CN2147357Y - J80 turbo supercharge and application thereof - Google Patents

Abstract

The utility model relates to the pressure boosting technology of the internal combustion engine, relating to a small-size radial flow type turbine pressure boosting device especially suitable for the automotive engine. The compressor impeller 6 of the small-size radial flow type turbine pressure boosting device adopts the novel structure of irregular pitch, blades with different lengths, anteverted flow diversion and round blade tip. Therefore, the higher efficiency is kept. A volute casing 5 adopts a snail shell with a compact configuration and an inner passage which is three circular arcs. The cross sections of the inner passage is designed with the frictional loss of the gas along the inner passage, which causes the compressor efficiency to achieve 75%, and the compressor efficiency is the leading position in China. A 360 DEG full admission two-passage turbine case 2 without a blade is adopted, and has a smaller radical structure size and light weight. The small-size radial flow type turbine pressure boosting device has the wide adaptive range of the flow capacity, and is suitable for the plateau automobiles.

Description

J80 turbo supercharge and application thereof

The utility model relates to the supercharging of internal combustion engine technology, is the small-type radial turbosupercharger, is specially adapted to vehicular engine.

The turbosupercharger of domestic production at present has the J110 pressurized machine of Shanghai Diesel Engine Plant, is used for generator set; The J125 pressurized machine that 70 Research Institute are produced is suitable for the high-power tracked vehicle motor.We retrieve a kind of prior art: CN86100943A from patent documentation, and it adopts guide ring and dish valve system, and structure is comparatively complicated, are not suitable for vehicle and use.

China is vast in territory, with a varied topography, many plateaus country, and in recent years, along with development and national economy, the automobile transport undertaking plays a part very important, and is especially all the more so in vast plateau section.And the vehicle that on China plateau, travels mostly dress be non-supercharged engine, height above sea level is high more, air is thin more, non-supercharged engine can not adapt to more, power will descend, oil consumption will be risen, 1000 meters of the every risings of height above sea level, engine power will descend 15%; Oil consumption will rise 8%, and this has just had a strong impact on the transport benefits of plateau section.

The purpose of this utility model is to overcome the shortcoming of non-supercharged engine, and the transport undertaking of development China plateau section is the motor car engine of using on the plateau, design, coupling J80 turbosupercharger.

The utility model is a kind of turbosupercharger that is made of gas compressor, turbine assembly and bearing unit three parts (seeing accompanying drawing 1), it is characterized in that compressor volute 5 and turbine box 2 all count gas in passage along the journey frictional loss, its passage than circulation area A/R along angle of circumference θ nonlinear Distribution, compressor impeller 6 is deviated splitter vane and oval blade profile and its inducer retapering of lean forward shunting, irregular pitch, and turbine 1 is designed to BI and by the stress distribution law moulding.In order to adapt to the needs of plateau motor car engine, we are intended to obtain the optimum Match of the set of data assembly of a high efficiency, utilizable flow wide ranges when design.

When design turbine 1, single gradient profile (seeing accompanying drawing 2, Fig. 2 A) is in the past changed in its blade radial cross section, and comes moulding by stress distribution law, and making it to be tending towards " equal strength " is that the blade outer rim is thinner, along with the radius blade that diminishes is thickeied gradually, thicken suddenly during near root.Design by this kind mode, it is more reasonable that its leaf quality distributes, and not only guaranteed blade strength but also reduced rotary inertia.While to it being designed to BI (seeing accompanying drawing 2, Fig. 2 B), has not only increased blade stiffness but also make that secondary speed had the possibility (exceeding the speed limit to 11.6 ten thousand r/min by 80,000) that increases nargin when altitude raise along sharf.

Turbine box 2 adopts the design proposal of no leaf turbine box, this be through I design studies for many years be tending towards ripe scheme at present, because the J80 turbosupercharger designs at engine for automobile, consider miniaturization and low cost and low engine speed characteristic, decision select the no leaf turbine box of the full intake type of Twin channel 360 degree for use so as to be suitable for that range of flow is wide, the inlet gas pulse is little, the light and handy impeller also little then to the turbine blade exciting, thereby improved the reaction sensitivity of J80 turbosupercharger.

