CN200955437Y - J130 radial-flow wormgear - Google Patents

Abstract

The utility model discloses a J130 racial-flow type turbine, pertaining to the technical field of vary-volume mechanism. The technical proposal is as follows: the turntable is semi-open type; the amount of the blade is twelve; the profile curve of the blade is designed according to the double equation method; the thickness of the blade around the wheel hub and the outer base cylinder is distributed following certain discipline. The beneficial effects of the utility model are energy saving, decline of the exhaust temperature, low cost.

Description

The J130 radial-flow turbine

Technical field: the utility model belongs to the variable capacity field of mechanical technique, is specifically related to a kind of J130 radial-flow turbine.

Background technique: turbosupercharger is the vitals that improves power of IC engine, reduction consumption rate of fired oil, improves discharging.Day by day short at the whole world energy, that environment goes from bad to worse today, exhaust gas turbocharge has become the only way which must be passed of internal combustion engine development.Turbine is to be the vital part of mechanical work with the I. C. engine exhaust transformation of energy in the pressurized machine, and the big young pathbreaker of the height of turbine efficiency and rotary inertia thereof directly influences turbo charged effect.Radial turbine is most widely used a kind of in three kinds of turbine patterns (axial flow, radial-flow type, mixed-flow).At present at home on the market popular product, be imitated external early stage product mostly, it is on the low side therefore to exist efficient, the dissatisfactory defective of turbosupercharging effect.

Summary of the invention: the utility model is in order to solve the deficiencies in the prior art, and develops a kind of J130 radial-flow turbine.

The technical solution of the utility model is, a kind of J130 radial-flow turbine, wheel disc are the semi-open type wheel disc, and the number of blade is 12, and the blade profile curve of blade adopts both sides' journey pattern, that is:

Z＝0～9

$\mathrm{\θ}=C_1\{1-{[1-{\left(\frac{9-Z}{b_1}\right)}^{p_1}]}^{\frac{1}{q_1}}\}$ [radian]

Z＝9～43

$\mathrm{\θ}=C_2\{1-{[1-{\left(\frac{Z-9}{b_2}\right)}^{p_2}]}^{\frac{1}{q_2}}\}$ [radian]

In the formula: θ-angle of circumference [radian]

b ₁, c ₁, b ₂, c ₂--the equation undetermined coefficient, by blade greatest axial length Zm, turbine outlet average diameter D _2pOn blade angle β _2pWith blade envelope angle θ _bDetermine, to the what radial-flow turbine, general Zm/D _1P=0.3～0.4, β _2p=30～40 °,

D ₁Be turbine inlet diameter, D ₂=[(D ²+ Do ²)/2] ^0.5

p ₁, q ₁, p ₂, q ₂--the equation index, its value influences the curvature variation of blade profile curve, is generally 1.8～3.0

Z--Z is to coordinate, [mm]

Along wheel hub and outside the vane thickness regularity of distribution of base cylinder:

Tg＝6+0.18992*Z-0.0142082*Z ²+0.0007029*Z ³

-0.0001995709*Z ⁴+0.00000203716*Z ⁵

Tw＝0.85+0.0018333*Z-0.00126667*Z ²+0.0009166667*Z ³

-0.00001333333*Z ⁴

In the formula: Tg--is along the vane thickness of wheel hub, [mm]

Vane thickness on the outer base cylinder of Tw--, [mm]

Z--Z is to coordinate, [mm]

The vane thickness of arbitrfary point on the blade:

$T=\mathrm{Tg}-(\mathrm{Tg}-\mathrm{Tw})\·{\left(\frac{R-\mathrm{Rg}}{\mathrm{Rw}-\mathrm{Rg}}\right)}^{{\left(\frac{\mathrm{Rg}}{1.5R}\right)}^m}$

In the formula: the vane thickness of arbitrfary point on the T--blade, [mm]

Tg, the Tg that Tw--tries to achieve by equation in 3, Tw value, [mm]

The hub radius of the corresponding Z of Rg--, [mm]

The radius of the outer base cylinder of Rw--, [mm]

Any radius of R--from Rg to Rw, [mm]

M--THICKNESS CONTROL index is a variable vertically;

m＝0.9-0.013704*Z+0.00074074*Z ²-0.0000291497*Z ³

+0.00000762082*Z ⁴-0.00000070563*Z ⁵

The wheel hub form parameter of radial-flow turbine is: R ₂=36.65mm, Do=φ 29.6mm, D _b=φ 94mm, Zm=43mm.

R ₂--arc radius at the bottom of the turbine hub, D ₀--turbine outlet hub radius, D _b--turbine inlet hub radius, Zm--turbine blade axial height.

The beneficial effects of the utility model: motor producer is by adopting the pressurized machine that is equipped with the J130 radial-flow turbine, make the oil consumption rate decline 6～9g/kwh of motor, delivery temperature reduces by 50～70 ℃, and the pressurized machine cost reduces about 15%, has created good economic benefit and social benefit.

