CN105736170A - Aviation diesel engine piston combustion chamber and combustion system - Google Patents
Aviation diesel engine piston combustion chamber and combustion system Download PDFInfo
- Publication number
- CN105736170A CN105736170A CN201610181775.2A CN201610181775A CN105736170A CN 105736170 A CN105736170 A CN 105736170A CN 201610181775 A CN201610181775 A CN 201610181775A CN 105736170 A CN105736170 A CN 105736170A
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- China
- Prior art keywords
- combustion
- piston
- diesel oil
- groove
- oil machine
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 66
- 239000000446 fuel Substances 0.000 claims abstract description 27
- 239000002283 diesel fuel Substances 0.000 claims description 23
- 239000007921 spray Substances 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 4
- 238000004880 explosion Methods 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 7
- 238000002347 injection Methods 0.000 description 5
- 239000007924 injection Substances 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000012827 research and development Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 235000019621 digestibility Nutrition 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003502 gasoline Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002372 labelling Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
Classifications
-
- 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
- F02F3/00—Pistons
- F02F3/26—Pistons having combustion chamber in piston head
Abstract
The invention discloses an aviation diesel engine piston combustion chamber and a combustion system. The aviation diesel engine piston combustion chamber comprises a cylinder cover and a cylinder barrel, wherein a piston is arranged in the cylinder barrel; a cavity of the combustion chamber is formed between the top of the piston and the cylinder cover; a combustion chamber concave pit is formed in the top of the piston; a groove is formed in the top of the piston and is located around the combustion chamber; and the groove is located on the outer side of the combustion chamber pit. The requirements of high power per liter, relatively low explosion pressure, engine weight and low effective brake specific fuel consumption during high-speed high-load operation of an aviation diesel engine can be met.
Description
Technical field
The present invention relates to technical field of engines, especially relate to a kind of aviation diesel oil machine piston combustion bowl and combustion system.
Background technology
Announcement along with country's " suggestion about the in-depth low altitude airspace reform of management system " and " navigation aviation flight task examination & approval and administrative provisions ", domestic navigation industry size gradually forms, it is the grand strategy opportunity catching this national strategy new industry that enterprise is equipped in each navigation, greatly develop the full industrial chain of navigation, cultivate growth and face sky industry.Wherein one of navigation core industry aero-engine is also paid attention to day by day.
At present, small-sized aviation piston engine is gasoline engine mostly, and the piston-engined research and development of small-sized Heavy End Aviation Fuel only reside within the demonstration stage；And external own through achieving many achievements in research with the piston-engined research and development of small-sized Heavy End Aviation Fuel and application aspect at unmanned plane, some small-sized Heavy End Aviation Fuel piston engines have been put in the middle of practical application.Four reciprocating piston diesel engines have relatively low fuel consumption, excellent high-level performance and higher reliability；Fuel tolerance is strong simultaneously, and fuel stores safe and easy acquisition, and the application that diesel engine is applied on long voyage, High aititude unmanned plane in navigation is more and more extensive.
Owing to power to weight ratio pursued by small-sized aviation diesel oil machine, at a high speed such as 3500-4000r/min time, being obviously prolonged in crank angle injection time, oil injection duration reaches 35 DEG C of more than A；And in order to reduce diesel engine quality, restriction maximum outbreak pressure, cause that injection advance angle is limited, so cause aviation diesel oil machine after upper 15 DEG C of A also in a large amount of oil spouts, now piston is substantially descending, if adopt conventional relative aperture and footpath deeply than ω shape combustor, a large amount of fuel are sprayed onto wall and clearance piston-top surface on the upside of piston, increase drops in effective specific fuel consumption, then affects aviation flight mileage.
Summary of the invention
Not enough for prior art, the technical problem to be solved is to provide a kind of aviation diesel oil machine piston combustion bowl and combustion system, to reach active balance diesel engine purpose of fuel consumption and maximum outbreak pressure when the high power per liter operating mode of high speed.
In order to solve above-mentioned technical problem, the technical solution adopted in the present invention is:
A kind of aviation diesel oil machine piston combustion bowl, including cylinder cap and cylinder barrel, is provided with piston in described cylinder barrel, the cavity of combustor is formed between described top land and cylinder cap, described top land is provided with combustion recess, and edge of combustion chamber top land is provided with groove, and groove is positioned at outside combustion recess.
