CN106870198B - Crankshaft main bearing cap and aviation piston engine - Google Patents
Crankshaft main bearing cap and aviation piston engine Download PDFInfo
- Publication number
- CN106870198B CN106870198B CN201710254613.1A CN201710254613A CN106870198B CN 106870198 B CN106870198 B CN 106870198B CN 201710254613 A CN201710254613 A CN 201710254613A CN 106870198 B CN106870198 B CN 106870198B
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- China
- Prior art keywords
- main bearing
- bearing cap
- piston engine
- bolt
- aviation piston
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- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F7/00—Casings, e.g. crankcases or frames
- F02F7/0021—Construction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F7/00—Casings, e.g. crankcases or frames
- F02F7/0002—Cylinder arrangements
- F02F7/0012—Crankcases of V-engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F7/00—Casings, e.g. crankcases or frames
- F02F7/0065—Shape of casings for other machine parts and purposes, e.g. utilisation purposes, safety
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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
- F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The crankshaft main bearing cover is in a step shape and is installed separately from a lower engine body, the crankshaft main bearing cover is connected with an upper engine body through bolts, impact on a crankshaft is transmitted to the main bearing cover when a piston reciprocates, the impact is transmitted to the upper engine body through the bolts and borne by the upper engine body, impact of alternating stress borne by the lower engine body is reduced, and the lower engine body is effectively protected from being broken due to high-cycle fatigue.
Description
Technical Field
The invention relates to a crankshaft main bearing cap and an aviation piston engine.
Background
The aviation piston engine uses heavy oil as fuel, has good economy, safe fuel transportation and easy acquisition, is listed as a scientific and technological plan in the thirteen-five period of the country after being developed and pressed, and has great application in military and civil use. China is beginning to develop the engine, but the information on the aspect is less disclosed at present.
In order to obtain a high power-weight ratio, the weight of an aircraft piston engine needs to be reduced as much as possible, the aircraft piston heavy oil engine mainly uses an opposed cylinder at present, a main bearing cap of the opposed cylinder is embedded and fixed in a lower engine body, so that impact generated during reciprocating motion of a piston can be directly transmitted to the main bearing cap, then the impact is acted on an opposed casing connected by a bolt through the main bearing cap, and the impact generated during working of the engine is borne by the casing and the bolt.
Disclosure of Invention
The invention aims to provide a crankshaft main bearing cap and an aviation piston engine, which can effectively prevent lower engine body fatigue and improve the fault-free running time and reliability of the engine.
The invention adopts the following technical scheme to realize the technical purposes: the utility model provides a bent axle main bearing cap, includes the main bearing cap body, the both sides and the bottom side of main bearing cap body be equipped with organism contact down, to the radial spacing supporting part of main bearing cap body, the upside middle part of main bearing cap body is equipped with the bearing mounting hole, the main bearing cap body is equipped with the bolt hole that is used for fixing on last organism at the bilateral symmetry of bearing mounting hole. The main bearing cap body is installed for the disconnect-type with organism down, the main bearing cap body contacts spacingly through supporting part and organism down, the main bearing cap body is fixed with last organism, through this kind of structure, make when engine during operation, vibration and impact transmission give the bent axle, and then transmit on the main bearing cap body, the impact and the vibration that the main bearing cap body bore transmit for last organism through the bolt, thereby shift the impact and bear for last organism, make the organism only bear the slight vibration of engine operation down, reach the tired purpose of organism down, because last organism intensity is high, the structure size is big, and design strength is far greater than organism down, sufficient intensity factor of safety has, consequently can resist the high all fatigue that arouses by the impact completely, the impact of this kind of degree can not lead to the fact the influence to last organism, thereby organism under the effective protection, prevent down the organism because of high all fatigue fracture.
Furthermore, the two sides of the main bearing cap body are symmetrically provided with openings which are communicated with the bolt holes and facilitate bolt installation.
Furthermore, a lining is embedded in the bolt hole, and threads are arranged in the lining. The bush makes the bolt can not appear the clearance at the screw-in-process, prevents when the impact vibration of high frequency, to the impact force of bolt, and the bush also can bear certain shear stress in addition.
