CN104131879A - Heat transfer surface structure of combustion chamber - Google Patents
Heat transfer surface structure of combustion chamber Download PDFInfo
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- CN104131879A CN104131879A CN201410375561.XA CN201410375561A CN104131879A CN 104131879 A CN104131879 A CN 104131879A CN 201410375561 A CN201410375561 A CN 201410375561A CN 104131879 A CN104131879 A CN 104131879A
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- Prior art keywords
- heat transfer
- reflection groove
- oblique
- groove
- firing chamber
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- 238000002485 combustion reaction Methods 0.000 title abstract description 29
- 239000000463 material Substances 0.000 claims abstract description 14
- 239000000446 fuel Substances 0.000 claims abstract description 12
- 238000010304 firing Methods 0.000 claims description 41
- 238000010438 heat treatment Methods 0.000 claims description 32
- 239000011159 matrix material Substances 0.000 claims description 19
- 239000007789 gas Substances 0.000 claims description 13
- 239000000470 constituent Substances 0.000 claims description 12
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 7
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 7
- 229910052799 carbon Inorganic materials 0.000 claims description 7
- 238000006555 catalytic reaction Methods 0.000 claims description 7
- 239000001257 hydrogen Substances 0.000 claims description 7
- 229910052739 hydrogen Inorganic materials 0.000 claims description 7
- 229910052703 rhodium Inorganic materials 0.000 claims description 7
- 229910010413 TiO 2 Inorganic materials 0.000 claims description 5
- 229910052697 platinum Inorganic materials 0.000 claims description 4
- 229910002091 carbon monoxide Inorganic materials 0.000 abstract description 4
- 239000004215 Carbon black (E152) Substances 0.000 abstract 1
- 238000010521 absorption reaction Methods 0.000 abstract 1
- 229930195733 hydrocarbon Natural products 0.000 abstract 1
- 150000002430 hydrocarbons Chemical class 0.000 abstract 1
- 239000000203 mixture Substances 0.000 description 9
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 5
- 239000001301 oxygen Substances 0.000 description 5
- 229910052760 oxygen Inorganic materials 0.000 description 5
- 230000005855 radiation Effects 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 229910052700 potassium Inorganic materials 0.000 description 3
- 229910052721 tungsten Inorganic materials 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 206010020843 Hyperthermia Diseases 0.000 description 1
- 238000013019 agitation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000036031 hyperthermia Effects 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000004663 powder metallurgy Methods 0.000 description 1
- 230000001932 seasonal effect Effects 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B23/00—Other engines characterised by special shape or construction of combustion chambers to improve operation
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a heat transfer surface structure of a combustion chamber. The heat transfer surface structure of the combustion chamber comprises a base body with a heated surface, multiple transverse reflection grooves transversely arranged in the heated surface and multiple inclined reflection grooves arranged in the heated surface in an inclined mode, a transverse load surface is located between every two adjacent transverse reflection grooves, an inclined load surface is located between every two adjacent inclined reflection grooves, and independent concave reflection curved surfaces are formed at the junctions of the transverse load surfaces and the inclined load surfaces. Certain included angles are formed between the transverse reflection grooves and the inclined reflection grooves. The transverse reflection grooves and the inclined reflection grooves are both provided with reflection curved surfaces, and the length direction of the transverse reflection grooves is perpendicular to the moving direction of high-speed high-temperature air flow. A heat transfer surface is made of function materials which are capable of catalyzing hydrocarbon fuel and H2O steam, high in heat resistance, low in heat absorption rate and high in structural intensity. The heat transfer surface structure of the combustion chamber reduces heat losses, lowers emission of CH, CO and NO, and improves heat efficiency in the mode of a certain surface structure and the function materials.
Description
Technical field
The present invention relates to a kind of firing chamber heat transfer surface structures, be specifically related to cylinder, cylinder head, valve, piston, the cylinder liner of combustion chambers of internal combustion engines and combustion chambers of internal combustion engines, more specifically, relate to the heat transfer surface structures having on the cylinder of firing chamber, cylinder head, valve, piston, cylinder-barrel surface and there is catalyzed carbon hydrogen fuel, catalysis H
2the functional material of O steam, high thermal resistance, low thermal absorptivity and high structural strength.
