CN203067037U - Turbine of turbocharger - Google Patents
Turbine of turbocharger Download PDFInfo
- Publication number
- CN203067037U CN203067037U CN 201320064667 CN201320064667U CN203067037U CN 203067037 U CN203067037 U CN 203067037U CN 201320064667 CN201320064667 CN 201320064667 CN 201320064667 U CN201320064667 U CN 201320064667U CN 203067037 U CN203067037 U CN 203067037U
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- Prior art keywords
- blade
- turbine
- angle
- wheel disc
- turbocharger
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a turbine of a turbocharger. The turbine comprises a wheel disc, wherein the wheel disc is a semi-open type wheel disc; a hub is arranged on one side of the wheel disc; a plurality of blades are uniformly arranged on the outer circumference of the hub; a turbine airflow passage is formed between two adjacent blades; and the section of each blade adopts a variable cross-section structure. The turbine of the turbocharger adopts the technical scheme, and during assembly, a blade type turbine is adopted. Compared with an original supercharger imported from abroad, the turbine of the turbocharger has the advantages that a whole line of the fuel oil consumption rate is lowered to different extents, the optimum point is lowered by more than 10 g/kwh, and good economic and social benefits are created.
Description
Technical field
The utility model relates to a kind of turbine of turbosupercharger, belongs to field of internal combustion engine.
Background technique
Turbosupercharger is the vitals that improves power of IC engine, reduction fuel consumption rate, improves discharging.As a new technology, turbosupercharger has promoted the development of internal-combustion engine, has improved the technical performance of internal-combustion engine, has been acknowledged as one of developing direction of internal-combustion engine, is still keeping growth momentum in the ascendant so far.Turbine is the vital part of turbosupercharger, and it is worked under high temperature, high-speed condition, and its effect is the mechanical work that the exhaust energy of internal-combustion engine is converted to the coaxial high speed rotation of drive gas compressor.Because the turbine operating conditions is extremely harsh, abominable, the requirement that the design of turbine not only will be satisfied aerodynamic performance reaches good performance to guarantee turbine, guarantees that again turbine blade has enough strength and stiffness simultaneously, and design difficulty is well imagined.At present, in the design of turbine, often more consider from structural strength, efficient is made some sacrifices, cause turbine efficiency on the low side, be embodied on the coupling of motor, then Engine torque is less than normal, oil consumption is high, and the urgent need design is a kind of can satisfy structural strength, can obtain the new blade profile turbine of big performance boost again, to adapt to client's expectation more and more higher to booster performance.
The model utility content:
The utility model provides a kind of turbocharger turbine that can improve combustion engine powered property by a relatively large margin, reduce the internal-combustion engine oil consumption at the inefficient defective of conventional turbine.
For addressing the above problem, the utility model adopts following technological scheme:
A kind of turbocharger turbine comprises wheel disc, and described wheel disc is the semi-open type wheel disc, one side of described wheel disc is provided with wheel hub, evenly be provided with some blades on the excircle of wheel hub, form the turbine airflow passage between the adjacent vanes, described blade profile adopts variable section structure.
Below be the utility model to the further optimization of such scheme: the number of described blade is 10.
Further optimize: the entrance width of described turbine is that 10 ± 1.5mm, inlet diameter are φ 75.5 ± 1.5mm; Outlet diameter is that φ 69 ± 1.5mm, hub diameter are φ 23 ± 1.5mm.
Further optimize: described blade has blade tip and blade root, and the spacing between the blade tip of described adjacent blades is 21.3 ± 1.5mm, and the spacing between the blade root of adjacent blades is 7.6 ± 1.5mm.
Further optimize: the axial chord length of the blade tip of described blade is 14 ± 1.5mm, and the axial chord length of the blade root of blade is 26.7 ± 1.5mm.
Further optimize: described blade has inlet side and outlet limit respectively, forms the mean camber line bending angle between the tangent line of the tangent line of the inlet side mean camber line of described blade and outlet limit mean camber line, and this mean camber line bending angle is 64 ± 3 degree.