Description of drawings: the present invention has 6 width of cloth accompanying drawings, and wherein Fig. 1 is the preferred example of model utility, also can make the accompanying drawing of specification digest.

Fig. 1 is a structural drawing of the present utility model;

Fig. 2 is " skeleton blade forming method " schematic representation;

Fig. 3 is the blade profile curve schematic representation;

Fig. 4 is the vane thickness schematic representation;

Fig. 5 is a J130 radial-flow turbine meridian access diagram;

Fig. 6 designs and calculation flow chart for turbine blade.

Embodiment: most preferred embodiment of the present utility model is further described below in conjunction with accompanying drawing.

Preferred example of the present invention as shown in Figure 1, wheel disc is the semi-open type wheel disc, the number of blade is 12.

The blade mould-forming method as shown in Figure 2, a blade of turbine is made of convex surface and concave surface, " skeleton blade forming method " adopted in the shaping of male and female face--also promptly set a base cylinder, and on this cylinder, set up θ ^*=f (Z) (or S ^*=f (Z)) blade profile curve, along the given a series of point of Z axle, one by one by this a series of point on the Z axle and pass a series of radius that blade profile curve is drawn parallel X-Y plane, these rays just form cambered surface in the blade that does not have thickness, and the thickness of enclosing blade in each ray both sides (parallel X-Y plane) symmetry according to certain rule has promptly formed the male and female face of blade.Usually we are considered as blade profile curve on " backbone ", and a series of radius is considered as " rib ", set up one so-called " skeleton " before attached vane thickness earlier, and we are referred to as this method " skeleton blade forming method ".

* θ is an angle of circumference, and S is an arc length

In order to improve the efficient of turbine, start with from reducing gas incident loss, the loss of turning round, leaving loss.And reasonably blade profile curve, the vane thickness regularity of distribution of science and wheel hub and the cover hub line that distributes to determine by gas flowfield are the keys of this turbine design under the prerequisite that guarantees blade strength.

1. blade profile curve is adjusted blade profile curve for just what as shown in Figure 3, adopts both sides' journey pattern, Zm among Fig. 3 ₁Be the separation of two equations, that is:

Z＝0～9

$\mathrm{\θ}=C_1\{1-{[1-{\left(\frac{9-Z}{b_1}\right)}^{p_1}]}^{\frac{1}{q_1}}\}$ [radian] ... ZL1

Z＝9～43

$\mathrm{\θ}=C_2\{1-{\left[1{-\left(\frac{Z-9}{b_2}\right)}^{p_2}\right]}^{\frac{1}{q_2}}\}$ [radian] ... ZL2

In the formula: θ--angle of circumference, [radian]

Z--Z is to coordinate values, [mm]

b ₁, c ₁, b ₂, c ₂--the equation undetermined coefficient, by blade greatest axial length Zm, turbine outlet average diameter D _2pOn blade angle β _2pWith blade envelope angle θ _bDetermine.For radial turbine, general Zm/D ₁=0.3～0.4 (D ₁Be the turbine inlet diameter),

D ₂＝[(D ₂ ²+D ₀ ²)/2] ^0.5，β _2p＝30～40°，

p ₁, q ₁, p ₂, q ₂--the equation index, its value influences the curvature variation of blade profile curve, is generally 1.8～3.0.

2. along the vane thickness of wheel hub and outer base cylinder as shown in Figure 4, size, the number of blade, blade strength, the Flow Field Distribution of its thickness and turbine are relevant, for the plasticity of the realization vane thickness regularity of distribution, generally represent with the equation of higher degree.The vane thickness equation of this turbine is:

Tg＝6+0.18992*Z-0.0142082*Z ²+0.0007029*Z ³

-0.0001995709*Z ⁴+0.00000203716*Z ⁵ [mm]……ZL·3

Tw＝0.85+0.0018333*Z-0.00126667*Z ²+0.0009166667*Z ³

-0.00001333333*Z ⁴ [mm]……ZL·4

In the formula: Z--Z is to coordinate, [mm]

T _g--the vane thickness on any Z value wheel hub, [mm]

T _W--Z value, radius are R arbitrarily _WOuter base cylinder on vane thickness, [mm]

3. the vane thickness of arbitrfary point is as shown in Figure 4 on the blade, ZL.3 and ZL.4 formula have only provided the vane thickness regularity of distribution of two end points on the Z cross section such as any, and for certain first-class Z cross section, the vane thickness regularity of distribution from Rg to Rw is then by the blade stress regularity of distribution with follow the principle that reduces turbine rotation inertia and determine that the thickness representation of this turbine is as far as possible:

$T=\mathrm{Tg}-(\mathrm{Tg}-\mathrm{Tw})\·{\left(\frac{R-\mathrm{Rg}}{\mathrm{Rw}-\mathrm{Rg}}\right)}^{{\left(\frac{\mathrm{Rg}}{1.5R}\right)}^m}$ [mm]……ZL·5

In the formula: the vane thickness at any Z of T--, R place, [mm]

The given Z value of Tg, Tw--is by the vane thickness that ZL.3 and ZL.4 formula calculate, [mm]

The hub radius at any Z value of Rg, Rw--place and outer base cylinder radius, [mm]

The radius of R--evaluation point, [mm]

M--THICKNESS CONTROL index, its along Z to variation express with the equation of higher degree, the m equation of this turbine is:

m＝0.9-0.013704*Z+0.00074074*Z ²-0.000029147*Z ³

+0.00000762082*Z ⁴-0.00000070563*Z ⁵ ……ZL.6

Turbine meridian channel design as shown in Figure 5, its parameter is: R ₁=17mm, R ₂=36.65mm, α=5 °, D ₁=φ 124mm, D ₂=φ 98mm, Do=φ 29.6mm, D _b=φ 94mm, b _T1=17.5mm, Zm=43mm.