Furthermore, the bearing mounting hole upper surface of main bearing cap body is provided with the groove of being convenient for install the axle bush.
Further, the main bearing cap body is T-shaped. The structure can ensure the strength and the convenience of bolt installation.
An aviation piston engine comprises the crankshaft main bearing cap, an upper machine body and a lower machine body, wherein an opening matched with the crankshaft main bearing cap in size is formed in the lower machine body, the crankshaft main bearing cap is installed in the opening through a supporting portion, a bolt fixing hole corresponding to the position of a bolt hole of the crankshaft main bearing cap is formed in the upper machine body, and the crankshaft main bearing cap is fixed on the upper machine body through a bolt arranged in the bolt hole.
The aviation piston engine is a V-shaped layout aviation piston engine.
In conclusion, the invention can effectively prevent the lower engine body from fatigue and can improve the fault-free running time and reliability of the engine.
Drawings
FIG. 1 is a schematic view of the interior of an aviation piston engine having a V-configuration according to the present invention.
FIG. 2 is a schematic illustration of the installation of the main bearing caps of the crankshaft of the present invention.
FIG. 3 is a schematic illustration of an aircraft piston engine configuration according to the present invention.
FIG. 4 is a schematic illustration of the construction of the crankshaft main bearing cap of the present invention.
Implementation measures
The present invention will be described in more detail with reference to the accompanying drawings.
As shown in fig. 1 to 4, an aviation piston engine adopts a separated step-shaped main bearing cap body 8 mounted on a lower machine body 1, the main bearing cap body 8 is fixed on an upper machine body 10 through a first bolt 7 and a bushing 6, and the upper machine body 10 and the lower machine body 1 are fixed together through a second bolt 9. The engine adopts the V-shaped layout to reduce the installation size, and piston 4 links to each other with connecting rod 3, drives connecting rod 3 and moves down, and connecting rod 3 is connected together with bent axle 2. The crankshaft 2 is seated on the bearing 5, and the bearing 5 and the main bearing cap body 8 are fixed together to prevent relative movement between the bearing 5 and the main bearing cap body 8 during operation of the engine. The main bearing cap body 8 and the lower body 1 are not connected, and only sit on the lower body 1. The first bolts 7 serve the main function of connecting the main bearing cap body 8 and the upper housing 10, with bushings embedded in the bolt holes, filling the gaps between the bolts and the screw holes, to prevent any relative movement between the main bearing cap body 8 and the upper housing 10.
After gas pressure passes through the transmission, strike main bearing cap body 8 on, transmit first bolt 7 via main bearing cap body 8 on, and then transmit for last organism 10, because the design strength and the structure size of last organism 10 are far greater than organism 1 down, have sufficient intensity factor of safety, consequently can resist the high cycle fatigue that arouses by the impact completely.
The main bearing cap body 8 can effectively transmit the impact force in the rotation process of the crankshaft to the upper machine body 10 through the first bolt 7 and the bushing 6, and reduce the impact on the lower machine body 1 in the working process and the high-cycle fatigue caused by the impact
Referring to fig. 1, when the engine is operated, the explosive force generated by the instantly combusted gas directly acts on the top surface of the piston 4, the piston 4 is connected with the connecting rod 3 through a piston pin, the piston 4 moves downwards in the cylinder, and the connecting rod 3 pushes the crankshaft 2 to rotate, so that the engine outputs power and torque. Because there is not any restraint between disconnect-type main bearing cap body 8 and the organism 1 down, belong to two complete independent parts, vibration and impact transmit the bent axle, and then transmit to the main bearing cap body on, because the effect of first bolt 7 and bush 6 at this moment, main bearing cap body 8 and last organism 10 are tightly connected together, and only contact between with organism 1 down. The main bearing cap body 8 bears the impact and vibration mainly through first bolt 7 and bush 6 transmission for last organism, by high strength, the big last organism 10 of structure size bears, lower organism 1 is through bearing the slight vibration of engine in service, the bolt hole diameter of both sides is greater than the bolt on the main bearing cap body 8, and the slotted installation of the bearing bush of being convenient for of upper surface, there is the clearance between first bolt 7 and the main bearing cap body after this hole inserts, under long-term vibration and impact, the clearance may appear between main bearing cap body 8 and the last organism 10, consequently, the bush 6 that adopts high strength material to make is installed in the bolt hole, the inside screw thread of bush 6, first bolt 7 just can not appear any clearance at the wrong in-process, and when the impact vibration of high frequency, bush 6 can also bear certain shear stress.