Further optimize: tangent line and the angle between the turbine axis of the inlet side mean camber line of described blade are inlet blade angle, and this inlet blade angle is 74 ± 3 degree.
Further optimize: tangent line and the angle between the turbine axis of described outlet limit mean camber line are blade outlet angle, and this blade outlet angle is 62.5 ± 3 degree.
Further optimize: outlet limit airflow direction and the angle between the turbine axis of described blade are efflux angles, and this efflux angles is 83.5 ± 3 degree.
The utility model adopts such scheme, the machine test of joining at certain 7 liters of diesel engine of main engine factory shows, behind equipped this blade profile turbine of employing, compare with first wife's external inlet plenum device, the consumption rate of fired oil sliver has decline in various degree, more than the optimum point decline 10g/kwh, good economic benefit and social benefit have been created.
The utility model is described in further detail below in conjunction with drawings and Examples.
Description of drawings
Accompanying drawing 1 is the utility model embodiment's structural representation;
Accompanying drawing 2 is blade profile schematic representation of the utility model embodiment;
Accompanying drawing 4 is that schematic representation is arranged in the expansion of blade among the model utility embodiment.
Among the figure: the 1-wheel disc; The 2-blade; The 3-blade profile; The 4-wheel hub; 5-turbine airflow passage; D
0-hub diameter; D
1-turbine inlet diameter; D
2-turbine outlet diameter; B-turbine inlet width; L
1-spacing; L
2-axial chord length; α
1-mean camber line bending angle; α
2-inlet blade angle; α
3-efflux angles; α
4-blade outlet angle; The a-blade tip; B-blade root; C-turbine axis; The e-inlet side; F-exports the limit; The tangent line of g-inlet side mean camber line; The tangent line of h-outlet limit mean camber line.
Embodiment
Embodiment, as shown in Figure 1, a kind of turbocharger turbine, comprise wheel disc 1, described wheel disc 1 is the semi-open type wheel disc, and a side of described wheel disc 1 is provided with wheel hub 4, on the excircle of wheel hub 4, evenly be provided with 10 blades 2, form turbine airflow passage 5 between the adjacent vanes 2, as shown in Figure 2, described blade profile 3 adopts variable section structure.
As shown in Figure 3, Figure 4, the entrance width B of described turbine is that 10 ± 1.5mm, inlet diameter D1 are φ 75.5 ± 1.5mm; Outlet diameter D2 is that φ 69 ± 1.5mm, hub diameter D0 are φ 23 ± 1.5mm.
Described blade 2 has blade tip a and blade root b, and the spacing L1 between the blade tip of described adjacent blades is 21.3 ± 1.5mm, and the spacing between the blade root of adjacent blades is 7.6 ± 1.5mm.
The axial chord length L2 of the blade tip of described blade 2 is 14 ± 1.5mm, and the axial chord length of the blade root of blade 2 is 26.7 ± 1.5mm.
Described blade has inlet side e and outlet limit f respectively, forms the mean camber line bend angles alpha between the tangent line h of the tangent line g of the inlet side mean camber line of described blade and outlet limit mean camber line
1, this mean camber line bend angles alpha
1Be 64 ± 3 degree.
Angle between the tangent line g of the inlet side mean camber line of described blade and the turbine axis c is inlet blade angle α
2, this inlet blade angle α
2Be 74 ± 3 degree.
Tangent line h and the angle between the turbine axis of described outlet limit mean camber line are angle of impeller outlet alpha
4, this angle of impeller outlet alpha
4Be 62.5 ± 3 degree.
Outlet limit airflow direction and the angle between the turbine axis of described blade are efflux angles α
3, this efflux angles α
3Be 83.5 ± 3 degree.
But the equal proportion convergent-divergent forms the same blade profile turbine of different flow scope.