Background technique
In internal-combustion engine, firing chamber total heat transfer accounts for 32% left and right of total fuel combustion generation heat.Traditional combustion chambers of internal combustion engines radiative heat transfer amount of thinking accounts for the 0-7% of total amount of heat, in engineering, generally ignore now or adopt empirical correlation to calculate, inventor finds or has recognized that radiative heat transfer becomes the main heat transfer type in firing chamber in certain temperature range through studying for a long period of time.When chamber temperature is in the time that 1173K is above, its heat transmits form taking radiation as main, and hyperthermia radiation energy great majority concentrate on 1～5 mu m waveband, account for 90% of heat output, structure and surfacing composition Ni thereof, W, Mo, Ca, K, Pt, Rh, Ce0.75O
2zr0.25O
2, γ-A1
2o
3, TiO
2to combustion gas acting in conjunction, there is catalyzed carbon hydrogen fuel, catalysis H
2o steam, high thermal resistance, low thermal absorptivity, adjusts structural strength function, not yet has in the prior art for the surface structure of the present invention that reduces radiative heat transfer loss, CH, CO, NO discharge, the raising thermal efficiency.
Summary of the invention
In order to reduce thermal loss, reduce CH, CO discharge, coordinate burning tissue, to improve the thermal efficiency, the present invention aims to provide a kind of firing chamber heat transfer surface structures, and this surface structure reduces thermal loss to have the mode of certain surface structure, reduces CH, CO discharge, coordinates burning tissue, improves the thermal efficiency.
To achieve these goals, surface structure of the present invention is:
A kind of firing chamber heat transfer surface structures, its structural feature is to comprise
---matrix, it has heating surface;
---many are arranged on the horizontal reflection groove of lateral arrangement on heating surface, between adjacent two horizontal reflection grooves, are the lateral load faces as bearing structure;
---many are arranged on the oblique reflection groove of oblique layout on heating surface, between adjacent two oblique reflection grooves, are the oblique orientation load faces as bearing structure;
Described horizontal reflection groove and oblique reflection groove are in a certain angle; Described horizontal reflection groove and oblique reflection groove all have reflecting curved surface, and the length direction of described oblique reflection groove or laterally reflection groove is vertical with high-speed and high-temperature air motion direction;
The intersection of described lateral load face and oblique orientation load face is provided with independent spill reflecting curved surface;
Described matrix or its heating surface are by having catalyzed carbon hydrogen fuel, catalysis H
2the functional material of O steam, high thermal resistance, low thermal absorptivity and high structural strength is made.
High-speed and high-temperature air-flow of the present invention refers to that temperature is higher than 1173K, and speed is higher than the air-flow of 27m/s.
Thus, in the region of the heat that reflecting curved surface gathers e heating surface near, improved gas temperature herein, accelerate not fire the burning of composition, improved the combustion efficiency of mixed gas, reduced the discharge of CH, CO, improve the temperature of heating surface, reduced radiative heat transfer loss.Due to the laterally existence of reflection groove and oblique reflection groove, reduce high-speed and high-temperature air-flow area of contact, reduce high speed convection heat transfer loss.Due to the laterally existence of reflection groove and oblique reflection groove, increase the turbulent flow film micro area disturbance of heating surface high-speed and high-temperature air-flow, increase and do not fired the obtaining oxygen, obtain heat of composition, the combustion condition of chain reaction.Due to the laterally existence at the α angle of reflection groove and oblique reflection groove, for surface combustion tissue, the optimization etc. of firing chamber provide possibility.
The present invention is by having catalyzed carbon hydrogen fuel, catalysis H
2the firing chamber heat transfer surface structures that the material of O steam, high thermal resistance, low thermal absorptivity and high structural strength is made.
Be below further concrete structure of the present invention:
In order to improve the combustion efficiency of inflammable mixture, reduce thermal loss, the opening diameter d1 of described independent spill reflecting curved surface can be by d1=0.7C, degree of depth h1=1.1326C calculates, place-centric arranges at two plane of load center line intersection point places, in the time of calculated value d1≤1mm, independent reflecting curved surface is not set.
Width c=(0.017～0.333) A of described lateral load face or oblique orientation load face, wherein bearing structure maximum stress carrying width A=2mm～26mm.