In the 60 to 70's, the design method with the linear rule of angle of circumference θ than circulation area A/R is almost all adopted in countries in the world, finds afterwards that the gas-static of turbine wheel ingress was circumferentially extremely inhomogeneous, and this is very unfavorable to turbine efficiency.From the eighties mid-term, through repeatedly practice, we have done the design method of oneself, current the utility model just adopt along angle of circumference θ count in passage along the journey frictional loss, it is the design method (seeing accompanying drawing 3) of nonlinear Distribution rule than circulation area A/R.

Can the quality of bearing arrangement will be related to pressurized machine and reliably turn round effectively, should consider functional reliability when we design, and make it have higher mechanical efficiency again.For this reason, we adopt radially oil-feed, built-in full floating floating-ring bearing 3, and are so-called flexible shaft scheme (seeing accompanying drawing 4) with heavy wall, big span, than pilot pin.Bearing support 4 adopts the HTM-3B wear resisting cast iron, to improve its reliability.

Compressor volute 5, adopt the three-arc passage count gas in passage along the snail type spiral case (seeing accompanying drawing 5) of journey flow losses and adopt vaneless diffuser (outer diameter D ₃=130mm), although it than blade diffuser inferior a bit aspect pressure ratio and the efficient, its characteristic variations is smooth, this more is applicable to vehicular engine undoubtedly.

Compressor impeller 6 adopts the deviated splitter vane and the oval blade profile curve impeller (outer diameter D of lean forward shunting, irregular pitch ₂=78mm), and with the forward position retapering of inducer blade.Test shows, the prismatic blade impeller that band leans forward, and being more evenly distributed of outlet port gas flowfield is suitable for the range of flow broad, and efficient is also higher.By computational analysis to ternary flow field in the impeller passage, find short blade position deflection linear leaf pressure side one side deviated splitter vane impeller (promptly not waiting the intercept impeller to see accompanying drawing 6) than routine etc. the intercept impeller have more superior performance, efficient can improve 2%, and efficiently the scope in district has also enlarged, and has also improved in following pressure ratio that can reach of identical peripheral velocity.At the characteristics of vehicular engine, adopt oval blade profile curve (seeing accompanying drawing 7), the blade profile equation on the moulding basic circle is:

Z′＝（b／a） $\sqrt{a2-{(a-Y^{\′})}^2}$

By given blade profile top rake γ, expansion arc length S o, axial length Zo and blade angle β ₀All parameters can be obtained oval major and minor axis a and b.

Lose to improve compressor efficiency in order to reduce the bump of air-flow at the impeller eye place, we are with the forward position retapering of inducer blade (seeing accompanying drawing 8).

Bearing disk 7, thrust plate 10, rotor shaft 11 and stuffing box gland 13, seal ring 14, oil baffle 15 and spacer sleeve 16 common two-way thrust system of formation and double seal systems (seeing accompanying drawing 9).

Conduct heat to improve efficiency of turbocharger, to delay oil ageing to cold junction in order to reduce the hot junction, the J80 turbosupercharger has adopted the thermal shield 12 that is divided into two bodies with bearing support 4, and it forms two heat-insulation chambers with bearing support 4.

Being connected of turbine box 2 compressor volutes 5 and bearing support 4, all adopt pressing plate and screw, both guaranteed to connect reliably, the circumferential position of three big housings is adjusted arbitrarily, make pressurized machine that bigger adjustment degrees of freedom is installed on motor.Boundary dimension is 200 * 215 * 186(mm).

The J80 turbosupercharger is to absorb independent design on the basis of military pressurized machine technology, developing, prove through stand test and service testing, reliable operation, its compressor efficiency has reached 75%, be in leading domestic status, and reach international the eighties advanced level.Adopt automobile of the present utility model, engine power improves 23% on the plateau, and torque increases by 31%, and fuel consumption rate reduces by 8%, and delivery temperature reduces by 100 ℃, and fuel consumption per hundred kilometers reduces about 8%.

Description of drawings:

Fig. 1 is J80 turbocharger arrangement figure.

Wherein 1, turbine; 2, turbine box; 3, floating-ring bearing; 4, bearing support; 5, spiral case; 6, compressor impeller; 7, bearing disk; 8, back of the body dish; 9, locking nut; 10, thrust plate; 11, rotor shaft; 12, thermal shield.

