CN104234755A - Centripetal turbine blade back small wing structure capable of inhibiting clearance leakage - Google Patents
Centripetal turbine blade back small wing structure capable of inhibiting clearance leakage Download PDFInfo
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- CN104234755A CN104234755A CN201410478612.1A CN201410478612A CN104234755A CN 104234755 A CN104234755 A CN 104234755A CN 201410478612 A CN201410478612 A CN 201410478612A CN 104234755 A CN104234755 A CN 104234755A
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Abstract
The invention discloses a centripetal turbine blade back small wing structure used for a turbocharger of an aviation piston engine. Small wings are constructed at the back of an opened centripetal turbine blade, and three implementation forms of the small wings are as follows: constructing one small wing on a suction surface of the back of the blade, constructing one small wing on a pressure surface, and constructing the rest small wings respectively at the two sides of the blade. The centripetal turbine blade back small wing structure has the advantages that (1) the small wing on the pressure surface of the back is capable of effectively inhibiting gas being leaked onto the suction surface of the blade through gaps at the back of a turbine from the pressure surface of the blade, so that leakage loss is reduced, and the efficiency of the turbine is improved; (2) the small wing on the suction surface is capable of effectively inhibiting vortex being generated near the gaps of the blade back of the suction surface, so that the actual acting ability of the blade is improved; (3) the small wings at the two sides of the blade can integrate the advantages of the small wing on the suction surface and the small wing on the pressure surface, and the weight of the turbine and the blade back friction loss are slightly increased, so that the turbine efficiency is improved on the whole.
Description
Technical field
The present invention relates to aviation piston engine turbocharging technology field, relate to centripetal turbine pneumatic design, heat transfer and structural design, specifically then for the centripetal turbine with the turbine blade back of improving centripetal turbine efficiency with little wing structure is revealed in a kind of gap that suppresses.
Background technique
The turbine stage of turbosupercharger is operated in hot environment, and high rotating speed lower blade and wheel disc bear very large aerodynamic force and centrifugal force, and under the prerequisite ensureing the reliable and stable work of turbosupercharger, how improving the efficiency of turbine, is a challenge of pneumatic design.
Centripetal turbine has that structure is simple, cost is low, single-stage pressure ratio high, and open type centripetal turbine is a kind of typical structure.Wheel disc, on the basis of conventional turbine, is reduced to root of blade by open type turbine, reduces rotor weight and rotary inertia to greatest extent, reduces wheel disc and root stress.
Open type centripetal turbine has advantage in intensity He in weight, but introduces new loss on pneumatic, and namely loss is revealed in blade back gap.Domestic and international correlative study shows, gap loss is the chief component of turbomachine aerodynamic loss, and blade back loss accounts for the ratio that whole gap loss is about half.The flow characteristic (see accompanying drawing 1) in visible research blade back gap, it is necessary for finding out the measure reducing the leakage loss of blade back gap.
The present invention proposes a kind of gap that suppresses to reveal with the blade back winglet structure improving centripetal turbine efficiency, solve this problem preferably.
Summary of the invention
For the advantages and disadvantages of existing open type turbine, the present invention proposes a kind of gap that suppresses and reveal with the blade back winglet structure improving centripetal turbine efficiency, the turbine efficiency decline that can effectively suppress blade back gap to be revealed to cause.
In order to reach above-mentioned purpose, the present invention takes following technical solution:
1) for a kind of centripetal turbine blade back winglet structure suppressing gap to be revealed of the turbosupercharger of aviation piston engine, to it is characterized in that: the winglet at described turbine blade back structure.Winglet is approximately perpendicular to blade tangent plane and arranges.Winglet width W is 1-1.5 times of vane thickness T, height H is 1.5-2.2 times of vane thickness T, winglet and spoon of blade knuckle radius R1 are 1.2-1.5 times of vane thickness T, winglet tip is wedge shape and has knuckle radius R2 to be the 1.0-1.33 fillet doubly of vane thickness T, blade is wedge shape, and included angle A is about 7.5-10 degree.Winglet is equal with gap, blade back with the gap at back.