Distance e=r-h=(0.3～1.3) h between focusing center's point of described reflecting curved surface and described lateral load face or oblique orientation load face, the wherein degree of depth h=of reflecting curved surface (0～1.618126) b, b is the groove width of horizontal reflection groove or oblique reflection groove, r is reflecting curved surface radius of curvature, b=(0.24975～0.4745) A; Wherein bearing structure maximum stress carrying width A=2mm～26mm.
Preferably, described reflecting curved surface is parabola.
As a kind of structural type of concrete application, the heating surface of described matrix is annular surface, and described horizontal reflection groove is circular groove, and described oblique reflection groove is spiral chute; Described spiral fluted pitch angle alpha will is by relation: tg α=Φ × p/ π d determines, wherein: d=h+2R, R is matrix curvature of curved surface radius, line is counted Φ=1～∞, pitch angle alpha will ∈ (0 °, 90 °); Described spiral fluted pitch is p=c+b, width c=(0.017～0.333) A of wherein said lateral load face or oblique orientation load face, described oblique reflection groove and laterally groove width b=(0.24975～0.4745) A of reflection groove; Bearing structure maximum stress carrying width A=2mm～26mm.This heat transfer structure can be used on the curved inner wall or outer surface of contact high-temperature high-speed airflow, as cylinder inner wall, and outer surface of piston.
As the structural type of the concrete application of another kind, the heating surface of described matrix is plane.Adjacent two horizontal reflection grooves layout that is parallel to each other in plane, adjacent two oblique reflection grooves layout that is parallel to each other, in horizontal, oblique reflection groove one vertical with air-flow, α angle is determined by combustion chambers burn tissue guide angle, (0 ° of α ∈, 90 °), this plane surface heat transfer structure application representative as: cylinder head.
As the structural type of the concrete application of another kind, the heating surface of described matrix is to change continuously curved surface or multistage radius of curvature curved surface, the length direction of a reflection groove in horizontal, oblique reflection groove is vertical with airflow direction, and another reflection groove forms curved surface annular groove or reflective trenches segmental arc centered by base structure center of surface.
The intersection of described oblique reflection groove or laterally reflection groove and described lateral load face or oblique orientation load face is fillet.
Feature of the present invention is also that the thickness of described functional material is 0.01mm～20mm, and its constituent and mass percent meet following relation:
Each constituent content sum is 100% above; Described w (Pt, Rh)=m
1(Pt)/m
2(Rh)=5/1.
Further constituent and the mass percent of preferred described functional material meet following relation:
In discharge in internal-combustion engine, the discharge of CH, CO is mainly derived from low temperature oxygen deprivation region, firing chamber internal surface is the keypoint part of low temperature (229 DEG C of left and right), oxygen deprivation, improving internal surface temperature, increasing air agitation, reduce CH, CO discharge is main theory foundation of the present invention, and adopting reflecting curved surface reflect focalization heat energy, increasing that reflective trenches reduces radiation and high-speed high-temperature gas area of contact, increase problem area air and do not fire that constituent fluctuation mixes is concrete structure of the present invention.
The present invention is directed to radiative heat transfer has proposed to set up reflecting curved surface, horizontal reflection groove, oblique reflection groove structure at combustor surface, in order to improve combustion chamber wall surface or near gas temperature, solve due to the low a large amount of generation CH of wall surface temperature, a CO effulent difficult problem, due to the raising of this temperature with reduced closely radiation surface area, radiative heat transfer loss is greatly reduced; Due to the high-temperature gas of high-speed motion in firing chamber and closely high speed area of contact minimizing, significantly reduced heat transfer by convection loss simultaneously; Increased again the disturbance of concave region unburned gas composition simultaneously, made unburned fuel composition obtain obtaining oxygen, obtain heat, the condition of chain reaction, make burning more abundant with cleaning.
The present invention is provided with lateral load face, oblique orientation load face structure for the heating surface that may carry, and makes the functions such as above-mentioned heat transfer and bearing function obtain good combination.
The present invention, for coordinating combustion chambers burn ground tissue, is provided with α helix angle structure parameter, and the General that makes to burn improves.
The present invention, by adjusting structural parameter b, c, h, e, α, can obtain the different surface structures that require.