Described combustion recess is ω type pit, and whole combustion recess is symmetrical about piston axis.
Described groove is oblique groove, passes through arc transition between oblique groove and combustion recess.
Described combustion recess center is provided with boss, and boss diameter is 4.0～5.0mm, and the table top of boss is 4.5～5.5mm to the distance between piston-top surface.
The bottom of described combustion recess is pit circular arc, and pit arc diameter is 6.3～7.0mm.
Angle between groove oblique line and the piston-top surface in the bottom land cross section of described oblique groove is 22～28 °.
Described boss both sides adopt straight line to be connected with combustion recess bottom section, and between straight line and piston axis, angle is 55～60 °.
A kind of combustion system with described aviation diesel oil machine piston combustion bowl, described cylinder cap is provided with fuel injector, and the spray cone angle of fuel injector is 148～155 °.
Including air intake duct, described air intake duct adopts helical intake and tangential air flue combination.
The swirl ratio of described air intake duct is 1.6～1.8.
The present invention compared with prior art, requires high power per liter, relatively low explosion pressure and engine weight to require and relatively low effective fuel oil digestibility demand when having the advantage that and can reach to meet the operation of aviation diesel oil machine high-speed high-load；Burning highly effective, evades the aviation diesel oil machine fuel oil seriously rebuffed problem of high power to weight ratio, and active balance aviation diesel oil machine is the relation of fuel consumption and maximum outbreak pressure when high speed high power per liter operating mode.
Accompanying drawing explanation
Below the content expressed by each width accompanying drawing of this specification and the labelling in figure are briefly described:
Fig. 1 is combustor sectional view of the present invention.
Fig. 2 is combustor key parameter schematic diagram of the present invention.
Fig. 3 is diesel engine of the present invention After Top Center 20 DEG C of A fuel oil injection schematic diagrams.
Fig. 4 is Fig. 3 combustor groove close-up schematic view.
Fig. 5 is aviation diesel oil machine combustion system top view of the present invention.
In figure: 1. cylinder cap, 2. piston-top surface, 3. fuel injector, 4. oil spout oil bunch, 5. groove, 6. groove oblique line, 7. cylinder barrel, 8. piston, 9. combustion recess, 10. boss both sides straight line, 11. boss, 12. pit circular arcs, 13. transition arcs.
Detailed description of the invention
Below against accompanying drawing, by the description to embodiment, the specific embodiment of the present invention is described in further detail.
As shown in Figures 1 to 5, this aviation diesel oil machine piston combustion bowl and combustion system, including cylinder cap 1 and cylinder barrel 7, piston 8 it is provided with in cylinder barrel 7, forming the cavity of combustor between top land and cylinder cap, top land is provided with combustion recess 9, and edge of combustion chamber top land is provided with groove 5, groove is positioned at outside combustion recess, and cylinder cap 1 is provided with fuel injector 3.
Combustion recess 9 is positioned at piston crown, and combustion recess is ω type pit, and whole combustion recess is symmetrical about piston axis, and ω type pit is totally straight mouth shape or somewhat extends out state.
Setting up a groove 5 at combustor outer openings place, groove is oblique groove, is connected by transition arc 13 between oblique groove with combustion recess.Angle α between groove oblique line 6 and the piston-top surface in the bottom land cross section of oblique groove is 22～28 °.
The relative aperture of the opening of whole combustor cavity is 0.60～0.70, and footpath ratio deeply is for 0.158～0.175；Combustion recess center is provided with boss 11, boss 11 diameter DmBeing 4.0～5.0mm, the table top of boss is to the distance T between piston-top surface 2mIt is 4.5～5.5mm.The bottom of combustion recess is pit circular arc, and pit circular arc 12 diameter 2 × R is 6.3～7.0mm.Boss both sides adopt straight line to be connected with combustion recess bottom section, angle between boss both sides straight line 10 and piston axisIt it is 55～60 °.Being straight line with combustion recess side cross-section bottom combustion recess, the angle beta between this straight line and piston-top surface is 100～110 °.
Cylinder cap 1 is provided with fuel injector 3, and the spray orifice of fuel injector 3 is 6-7, and fuel injector central vertical is arranged, the spray cone angle δ of fuel injector is 148～155 °.
