CN200952423Y - H55 mixed-flow turbine - Google Patents

Abstract

The utility model discloses a H55 mixed-flow turbine and pertains to the technology field of variable-volume mechanism. And the technical plan of H55 mixed-flow turbine is that: the rotary table is semi-open type; the blade number is 10 and the blade profile curve adopts two-equation model, and distributes along the blade thickness at the wheel hub and the outer base cylinder, according to certain rules; the blade thickness T of arbitrary point on the blade is decided by the equation; and the inlet blade tip retapering is also decided by the equation. The utility model has the beneficial effects of reduced of turbine oil consumption rate and gas exhaust temperature.

Description

The H55 mixed flow turbine

Technical field: the utility model belongs to the variable capacity field of mechanical technique, is specifically related to a kind of H55 mixed flow turbine.

Background technique: turbosupercharger is the vitals that improves power of IC engine, reduction consumption rate of fired oil, improves discharging.Turbine is vital part of high speed rotating at high temperature in the turbosupercharger, and its effect is that the exhaust energy with internal-combustion engine is converted to the mechanical work that drives the coaxial high speed rotating of gas compressor.The pattern of turbine has three kinds, i.e. axial flow, radial-flow type, mixed-flow.Axial flow is used for large-sized turbo-charging device and gas turbine more, and radial-flow type is used for the small sized turbine pressurized machine more.Because the height of turbine efficiency directly influences the effect of internal combustion engine turbocharging, so the combined flow turbine between axle, radial-flow type is subjected to people's favor because of having higher turbine efficiency.At present, on the small-sized at home pressurized machine market, almost all adopt radial turbine, its efficient is lower, influences the matching performance of pressurized machine and complete machine.

Summary of the invention: the utility model is developed a kind of H55 mixed flow turbine for the validity that improves internal combustion engine turbocharging.

The technical solution of the utility model is, a kind of H55 mixed flow turbine, wheel disc are the semi-open type wheel disc, and the number of blade is 10, and the blade profile curve of blade adopts both sides' journey pattern, that is:

Z＝0～7.5

$\mathrm{\θ}=C_1\{1-{[1-{\left(\frac{7.5-Z}{b_1}\right)}^{p_1}]}^{\frac{1}{q_1}}\}$ [radian]

Z＝7.5～22.5

$\mathrm{\θ}=C_2\{1-{[1-{\left(\frac{Z-7.5}{b_2}\right)}^{p_2}]}^{\frac{1}{q_2}}\}$ [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 mixed flow turbine, general Zm/D _1P=0.4～0.5, β _2p=30～40 °,

D _1PBe turbine inlet average diameter, D _2P=[(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

T _g＝2.8+0.20231*Z+0.0021445*Z ²-0.00191276*Z ³

+0.000962052*Z ⁴-0.00001403593*Z ⁵[mm]

T _w＝0.25+0.0706667*Z-0.00336667*Z ²

+0.00093333*Z ³-0.0000133333*Z ⁴[mm]

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＝0.9-0.02213*Z+0.001709*Z ²-0.00059795*Z ³+0.000022092*Z ⁴

Inlet vane retapering equation is:

T＝Tx[0.5-0.0513(R-Rx)+0.079998(R-Rx) ²-0.178665(R-Rx) ³][mm]

In the formula: T--revises the vane thickness in district, [mm]

Tx--by equation in 4 calculate corresponding Z, the Rx vane thickness of ordering, [mm]

Rx--revises the start radius in district, [mm]

R--revises the radius of arbitrfary point, district, [mm]

Along b _T1The regularity of distribution of inlet vane established angle

β ₁＝β ₁/β _1max b＝b/b _T1

Wherein: β ₁The relative blade angle of-import,

β ₁-inlet vane established angle, [°], definition is referring to Fig. 4

β _1max-maximum inlet blade angle is generally 20～25 °

The relative inlet vane width of b-,

B-is the inlet vane width of any arbitrarily, [mm]

b _T1-maximum inlet width of blade.[mm]

The wheel hub form parameter of mixed flow turbine is: R ₂=16.1mm, α ₂=20 °, α ₃=3 °, D _o=φ 14.5mm, D _b=φ 42mm, Zm=22.5mm.

The beneficial effects of the utility model: the machine test of joining of Diesel Engine Plant of a few at home family shows, behind the pressurized machine of the equipped employing of motor H55 mixed flow turbine, with comparing of import with the shelves pressurized machine, consumption rate of fired oil decline 5～6g/kw.h, delivery temperature has descended about 60 ℃, has created good economic benefit and social benefit.

Description of drawings: the present invention has 8 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 vane thickness and inlet vane established angle schematic representation;

Fig. 5 is the regularity of distribution schematic representation of H55 turbine inlet blade angle;

Fig. 6 is an inlet vane retapering schematic representation;

Fig. 7 is a H55 mixed flow turbine meridian access diagram;

Fig. 8 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 10.

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--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.

As shown in Figure 3, for ease of adjusting blade profile curve, adopt both sides' journey pattern, Zm among Fig. 3 ₁For the separation of two equations, that is:

Z＝0～7.5

$\mathrm{\θ}=C_1\{1-{[1-{\left(\frac{7.5-Z}{b_1}\right)}^{p_1}]}^{\frac{1}{q_1}}\}$ [radian] ... ZL1

Z＝7.5～22.5

$\mathrm{\θ}=C_2\{1-{[1-{\left(\frac{Z-7.5}{b_2}\right)}^{p_2}]}^{\frac{1}{q_2}}\}$ [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 leaf packet road angle θ _bDetermine.For combined flow turbine, general Zm/D _1p=0.4～0.5 (D _1pAverage diameter for turbine inlet), D _2p=[(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.