The present invention is by chamber structure and surfacing composition Ni, W, Mo, Ca, K, Pt, Rh, Ce0.75O
2zr0.25O
2, γ-A1
2o
3, TiO
2; To combustion gas acting in conjunction, to unburned carbon hydrogen fuel wherein, H
2o steam has catalysis, can reduce CH, CO, NO discharge, improve the thermal efficiency, has high thermal resistance simultaneously, low thermal absorptivity, and high structural strength, adjusts its proportioning and can make material have adaptability.
Compared with prior art, the invention has the beneficial effects as follows: laterally in the scope of reflection groove, oblique reflection groove, near reflecting curved surface structure e heating surface, improve gas temperature, accelerate the burning that composition is not fired in firing chamber, improve the combustion efficiency of fuel, reduce the discharge of CH, CO, reduced radiative heat transfer loss.Laterally reflection groove, oblique reflection groove, reflecting curved surface structure decrease high-speed and high-temperature air-flow area of contact, reduced high speed convection heat transfer loss.The turbulent flow that laterally reflection groove, oblique reflection groove, reflecting curved surface structure have increased heating surface high-speed and high-temperature air-flow is in heating surface zone-perturbation, strengthened and do not fired the obtaining oxygen, obtain heat of composition, chain reaction condition, makes burning more fully cleaner.Surface combustion tissue, optimization etc. that laterally the α corner structure of reflection groove and oblique reflection groove is firing chamber provide may.Firing chamber heat transfer surface structures material has utilized combustion chamber high temperature heat energy cleverly, has reduced CH, CO, NO discharges usefulness, has improved the thermal efficiency.
Below in conjunction with drawings and Examples, the present invention is further elaborated.
Brief description of the drawings
Fig. 1 is the structural configuration schematic diagram of one embodiment of the invention;
Fig. 2 is A-A sectional view of Fig. 1;
Fig. 3 is B-B sectional view of Fig. 1;
Fig. 4 is C-C sectional view of Fig. 1;
Fig. 5 is firing chamber each several part pie graph;
Fig. 6 is chamber gas temperature and crank angle graph of a relation;
Fig. 7 is that firing chamber gas instantaneous temperature and crank angle launch graph of a relation;
Fig. 8 is that cylinder liner temperature is along axis distribution map;
Embodiment
Fig. 1～4 have schematically shown a kind of firing chamber heat transfer surface structures that is applied in high temperature and high speed gas flow, and this heating surface can be the firing chamber heating surfaces such as internal-combustion engine, combustion chambers of internal combustion engines, Thermal Equipment, instrument.May there is the comprehensive surface that has carrying mechanical load and friction to require in certain region in heating surface.
Fig. 1 is a firing chamber heating surface embodiment's structural layout plan.In figure, 1 is firing chamber heating surface matrix.On matrix 1, have the horizontal reflection groove 5 of many lateral arrangement and the oblique reflection groove 6 of many oblique layouts.Fig. 2 is horizontal reflection groove 5 or oblique reflection groove 6 sectional drawings.A-A cross-section structure is that reflecting curved surface is distributed in the lip-deep structure of heat transfer parts by groove form.The length direction of its reflective trenches is vertical or angled with main air motion direction.If when main air motion is turbulent flow, the length direction of reflective trenches is parallel with main mating face or the main processing datum of parts, or the curved surface annular groove or the reflective trenches segmental arc that centered by parts structure center of surface, form.
In the heat transfer surface structure of Fig. 1 firing chamber, label 2 is bearing structure intersection independence reflecting curved surface structure in the heat transfer surface structures of firing chamber.Its opening diameter d1 can be by d1=0.7C, and degree of depth h1=1.1326C calculates, and place-centric arranges at two plane of load center line intersection point places, in the time of calculated value d1≤1mm, independent reflecting curved surface is not set.
Determining of reflecting curved surface focusing center's point and reflecting curved surface: in Fig. 4, reflecting curved surface focusing center's point is determined with bearing structure surface distance e's: e=r-h=(0.3～1.3) h; H=(0～1.618126) b; Reflecting curved surface is parabolic surface.Reflecting curved surface width b=(0.24975～0.4745) A; A=2～26mm; Degree of depth h=(0～1.618126) b.