Fig. 2 is the turbine blade pattern; Fig. 2 A is the A-A section of Fig. 2; Fig. 2 B is the B-B section of Fig. 2.

Fig. 3 is the Changing Pattern of no leaf turbine box passage than circulation area A/R.

Fig. 4 is the bearing arrangement schematic representation.

Fig. 5 is three-arc spiral case passage figure.

Fig. 6 is an irregular pitch impeller schematic representation.

Fig. 7 is the oval blade profile curve figure of compressor impeller.

Fig. 8 is an inducer blade forward position retapering schematic representation.

Fig. 9 is two-way thrust and double sealing structure figure.

Figure 10 is blower outlet air density γ ₂With pressure ratio π _CRelation curve.

Figure 11 is a J80 turbocharger air compressor characteristic curve.

Figure 12 is a J80 turbocharger turbine flow characteristics curve.

Figure 13 is J80 turbosupercharger and 6102QA motor connection diagram.

Wherein 1, J80 pressurized machine; 2,6102QA motor.

Enumerate the embodiment of the utility model and vehicular engine coupling below:

Turbosupercharger and Engine Matching more complicated need be mated in advance and calculate so that reasonably determine the gas compressor design parameter, and be determined the circulation area of turbine and turbine box in view of the above.Provide design conditions earlier:

Atmospheric condition: Po=100KP.

Atmospheric temperature: to=20 ℃

Engine model: 6102QA

Important technological parameters behind the 1 6102QA h type engine h coupling J80 pressurized machine

Pattern: array, six cylinders, water-cooled, four-stroke, toroidal swirl type

Supercharging mode: cold in pulse turbocharging, the nothing

Bore/stroke: 102 * 115(mm)

Cylinder total displacement: 5.638L

Nominal operation rotating speed: 3000r/min

Rated power: 99KW

Inlet and exhaust valve overlapping angle: 30 °

2 gas compressors coupling is calculated

According to the technical order that will reach after the structural parameter of motor and the supercharging, at first determine its required air amount G _c, then determine its required pressure ratio π again _c, according to the G that is drawn _c, π _cSelect suitable gas compressor.

21 motors required air amount G when declared working condition _c

G _c＝ (g _e·H _e·a·b)/250 （Kg／s）

g _eThe fuel consumption rate of-motor is got g _e=234(g/KWh)

The rated power of Ne-motor, 2000 meters power of general supercharged engine altitude rising descend 6% approximately.The performance number that the engine power at 2000 meters of height above sea level is converted to the standard regions is:

99／0.94＝105.32（KW）

The total excess air coefficient of α φ-motor, get α φ=2.21 item:

G _c＝ (0.234×105.32×2.21)/250 ＝0.218（Kg／s）

The pressure ratio π of 22 constant engine operating modes _c:

G _CAfter determining, its pressure ratio π _cThe discharge capacity V of decision motor _h, rotation speed n _eWith volumetric efficiency η _v, coefficient of scavenging φ and gas compressor efficiency eta _c

The gas density γ of required blower outlet ₂:

γ ₂＝ (60·G _C·π)/(η _V·φ·V _h·n _e) （Kg／m ³）

To four stroke engine stroke coefficient τ=2 then

To intake and exhaust overlapping angle is that 30 ° motor is got η _vφ=0.94 item:

γ ₂＝ (60×0.218×2)/(0.94×0.005638×3000) ＝1.645（Kg／m ³）

Make compressor efficiency η _c=0.74 by drawing corresponding pressure ratio π on accompanying drawing 10 curves _c=1.74

2.3 obtain air mass flow and pressure ratio along engine test bench characteristic

This is a problem that be difficult to solve, because it is controlled by factors such as the efficiency change of turbosupercharger and engine oil rule rate.For the matching state of calculation engine external characteristics and compressor characteristics, we join machine data according to motors such as 6P125,12V150 in the past, BF12L413 and 6130 to calculate in a large number.Supercharging pressure ratio π when studying these supercharged engine along external characteristics _cWith gas flow G _cRelative Changing Pattern, just the 6102QA motor be can calculate with the pressure ratio of the declared working condition obtained previously and flow again and pressure ratio and flow joined behind the J80 pressurized machine along external characteristics, it is plotted on the J80 supercharger air compressor characteristic curve on the accompanying drawing 11, the coupling that can find out motor and supercharger air compressor is more rational, because the consumption gas line of engine test bench characteristic is just through the high efficient area of gas compressor.Behind the 6102QA coupling JQ80 pressurized machine is 6102ZQA.