Claims (6)
1. An aviation piston engine, characterized in that: the crankshaft main bearing cover comprises a main bearing cover body (8), supporting parts which are contacted with the lower machine body (1) and used for radially limiting the main bearing cover body (8) are arranged on the two sides and the bottom side of the main bearing cover body (8), bearing mounting holes are formed in the middle of the upper side of the main bearing cover body (8), and bolt holes used for being fixed on the upper machine body (10) are symmetrically formed in the two sides of the bearing mounting holes of the main bearing cover body (8);
the crankshaft main bearing cap is characterized in that an opening matched with the crankshaft main bearing cap in size is formed in the lower machine body (1), the crankshaft main bearing cap is installed in the opening through a supporting portion, bolt fixing holes corresponding to the positions of bolt holes of the crankshaft main bearing cap are formed in the upper machine body (10), and the crankshaft main bearing cap is fixed on the upper machine body (10) through bolts arranged in the bolt holes.
2. The aviation piston engine of claim 1, wherein: the aviation piston engine is in a V-shaped layout.
3. The aviation piston engine of claim 1, wherein: the two sides of the main bearing cap body (8) are symmetrically provided with openings which are communicated with the bolt holes and facilitate bolt installation.
4. An aviation piston engine as claimed in claim 1 or 3, wherein: a lining (6) is embedded in the bolt hole, and threads are arranged inside the lining (6).
5. An aviation piston engine in accordance with claim 4, wherein: the upper surface of the bearing mounting hole of the main bearing cap body (8) is provided with a groove (11) convenient for mounting a bearing bush.
6. An aviation piston engine in accordance with claim 5, wherein: the main bearing cap body (8) is T-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710254613.1A CN106870198B (en) | 2017-04-18 | 2017-04-18 | Crankshaft main bearing cap and aviation piston engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710254613.1A CN106870198B (en) | 2017-04-18 | 2017-04-18 | Crankshaft main bearing cap and aviation piston engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106870198A CN106870198A (en) | 2017-06-20 |
| CN106870198B true CN106870198B (en) | 2022-10-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710254613.1A Active CN106870198B (en) | 2017-04-18 | 2017-04-18 | Crankshaft main bearing cap and aviation piston engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN106870198B (en) |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB712307A (en) * | 1951-07-16 | 1954-07-21 | Bayerische Motoren Werke Ag | Crank shaft bearing, especially for combustion engines with cylinders arranged in-line |
| JP3741362B2 (en) * | 2001-05-17 | 2006-02-01 | 本田技研工業株式会社 | Oil pump mounting structure |
| JP3948272B2 (en) * | 2001-12-21 | 2007-07-25 | スズキ株式会社 | Engine bearing cap manufacturing method |
| CN201401233Y (en) * | 2009-04-27 | 2010-02-10 | 常柴股份有限公司 | V-type water-cooled diesel engine |
| CN103206252B (en) * | 2012-09-06 | 2015-09-16 | 祥天控股（集团）有限公司 | The control mechanism of variable multi-cylinder aerodynamic engine |
| CN104047758A (en) * | 2014-07-07 | 2014-09-17 | 广西玉柴机器股份有限公司 | Main bearing cover of engine |
| US9719461B2 (en) * | 2015-02-12 | 2017-08-01 | Ford Global Technologies, Llc | Bulkhead insert for an internal combustion engine |
| CN205064097U (en) * | 2015-08-05 | 2016-03-02 | 宁波市鄞州德来特技术有限公司 | Integrated morphology and internal -combustion engine of lower organism |
| CN205078357U (en) * | 2015-09-06 | 2016-03-09 | 常州市宝迅机械有限公司 | Diesel engine of diesel engine organism and applied this organism |
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2017
- 2017-04-18 CN CN201710254613.1A patent/CN106870198B/en active Active
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| Publication number | Publication date |
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| CN106870198A (en) | 2017-06-20 |
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