3 is bearing structure lateral load face; 4 is bearing structure oblique orientation load face.Bearing structure lateral load face 3 center lines (or median plane) are parallel to heat energy reflecting curved surface center line (or median plane).Bearing structure oblique orientation load face 4 center lines (or median plane) become α angle with heat energy reflecting curved surface center line (or median plane), α ∈ (0 °, 90 °).
Determining of bearing structure plane of load width dimensions c and other physical dimensions.The maximum bearing stress characteristic width of selected parts load-bearing surface A, length L, feature load p.For example: the unit length that combustion chambers of internal combustion engines cylinder liner load-bearing surface first piston ring height is maximum bearing stress width A, piston ring contact arc length is that the load in L, unit area is P.Design is seasonal: the loaded area A=3c+2b of unit; Structural bearing rate is V=3c/ (3c+2b); V=0.05～1; C=(0.017～0.333) A;
The heating surface of matrix is annular surface, and described horizontal reflection groove is circular groove, and described oblique reflection groove is spiral chute, as cylinder inner wall surface.
Spiral fluted pitch angle alpha will is by relation: tg α=Φ × p/ π d, wherein: d=h+2R, R is matrix curvature of curved surface radius, line is counted Φ=1～∞, pitch angle alpha will ∈ (0 °, 90 °); Pitch is p=c+b.
As the concrete structural type of another kind, the heating surface of described matrix is plane.Adjacent two horizontal reflection grooves layout that is parallel to each other in plane, adjacent two oblique reflection grooves layout that is parallel to each other, in horizontal, oblique reflection groove one vertical with air-flow, α angle determined by combustion chambers burn tissue guide angle, this plane surface heat transfer structure application representative is as cylinder head.
As the concrete structural type of another kind, the heating surface of described matrix is to change continuously curved surface or multistage radius of curvature curved surface, article one, the length direction of reflective trenches is vertical with airflow direction, and another forms curved surface annular groove or reflective trenches segmental arc centered by parts structure center of surface.
The heat transfer surface structures moulding of parts firing chamber.Fig. 1 surface structure can adopt the modes such as powder metallurgy, precision casting, pressure forming and machining to make the parts with this firing chamber heat transfer surface structures, surface roughness Ra=0.63～0.006 μ m; Each sharp corner becomes fillet.
Described in the present embodiment, matrix 1 and heating surface are by having catalyzed carbon hydrogen fuel, catalysis H
2the functional material of O steam, high thermal resistance (heat-transfer coefficient: λ (3.3～8.8) W/ (mK)), low thermal absorptivity (20～40%) and high structural strength (800HV～1000HV) is made, the thickness of this functional material is 5mm, and its constituent and mass percent meet following relation:
35.9％Ni；
18％Ce0.75O
2Zr0.25O
2；
4.5％W；
4.5％Mo；
2％Ca；
2％K；
0.1％w(Pt、Rh)＝m
1(Pt)/m
2(Rh)＝5/1；
1％γ-A1
2O
3；
32％TiO
2。
The present embodiment can improve 2～88 DEG C of heating surface and near temperature, reduces heat transfer thermal loss 5～30%, reduces specific fuel consumption 1.6～9.6%, reduces CH, CO discharge 1～15%.
Relevant data:
1) firing chamber each several part pie graph (Fig. 5)
2) the each constituent elements temperature in firing chamber (table 1)
Table 1: firing chamber each constituent elements temperature list (K)
3) the each constituent element heat output in firing chamber (table 2)
Table 2: the each constituent element heat output in firing chamber (W)
4) chamber gas temperature and crank angle graph of a relation; (Fig. 6);
5) firing chamber gas instantaneous temperature and crank angle launch graph of a relation; (Fig. 7);
6) cylinder liner temperature is along axis distribution map; (Fig. 8).
The present invention is during as the firing chamber heat transfer surface structures of Combustor, cylinder liner, between cylinder first piston ring top and cylinder end face, there are many horizontal reflection grooves, oblique reflection groove, lateral load face, oblique orientation load face, owing to being combustor surface between first piston ring top and cylinder end face, do not carry mechanical load, c size can be by less coefficient calculations; Be carrying heating surface at first piston ring and lower surface, c size can be by larger coefficient calculations.
The content that above-described embodiment is illustrated should be understood to these embodiments only for being illustrated more clearly in the present invention, limit the scope of the invention and be not used in, after having read the present invention, those skilled in the art all fall within the application's claims limited range to the amendment of various replacement forms of the present invention.