Combustion system of diesel engine adopts Four valve structure, air inlet and each two of exhaust valve, and air intake duct adopts spiral and tangential air flue combination；Multiple orifice nozzle vertical centre is arranged.Aviation diesel oil machine adopts four air valve organization, fuel injector can be arranged vertically in the middle of four valves, at this moment the combustor axial line on piston top, cylinder centerline overlap with fuel injector axial line, the each spray orifice of fuel injector is equal to the distance of combustion chamber wall surface, oil spout oil bunch 4 is uniform along combustion chamber periphery, along cylinder-bore axis direction, the drop point site on chamber wall is in sustained height to oil bundle, it is possible to the distance being stretched out cylinder head bottom surface by the conical surface angle between change spray orifice and fuel injector head is adjusted.
Secondly, air intake duct adopts spiral and tangential air flue combination, and in cylinder, eddy current retentivity is good；Whole combustor is symmetrical about piston axis, it is to avoid combustor biasing causes that intake swirl decay is very fast, reduces swirl ratio demand, then improves Flow coefficient of inlet, improve charge, reduces supercharger according to patience.Simultaneously, whole air intake duct forms swirl ratio 1.6～1.8, it is slightly less than face operating mode diesel engine for automobile same level swirl ratio, owing to circulation and the operating mode of climbing of aviation diesel oil machine are all high-speed high-load, now engine speed is in 3500～4000r/min, with conventional diesel, swirl ratio can reduce by 0.2～0.4, reduces cooling loss.
By Proper Match fuel injection parameter, Four valve structure and chamber structure parameter, can effectively evading the bigger aviation diesel oil machine fuel oil of power to weight ratio seriously rebuffed problem, active balance diesel engine is fuel consumption and maximum outbreak pressure relation when high speed high power per liter operating mode.
Above in conjunction with accompanying drawing, the present invention is exemplarily described; the obvious present invention implements and is not subject to the restrictions described above; as long as have employed the design of the present invention and the improvement of various unsubstantialities that technical scheme carries out; or the not improved design by the present invention and technical scheme directly apply to other occasion, all within protection scope of the present invention.
Claims (10)
1. an aviation diesel oil machine piston combustion bowl, including cylinder cap and cylinder barrel, it is provided with piston in described cylinder barrel, the cavity of combustor is formed between described top land and cylinder cap, it is characterized in that: described top land is provided with combustion recess, edge of combustion chamber top land is provided with groove, and groove is positioned at outside combustion recess.
2. aviation diesel oil machine piston combustion bowl as claimed in claim 1, it is characterised in that: described combustion recess is ω type pit, and whole combustion recess is symmetrical about piston axis.
3. aviation diesel oil machine piston combustion bowl as claimed in claim 1, it is characterised in that: described groove is oblique groove, passes through arc transition between oblique groove and combustion recess.
4. aviation diesel oil machine piston combustion bowl as claimed in claim 1, it is characterised in that: described combustion recess center is provided with boss, and boss diameter is 4.0～5.0mm, and the table top of boss is 4.5～5.5mm to the distance between piston-top surface.
5. aviation diesel oil machine piston combustion bowl as claimed in claim 1, it is characterised in that: the bottom of described combustion recess is pit circular arc, and pit arc diameter is 6.3～7.0mm.
6. aviation diesel oil machine piston combustion bowl as claimed in claim 3, it is characterised in that: the angle between groove oblique line and the piston-top surface in the bottom land cross section of described oblique groove is 22～28 °.
7. aviation diesel oil machine piston combustion bowl as claimed in claim 5, it is characterised in that: described boss both sides adopt straight line to be connected with combustion recess bottom section, and between straight line and piston axis, angle is 55～60 °.
8. one kind has the combustion system of aviation diesel oil machine piston combustion bowl as described in any one of claim 1 to 7, it is characterised in that: described cylinder cap is provided with fuel injector, and the spray cone angle of fuel injector is 148～155 °.
9. combustion system as claimed in claim 8, it is characterised in that: including air intake duct, described air intake duct adopts helical intake and tangential air flue combination.