As shown in Figure 6, the designing and calculating step is:

1. according to selected blade envelope angle θ _b, outlet blade angle β _2p, blade axial length Zm and blade profile equation index p ₁, q ₁, p ₂, q ₂Determine the undetermined coefficient b of blade profile equation ZL.1 and ZL.2 ₁, c ₁, b ₂, c ₂And determine the wheel hub line and the cover hub line of turbine according to flow field analysis.

2. compose Z value, step-length Sz, span: 0～Zm, Z=Z+Sz

3. do you judge whether Z 〉=Zm?

Be, finish, use the Proe modeling, carry out turbine mold design and manufacturing;

Not, ask θ with equation ZL.1 and ZL.2, ask Tg.Tw with equation ZL.3 and ZL.4, ZL.6 asks m with equation, carries out the 4th step;

4. compose R value, step-length S _RSpan: Rg～Rw, R=R+S _R

5. do you judge whether R 〉=Rw?

Be to return the 2nd step;

, do not carry out the 6th step;

6. ask T with the ZL.5 formula;

7. obtain the some X on protruding, the concave surface respectively _T, Y _TWith X _W, Y _WAnd input data file separately;

8. return the 4th step, find the solution down a bit.

Claims (1)

1, a kind of J130 radial-flow turbine is characterized in that: wheel disc is the semi-open type wheel disc, and the number of blade is 12, and the blade profile curve of blade adopts both sides' journey pattern, that is:

Z＝0～9

$\mathrm{\θ}=C_1\{1-{[1-{\left(\frac{9-Z}{b_1}\right)}^{p_1}]}^{\frac{1}{q_1}}\}$ [radian]

Z＝9～43

$\mathrm{\θ}=C_2\{1-{[1-{\left(\frac{Z-9}{b_2}\right)}^{p_2}]}^{\frac{1}{q_2}}\}$

[radian]

In the formula: θ-angle of circumference [radian]

b ₁, c ₁, b ₂, c ₂-----equation undetermined coefficient is by blade greatest axial length Zm, turbine outlet average diameter D _2pOn blade angle β _2pWith blade envelope angle θ _bDetermine, to the what radial-flow turbine, general Zm/D _1P=0.3～0.4, β _2p=30～40 °,

D ₁Be turbine inlet diameter, D ₂=[(D ²+ Do ²)/2] ^0.5

p ₁, q ₁, p ₂, q ₂---------equation index, its value influences the curvature variation of blade profile curve, is generally 1.8～3.0

Z Z is to coordinate, [mm]

Along wheel hub and outside the vane thickness regularity of distribution of base cylinder:

Tg＝6+0.18992*Z-0.0142082*Z ²+0.0007029*Z ³

-0.0001995709*Z ⁴+0.00000203716*Z ⁵

Tw＝0.85+0.0018333*Z-0.00126667*Z ²+0.0009166667*Z ³

-0.00001333333*Z ⁴

In the formula: Tg--is along the vane thickness of wheel hub, [mm]

Vane thickness on the outer base cylinder of Tw--, [mm]

Z--Z is to coordinate, [mm]

The vane thickness of arbitrfary point on the blade:

$T=\mathrm{Tg}-(\mathrm{Tg}-\mathrm{Tw})\·{\left(\frac{R-\mathrm{Rg}}{\mathrm{Rw}-\mathrm{Rg}}\right)}^{{\left(\frac{\mathrm{Rg}}{1.5R}\right)}^m}$

In the formula: the vane thickness of arbitrfary point on the T--blade, [mm]

Tg, the Tg that Tw--tries to achieve by equation in 3, Tw value, [mm]

The hub radius of the corresponding Z of Rg--, [mm]

The radius of the outer base cylinder of Rw--, [mm]

Any radius of R--from Rg to Rw, [mm]

M--THICKNESS CONTROL index is a variable vertically;

m＝0.9-0.013704*Z+0.00074074*Z ²-0.0000291497*Z ³

+0.00000762082*Z ⁴-0.00000070563*Z ⁵

The wheel hub form parameter of radial-flow turbine is: R ₂=36.65mm, Do=φ 29.6mm, D _b=φ 94mm, Zm=43mm,

R ₂--arc radius at the bottom of the turbine hub, D ₀--turbine outlet hub radius, D _b--turbine inlet hub radius, Zm--turbine blade axial height.

Images