Claims (10)
1. a firing chamber heat transfer surface structures, is characterized in that, comprises
---matrix (1), it has heating surface;
---many are arranged on the horizontal reflection groove (5) of lateral arrangement on heating surface, are the lateral load face (3) as bearing structure between adjacent two horizontal reflection grooves (5);
---many are arranged on the oblique reflection groove (6) of oblique layout on heating surface, are the oblique orientation load face (4) as bearing structure between adjacent two oblique reflection grooves (6);
Described oblique reflection groove (6) is with laterally reflection groove (5) is in a certain angle; Described horizontal reflection groove (5) all has reflecting curved surface with oblique reflection groove (6), and the length direction of described horizontal reflection groove (5) or oblique reflection groove (6) is vertical with high-speed and high-temperature air motion direction;
Described lateral load face (3) is provided with independent spill reflecting curved surface (2) with the intersection of oblique orientation load face (4);
Described matrix (1) or its heating surface are by having catalyzed carbon hydrogen fuel, catalysis H
2the functional material of O steam, high thermal resistance, low thermal absorptivity and high structural strength is made.
2. firing chamber according to claim 1 heat transfer surface structures, is characterized in that, width c=(0.017～0.333 of described lateral load face (3) or oblique orientation load face (4)) A, wherein bearing structure maximum stress carrying width A=2mm～26mm.
3. firing chamber according to claim 1 heat transfer surface structures, it is characterized in that, distance e=r-h=(-0.3 ~ 1.3 between the focus of described reflecting curved surface and described lateral load face (3) or oblique orientation load face (4)) h, wherein degree of depth h=(0～1.618126 of reflecting curved surface) b, b is the groove width of oblique reflection groove (6) and horizontal reflection groove (5), r is reflecting curved surface radius of curvature, b=(0.24975～0.4745) A; Wherein bearing structure maximum stress carrying width A=2mm～26mm.
4. firing chamber according to claim 1 heat transfer surface structures, is characterized in that, described reflecting curved surface is parabola.
5. firing chamber according to claim 1 heat transfer surface structures, is characterized in that, the heating surface of described matrix (1) is annular surface, and described horizontal reflection groove (5) is circular groove, and described oblique reflection groove (6) is spiral chute; This spiral fluted pitch angle alpha will is by relation: tg α=Φ × p/ π d determines, wherein: d=h+2R, R is matrix curvature of curved surface radius, line is counted Φ=1～∞, by high temperature gas flow orientation determination; α ∈ (0 °, 90 °); This spiral fluted pitch is p=c+b, width c=(0.017～0.333 of wherein said lateral load face (3) or oblique orientation load face (4)) A, described oblique reflection groove (6) and laterally groove width b=(0.24975～0.4745) A of reflection groove (5); Bearing structure maximum stress carrying width A=2mm～26mm.
6. firing chamber according to claim 1 heat transfer surface structures, it is characterized in that, the heating surface of described matrix (1) is plane, adjacent two horizontal reflection grooves (5) layout that is parallel to each other in plane, adjacent two oblique reflection grooves (6) layout that is parallel to each other, in horizontal, oblique reflection groove one vertical with airflow direction, become α angle with another reflection groove, α ∈ (0 °, 90 °).
7. firing chamber according to claim 1 heat transfer surface structures, it is characterized in that, the heating surface of described matrix (1) is to change continuously curved surface or multistage radius of curvature curved surface, the length direction of a reflection groove in horizontal, oblique reflection groove is vertical with airflow direction, and another reflection groove forms curved surface annular groove or reflective trenches segmental arc centered by base structure center of surface.
8. firing chamber according to claim 1 heat transfer surface structures, is characterized in that, described oblique reflection groove (6) or laterally reflection groove (5) are fillet with the intersection of described lateral load face (3) or oblique orientation load face (4).
9. firing chamber according to claim 1 heat transfer surface structures, is characterized in that, the thickness of described functional material is 0.01mm～20mm, and its constituent and mass percent meet following relation:
Ni （2～80）%；
Ce0.75O
2Zr0.25O
2 （2～60）%；
W （2～10）%；
Mo （2～10）%；
Ca （1～5）%；
K （1～5）%；
w(Pt、Rh) （0.05～2）%；
γ-A1
2O
3 （0.5～7）%；
TiO
2 （10～70）%；
Each constituent content sum is 100% above; Described w (Pt, Rh)=m
1(Pt)/m
2(Rh)=5/1.