The coupling of 3 turbines is calculated

In order to simplify the workload of coupling, common fixed turbine blade wheel structure size, realize the coupling of different motors with the turbine box that mates several different circulation areas in certain scope, thereby the coupling of turbine is calculated the selection that just is reduced to the turbine box circulation area.

3.1 required expansion ratio of turbine π _T:

Balance by gas compressor and turbine merit can get:

${\mathrm{\π}}_r=\left[\frac{1}{1-\frac{0.8881(t_1+273)({\mathrm{\π}}_c^{0.286}-1)}{(t_3+273)\·{\mathrm{\η}}_{\mathrm{to}}}}\right]394$

In the formula: t ₁-compressor inlet temperature is got 20 ℃

t ₃-turbine inlet temperature was got 520 ℃ with reference to former test data

η _TcThe total efficiency of-turbosupercharger gets 0.46

${\mathrm{\π}}_r=\left[\frac{1}{1-\frac{0.8881(20+273)({1.74}^{0.286}-1)}{(520+273)\×0.46}}\right]394=1.673$

Get the back pressure P behind the turbine ₄=0.102(MP _a)

The gas pressure P before the turbine then ₃=P ₄* π _T=0.102 * 1.673

＝0.1706（MP _a）

3.2 required turbine box circulation area A:

To obtain the nondimensional mass flow G of its stable state by platform test to existing turbine and turbine box _T

/ P ₃With expansion ratio π _T=P ₃/ P ₄Relation-be the turbine flow characteristics, obtain the required turbine box circulation area of different parameters according to the flow characteristics of turbine again.

The nondimensional mass flow that draws in view of the above under the required pulse condition of 6102ZQA is:

${\left(\frac{G_r\sqrt{T_3}}{P_3}\right)}^{\′}=\frac{0.218\×\sqrt{520+273}}{0.1706}=35.98\left(\frac{\mathrm{kg}/s\sqrt{K}}{{\mathrm{MP}}_n}\right)$

There is a scale factor a in the flow that turbine is passed through under stable state greater than the flow that is passed through between them under pulsation, get a=0.95 according to the test data in past, and then the required stable state nondimensional mass flow of 6102ZQA is:

$\frac{G_r\sqrt{T_3}}{P_3}={\left(\frac{G_r\sqrt{T_3}}{P_3}\right)}^{\′}/a=35.98/0.95=37.87\left(\frac{\mathrm{kg}/s\sqrt{K}}{{\mathrm{MP}}_a}\right)$

With π _T=1.673, G _T

/ P ₃=37.87 on accompanying drawing 12 turbine flow characteristicses, just can find out required turbine circulation area A=18(cm ²)

J80 turbosupercharger and the whole optimum matching parameters of 6102QA h type engine h have been obtained to this.

Figure 13 is the utility model and 6102QA engine air flue and lubricating oil path connection diagram.

Claims (5)

1, a kind of turbosupercharger that constitutes by gas compressor, turbine assembly and bearing unit three parts, it is characterized in that compressor volute 5 and turbine box 2 all count gas in passage along the journey frictional loss, its passage than circulation area A/R along angle of circumference θ nonlinear Distribution, compressor impeller 6 is deviated splitter vane and oval blade profile and its inducer retapering of lean forward shunting, irregular pitch, and turbine 1 is designed to BI and by the stress distribution law moulding.

2,, it is characterized in that compressor volute 5 adopts the hodmadod of three-arc passage, and adopt outer diameter D by the described turbosupercharging gas of claim 1 device ₃The vaneless diffuser of=130mm.

3,, it is characterized in that adopting the circulation area A=18cm of 360 ° of full air inlets of Twin channel by the described turbosupercharger of claim 1 ²No leaf turbine box 2.

4, by the described turbosupercharger of claim 1, it is characterized in that boundary dimension is 200 * 215 * 186(mm).

5,, it is characterized in that the outer diameter D of compressor impeller 6 by the described turbosupercharger of claim 1 ₂=78mm.

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