We have been described in detail invention according to the national patent method now, can identify improvement or the replacement of specific embodiment disclosed herein for those skilled in the art.These modifications are within the spirit and scope of the present invention.
Claims (9)
1. turbocharger turbine, comprise wheel disc (1), it is characterized in that: described wheel disc (1) is the semi-open type wheel disc, one side of described wheel disc (1) is provided with wheel hub (4), on the excircle of wheel hub (4), evenly be provided with some blades (2), form turbine airflow passage (5) between the adjacent vanes (2), described blade profile (3) adopts variable section structure.
2. a kind of turbocharger turbine according to claim 1, it is characterized in that: the number of described blade is 10.
3. a kind of turbocharger turbine according to claim 1 and 2 is characterized in that:
The entrance width of described turbine (B) is that 10 ± 1.5mm, inlet diameter (D1) are φ 75.5 ± 1.5mm; Outlet diameter (D2) is that φ 69 ± 1.5mm, hub diameter (D0) are φ 23 ± 1.5mm.
4. a kind of turbocharger turbine according to claim 3, it is characterized in that: described blade (2) has blade tip (a) and blade root (b), spacing between the blade tip of described adjacent blades (L1) is 21.3 ± 1.5mm, and the spacing between the blade root of adjacent blades is 7.6 ± 1.5mm.
5. a kind of turbocharger turbine according to claim 4, it is characterized in that: the axial chord length of blade tip (L2) of described blade (2) is 14 ± 1.5mm, the axial chord length of blade root of blade (2) is 26.7 ± 1.5mm.
6. a kind of turbocharger turbine according to claim 5 is characterized in that:
Described blade has inlet side (e) and outlet limit (f) respectively, forms mean camber line bending angle (α between the tangent line (h) of the tangent line (g) of the inlet side mean camber line of described blade and outlet limit mean camber line
1), this mean camber line bending angle (α
1) be 64 ± 3 degree.
7. a kind of turbocharger turbine according to claim 6, it is characterized in that: the tangent line (g) of the inlet side mean camber line of described blade and the angle between the turbine axis (c) are inlet blade angle (α
2), this inlet blade angle (α
2) be 74 ± 3 degree.
8. a kind of turbocharger turbine according to claim 7, it is characterized in that: the tangent line (h) of described outlet limit mean camber line and the angle between the turbine axis are blade outlet angle (α
4), this blade outlet angle (α
4) be 62.5 ± 3 degree.
9. a kind of turbocharger turbine according to claim 8, it is characterized in that: outlet limit airflow direction and the angle between the turbine axis of described blade are efflux angles (α
3), this efflux angles (α
3) be 83.5 ± 3 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320064667 CN203067037U (en) | 2013-01-31 | 2013-01-31 | Turbine of turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320064667 CN203067037U (en) | 2013-01-31 | 2013-01-31 | Turbine of turbocharger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203067037U true CN203067037U (en) | 2013-07-17 |
Family
ID=48765846
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320064667 Expired - Lifetime CN203067037U (en) | 2013-01-31 | 2013-01-31 | Turbine of turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203067037U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106194275A (en) * | 2014-12-08 | 2016-12-07 | 现代自动车株式会社 | Turbine wheel for turbocharger |
| CN114001050A (en) * | 2021-10-25 | 2022-02-01 | 中车大连机车研究所有限公司 | Compressor impeller for fuel cell air compressor |
-
2013
- 2013-01-31 CN CN 201320064667 patent/CN203067037U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106194275A (en) * | 2014-12-08 | 2016-12-07 | 现代自动车株式会社 | Turbine wheel for turbocharger |
| CN114001050A (en) * | 2021-10-25 | 2022-02-01 | 中车大连机车研究所有限公司 | Compressor impeller for fuel cell air compressor |
| CN114001050B (en) * | 2021-10-25 | 2024-06-04 | 中车大连机车研究所有限公司 | Compressor impeller for fuel cell air compressor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130717 |