10. firing chamber according to claim 9 heat transfer surface structures, is characterized in that, the constituent of described functional material and mass percent meet following relation:
Ni 35.9%；
Ce0.75O
2Zr0.25O
2 18%；
W 4.5 %；
Mo 4.5 %；
Ca 2%；
K 2%；
w(Pt、Rh) 0.1%；
γ-A1
2O
3 1%；
TiO
2 32%。
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410375561.XA CN104131879B (en) | 2014-08-01 | 2014-08-01 | A kind of combustion chamber heat transfer surface structures |
| PCT/CN2015/085609 WO2016015669A1 (en) | 2014-08-01 | 2015-07-30 | Heat conductive surface structure for combustion chamber and engine cylinder block |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410375561.XA CN104131879B (en) | 2014-08-01 | 2014-08-01 | A kind of combustion chamber heat transfer surface structures |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104131879A true CN104131879A (en) | 2014-11-05 |
| CN104131879B CN104131879B (en) | 2016-05-04 |
Family
ID=51804704
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410375561.XA Expired - Fee Related CN104131879B (en) | 2014-08-01 | 2014-08-01 | A kind of combustion chamber heat transfer surface structures |
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|---|---|
| CN (1) | CN104131879B (en) |
| WO (1) | WO2016015669A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016015669A1 (en) * | 2014-08-01 | 2016-02-04 | 周华祥 | Heat conductive surface structure for combustion chamber and engine cylinder block |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001049379A (en) * | 1999-08-12 | 2001-02-20 | Nkk Corp | Heat transfer tube for heat exchanger |
| CN1312885A (en) * | 1998-08-11 | 2001-09-12 | 法国马涅蒂·马雷利公司 | Piston with active guiding head and associated combustion chamber |
| CN1985084A (en) * | 2004-07-12 | 2007-06-20 | 通用汽车公司 | Auto-ignition gasoline engine combustion chamber and method |
| CN201045313Y (en) * | 2007-01-29 | 2008-04-09 | 北京理工大学 | Electric-controlled high-pressure injection burning chamber |
| WO2009020206A1 (en) * | 2007-08-09 | 2009-02-12 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Internal combustion engine |
| CN101576002A (en) * | 2008-05-09 | 2009-11-11 | 广西玉柴机器股份有限公司 | Diesel combustion chamber for preventing fuel from impacting walls |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204024799U (en) * | 2014-08-01 | 2014-12-17 | 周华祥 | A kind of heat transfer surface structures |
| CN104131879B (en) * | 2014-08-01 | 2016-05-04 | 周华祥 | A kind of combustion chamber heat transfer surface structures |
-
2014
- 2014-08-01 CN CN201410375561.XA patent/CN104131879B/en not_active Expired - Fee Related
-
2015
- 2015-07-30 WO PCT/CN2015/085609 patent/WO2016015669A1/en active Application Filing
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1312885A (en) * | 1998-08-11 | 2001-09-12 | 法国马涅蒂·马雷利公司 | Piston with active guiding head and associated combustion chamber |
| JP2001049379A (en) * | 1999-08-12 | 2001-02-20 | Nkk Corp | Heat transfer tube for heat exchanger |
| CN1985084A (en) * | 2004-07-12 | 2007-06-20 | 通用汽车公司 | Auto-ignition gasoline engine combustion chamber and method |
| CN201045313Y (en) * | 2007-01-29 | 2008-04-09 | 北京理工大学 | Electric-controlled high-pressure injection burning chamber |
| WO2009020206A1 (en) * | 2007-08-09 | 2009-02-12 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Internal combustion engine |
| CN101576002A (en) * | 2008-05-09 | 2009-11-11 | 广西玉柴机器股份有限公司 | Diesel combustion chamber for preventing fuel from impacting walls |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016015669A1 (en) * | 2014-08-01 | 2016-02-04 | 周华祥 | Heat conductive surface structure for combustion chamber and engine cylinder block |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2016015669A1 (en) | 2016-02-04 |
| CN104131879B (en) | 2016-05-04 |
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