As Fig. 4, shown in Figure 5, along turbine inlet width b _T1Blade angle β ₁, for reducing the eddy current loss that turbine inlet is in the blade convex surface, when when airflow direction is cut sth. askew blade, blade shape and air-flow relative velocity are matched, promptly form one so-called " the antecurvature turbine of cutting sth. askew ", it is to lean on the adjustment of the blade profile curve and the vane thickness regularity of distribution to realize.Fig. 5 shows the regularity of distribution of H55.

The relative inlet vane width of b-, b=b/b _T1

The inlet vane width of b-arbitrfary point, [mm]

b _T1-maximum inlet width of blade, [mm]

β ₁-relative inlet vane established angle,

β ₁＝β ₁/β _1max，

β ₁-inlet vane established angle, [degree]

β _1max-maximum inlet blade angle is generally 20～25 °.

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:

T _g＝2.8+0.20231*Z+0.0021445*Z ²-0.00191276*Z ³+0.000962052*Z ⁴

-0.00001403593*Z ⁵ [mm]……ZL·3

T _w＝0.25+0.0706667*Z-0.00336667*Z ²+0.00093333*Z ³

-0.0000133333*Z ⁴ [mm]……ZL·4

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

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

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

The vane thickness of arbitrfary point 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];

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

Rg, the hub radius at any Z value of 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＝0.9-0.02213*Z+0.001709*Z ²-0.00059795*Z ³+0.000022092*Z ⁴?ZL·6

Inlet's blade retapering as shown in Figure 6, for reducing the air impingement loss at turbine inlet place, to carry out retapering to inlet vane, determine that at inducer one revises the district, corresponding each Z value all has a Rx (revising the radius of starting point to gyration center), makes R=Rx substitution ZL.5 that formula is obtained the vane thickness T of this point, makes Tx=T again, utilize following formula to obtain the vane thickness T that revises section R＞Rx place, T=Tx*[0.5-0.0513 (R-Rx)+0.079998 (R-Rx) ²-0.178665 (R-Rx) ³] [mm]

……ZL·7。

Turbine meridian channel design as shown in Figure 7, its parameter is: R ₁=10.6mm, R ₂=16.1mm, α ₁=20 °, α ₂=20 °, α ₃=3 °, α ₄=8 °, D ₁=φ 47.75mm, D ₂=φ 45mm, D _o=φ 14.5mm, D _b=φ 42mm, b _T1=8.1mm, Zm=22.5mm.

As shown in Figure 8, 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, then finish, use the Proe modeling, turbine mold design and manufacturing;

, do not carry out the 4th step;

4. 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;

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

6. do you judge whether R 〉=Rw?

Be to return step 2;

, do not carry out the 7th step;

7. do you judge whether R 〉=Rx?

Be, make R=Rx and substitution ZL.5 formula ask Tx, ask T, carry out the 8th step with the ZL.7 formula;

Not, ask T, carry out the 8th step with the ZL.5 formula;

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

9. meet the 5th step, find the solution down a bit.

Claims (1)

1, a kind of H55 mixed flow turbine is characterized in that: wheel disc is the semi-open type wheel disc, and the number of blade is 10, and the blade profile curve of blade adopts both sides' journey pattern, that is:

Z＝0～7.5

$\mathrm{\θ}=C_1\{1-{[1-{\left(\frac{7.5-Z}{b_1}\right)}^{p_1}]}^{\frac{1}{q_1}}\}$ [radian]

Z＝7.5～22.5

$\mathrm{\θ}=C_2\{1-{[1-{\left(\frac{Z-7.5}{b_2}\right)}^{p_2}]}^{\frac{1}{q_2}}\}$ [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 mixed flow turbine, general Zm/D _1P=0.4～0.5, β _2p=30～40 °,

D _1PBe turbine inlet average diameter, D _2P=[(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

T _g＝2.8+0.20231*Z+0.0021445*Z ²-0.00191276*Z ³

+0.000962052*Z ⁴-0.00001403593*Z ⁵ [mm]

T _W＝0.25+0.0706667*Z-0.00336667*Z ²

+0.00093333*Z ³-0.0000133333*Z ⁴ [mm]

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

Tw---the vane thickness on the outer base cylinder, [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＝0.9-0.02213*Z+0.001709*Z ²-0.00059795*Z ³+0.000022092*Z ⁴

Inlet vane retapering equation is:

T＝Tx[0.5-0.0513(R-Rx)+0.079998(R-Rx) ²-0.178665(R-Rx) ³][mm]

In the formula: T---revise the vane thickness in district, [mm]

Tx---by equation in 4 calculate corresponding Z, the Rx vane thickness of ordering, [mm]

Rx---revise the start radius in district, [mm]

R---revise the radius of arbitrfary point, district, [mm]

Along b _T1The regularity of distribution of inlet vane established angle

β ₁＝β ₁/β _1max b＝b/b _T1

Wherein: β ₁The relative blade angle of-import,

β ₁-inlet vane established angle, [°], definition is referring to Fig. 4

β _1max-maximum inlet blade angle is generally 20～25 °

The relative inlet vane width of b-,

B-is the inlet vane width of any arbitrarily, [mm]

b _T1-maximum inlet width of blade .[mm]

The wheel hub form parameter of mixed flow turbine is: R ₂=16.1mm, α ₂=20 °, α ₃=3 °, D _o=φ 14.5mm, D _b=φ 42mm, Zm=22.5mm, R ₂---arc radius at the bottom of the turbine hub, α ₂---turbine inlet wheel hub angle of inclination, α ₃---turbine outlet wheel hub angle of inclination, D ₁---turbine inlet hub radius, D ₀---turbine outlet hub radius, Zm---turbine blade axial height.

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