecting rod tip head of connecting rod tip head 2
The center line of the cracking hole 7 of 2 two sides, the center line for the fault trough 8 that rises and the face absolutely of rising is overlapped.The fault trough 8 that rises is v-shaped structure, and rise fault trough 8
Angle is 40~60 °, and 8 groove depth of fault trough that rises is 0.4~0.9mm.In the present embodiment, two angle values of same root connecting rod answer one
It causes, left-right deviation is not more than 1 °, and groove depth is also consistent, and deviation is not more than 0.15；The V-arrangement rise fault trough formation initial collapse source
It can guarantee the disconnected effect that rises, moreover, the depth of two fault troughs 8 that rise is identical and linear structure, it is ensured that big hole two when rising disconnected
It holds while being broken, and reduce deformation, improve yield rate.
In the present embodiment, the cross section of connecting rod 3 be it is I-shaped, to enhance rigidity and mitigate weight.The I-shaped of 3 body of rod of connecting rod
Type groove both ends are respectively equipped with small end oilhole 14 and big end oilhole 13, small sircle hole close to the opposite side of small sircle hole 5 and big hole 6
5 and 6 top of big hole be respectively equipped with the oil groove to connect with small end oilhole 14 and big end oilhole 13；Connecting rod tip head 2 and connecting rod
Multiple oil grooves 10 are respectively arranged on the end face of end cap 1, oil groove 10 is uniformly distributed with big hole center, and one of oil groove 10, which is located at, to be connected
On the center line of the big end 2 of bar, 10 section of oil groove is arc, and the central angle of oil groove is 120 °, and oil groove width is 4~5mm, oil groove
Depth is 0.5~0.8mm.When work, lubricating oil enters in big hole 6 from 6 two sides oil groove 10 of big hole and top oil groove,
Big-end bearing is lubricated and is cooled down, under the action of crankshaft high-speed operates generated centrifugal inertial force, the profit of big hole 6
Lubricating oil is lubricated little-end bearing into 5 inner hole of small sircle hole by big end oilhole 13,3 shaft of connecting rod, small end oilhole 14, to increase
Strong lubricating effect reduces friction loss and cooling bearing.
In the present embodiment, connecting rod 3 and 2 connecting portion of connecting rod tip head are equipped with reinforcing rib 12.Connecting rod 3 and connecting rod end cap 1
Material is quenched steel alloy, and connecting rod 3 and 1 part of connecting rod end cap use carburizing or Nitrizing Treatment.To realize that face 11 absolutely of rising is controllable
As a result brittle failure, cracking hole 7,11 outer surface portions of face absolutely that rise of rise fault trough 8 and boss carry out Surface thermo-chemical treatment, with
It improves it and is conducive to rise disconnected surface hardness and brittleness.
In the present embodiment, material therefor 18Cr2Ni4W, 20CrMnMo, 20CrNiMo and 20CrMoA, and by using and
Process requirements are aided with carburizing to part and high-frequency quenching is handled；Or use material for 30Cr3Mo, 38CrMoAl, 42CrMoA, and
Nitrogen treatment is aided with to part with process requirements by using.Increase connecting rod by service life, improves the performance of engine, raising is risen
Breaking process and reduction contraction percentage of area controlled fracturing blasting face structure.
Claims (5)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811130724.2A CN109026977A (en) | 2018-09-27 | 2018-09-27 | A kind of small-sized aviation piston engine rises disconnected formula connecting rod |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811130724.2A CN109026977A (en) | 2018-09-27 | 2018-09-27 | A kind of small-sized aviation piston engine rises disconnected formula connecting rod |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109026977A true CN109026977A (en) | 2018-12-18 |
Family
ID=64620642
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811130724.2A Pending CN109026977A (en) | 2018-09-27 | 2018-09-27 | A kind of small-sized aviation piston engine rises disconnected formula connecting rod |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109058280A (en) * | 2018-09-29 | 2018-12-21 | 西安爱生技术集团公司 | A kind of quenched steel alloy of small-sized piston engine rises cracking connecting rod and process for making |
| CN116164027A (en) * | 2023-02-22 | 2023-05-26 | 芜湖欧宝机电有限公司 | Connecting rod structure of piston type efficient compressor and assembling method thereof |
| CN117817062A (en) * | 2024-02-04 | 2024-04-05 | 浙江海骆航空科技有限公司 | Compressor blade cutting method and compressor blade for turbine containment test |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109058280A (en) * | 2018-09-29 | 2018-12-21 | 西安爱生技术集团公司 | A kind of quenched steel alloy of small-sized piston engine rises cracking connecting rod and process for making |
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| CN116164027A (en) * | 2023-02-22 | 2023-05-26 | 芜湖欧宝机电有限公司 | Connecting rod structure of piston type efficient compressor and assembling method thereof |
| CN117817062A (en) * | 2024-02-04 | 2024-04-05 | 浙江海骆航空科技有限公司 | Compressor blade cutting method and compressor blade for turbine containment test |
| CN117817062B (en) * | 2024-02-04 | 2025-04-25 | 浙江海骆航空科技有限公司 | Compressor blade cutting method for turbine containment test and compressor blade |
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Application publication date: 20181218 |