10. combustion system as claimed in claim 9, it is characterised in that: the swirl ratio of described air intake duct is 1.6～1.8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610181775.2A CN105736170A (en) | 2016-03-28 | 2016-03-28 | Aviation diesel engine piston combustion chamber and combustion system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610181775.2A CN105736170A (en) | 2016-03-28 | 2016-03-28 | Aviation diesel engine piston combustion chamber and combustion system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105736170A true CN105736170A (en) | 2016-07-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610181775.2A Pending CN105736170A (en) | 2016-03-28 | 2016-03-28 | Aviation diesel engine piston combustion chamber and combustion system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105736170A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762100A (en) * | 2016-11-29 | 2017-05-31 | 奇瑞汽车股份有限公司 | A kind of aviation diesel oil machine offset piston combustion chamber and its combustion system |
| CN109339936A (en) * | 2018-10-30 | 2019-02-15 | 中国北方发动机研究所(天津) | A kind of blast groove type combustion chamber suitable for straight air flue combustion system |
| CN114183235A (en) * | 2022-02-14 | 2022-03-15 | 潍柴动力股份有限公司 | Internal combustion engine |
| CN114526151A (en) * | 2022-04-22 | 2022-05-24 | 潍柴动力股份有限公司 | Combustion chamber and diesel engine |
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| CN2497066Y (en) * | 2001-08-29 | 2002-06-26 | 昆明云内动力股份有限公司 | Shaped direct-injection diesel engine |
| CN2913638Y (en) * | 2006-07-06 | 2007-06-20 | 广西玉柴机器股份有限公司 | Single-cylinder four-spiracle diesel engine air flue |
| CN101984244A (en) * | 2010-11-11 | 2011-03-09 | 东风朝阳柴油机有限责任公司 | Communicated composite inlet channel system for four-valve diesel engine |
| CN101985896A (en) * | 2010-11-15 | 2011-03-16 | 东风朝阳柴油机有限责任公司 | Diesel engine combustion chamber with concave-convex structure |
| CN201810431U (en) * | 2010-09-20 | 2011-04-27 | 广西玉柴机器股份有限公司 | Diesel engine intake duct |
| CN204082363U (en) * | 2014-02-12 | 2015-01-07 | 第一拖拉机股份有限公司 | A kind of diesel engine piston combustion chamber |
-
2016
- 2016-03-28 CN CN201610181775.2A patent/CN105736170A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2497066Y (en) * | 2001-08-29 | 2002-06-26 | 昆明云内动力股份有限公司 | Shaped direct-injection diesel engine |
| CN2913638Y (en) * | 2006-07-06 | 2007-06-20 | 广西玉柴机器股份有限公司 | Single-cylinder four-spiracle diesel engine air flue |
| CN201810431U (en) * | 2010-09-20 | 2011-04-27 | 广西玉柴机器股份有限公司 | Diesel engine intake duct |
| CN101984244A (en) * | 2010-11-11 | 2011-03-09 | 东风朝阳柴油机有限责任公司 | Communicated composite inlet channel system for four-valve diesel engine |
| CN101985896A (en) * | 2010-11-15 | 2011-03-16 | 东风朝阳柴油机有限责任公司 | Diesel engine combustion chamber with concave-convex structure |
| CN204082363U (en) * | 2014-02-12 | 2015-01-07 | 第一拖拉机股份有限公司 | A kind of diesel engine piston combustion chamber |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762100A (en) * | 2016-11-29 | 2017-05-31 | 奇瑞汽车股份有限公司 | A kind of aviation diesel oil machine offset piston combustion chamber and its combustion system |
| CN106762100B (en) * | 2016-11-29 | 2018-10-26 | 奇瑞汽车股份有限公司 | A kind of aviation diesel oil machine offset piston combustion chamber and its combustion system |
| CN109339936A (en) * | 2018-10-30 | 2019-02-15 | 中国北方发动机研究所(天津) | A kind of blast groove type combustion chamber suitable for straight air flue combustion system |
| CN109339936B (en) * | 2018-10-30 | 2021-03-16 | 中国北方发动机研究所(天津) | Flow guide groove type combustion chamber suitable for straight gas channel combustion system |
| CN114183235A (en) * | 2022-02-14 | 2022-03-15 | 潍柴动力股份有限公司 | Internal combustion engine |
| CN114183235B (en) * | 2022-02-14 | 2022-04-19 | 潍柴动力股份有限公司 | Internal combustion engine |
| CN114526151A (en) * | 2022-04-22 | 2022-05-24 | 潍柴动力股份有限公司 | Combustion chamber and diesel engine |
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Application publication date: 20160706 |
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| RJ01 | Rejection of invention patent application after publication |