2) for a kind of centripetal turbine blade back winglet structure suppressing gap to be revealed of the turbosupercharger of aviation piston engine, it is characterized in that: be all furnished with winglet in described turbine blade backside pressure face and suction surface.
Arrange that winglet restrained effectively gas and is leaked to blade suction surface from blade pressure surface by gap, turbine back at blade back pressure side, reduce and reveal loss, improve turbine efficiency (principle is shown in schematic diagram 4); Suction surface winglet suppresses the generation of suction surface blade back near gaps vortex effectively, improves the actual acting ability of blade, and slightly winglet principle is the same to arrange leaf with wing; Blade both sides winglet has then concentrated the above two advantage, just slightly increases turbine weight and blade back frictional loss, generally speaking also improves turbine efficiency.
3) a kind of a kind of centripetal turbine blade back winglet structure suppressing gap to be revealed of the turbosupercharger for aviation piston engine, it is characterized in that: be furnished with winglet in described turbine blade backside pressure face, but suction surface is not arranged, suction surface keeps the curved-surface structure similar to vane nose.
4) a kind of a kind of centripetal turbine blade back winglet structure suppressing gap to be revealed of the turbosupercharger for aviation piston engine, it is characterized in that: at described turbine blade back, suction surface is furnished with winglet, but pressure side is not arranged, pressure side keeps the curved-surface structure similar to vane nose.
Accompanying drawing explanation
Signal and schematic diagram thereof are revealed in Fig. 1 turbine blade back;
The general open type turbine schematic diagram of Fig. 2 A;
Open type turbine schematic diagram with blade back winglet in Fig. 2 B the present invention;
Fig. 3 A does not arrange suction surface flow field, turbine blade back schematic diagram under winglet condition;
Suction surface flow field, turbine blade back schematic diagram under Fig. 3 B layout winglet condition;
Fig. 4 A does not arrange turbine blade backside pressure surface current field schematic diagram under winglet condition;
Turbine blade backside pressure surface current field schematic diagram under Fig. 4 B layout winglet condition;
Winglet form schematic diagram is all arranged in Fig. 5 A turbine blade backside pressure face and suction surface both sides;
Fig. 5 B turbine blade back suction surface arranges winglet form schematic diagram;
Winglet form schematic diagram is arranged in Fig. 5 C turbine blade backside pressure face;
Fig. 6 turbine blade back winglet scale diagrams.
Embodiment
At turbine blade back, one little wing structure is set with the form being approximately perpendicular to blade tangent plane, as shown in Figure 2 B.Winglet width W is 1-1.5 times of vane thickness T, height H is 1.5-2.2 times of vane thickness T, winglet and spoon of blade knuckle radius R1 are 1.2-1.5 times of vane thickness T, winglet tip is wedge shape and has knuckle radius R2 to be the 1.0-1.33 fillet doubly of vane thickness T, blade is wedge shape, included angle A is about 7.5-10 degree, and winglet is equal with gap, blade back with the gap at back, as shown in Figure 6.
Wherein a kind of embodiment is, is all furnished with winglet, as shown in Figure 5A in turbine blade backside pressure face and suction surface.Arrange that winglet restrained effectively gas and is leaked to blade suction surface from blade pressure surface by gap, turbine back at blade back pressure side, reduce and reveal loss, improve turbine efficiency, as shown in figs. 4 a-4b; Suction surface winglet suppresses the generation of suction surface blade back near gaps vortex effectively, improves the actual acting ability of blade, and slightly winglet principle is the same to arrange leaf with wing, as shown in figs 3 a and 3b; Blade both sides winglet has then concentrated the above two advantage, just slightly increases turbine weight and blade back frictional loss, generally speaking also improves turbine efficiency.
Another kind of embodiment is that be only furnished with winglet in turbine blade backside pressure face, as shown in Figure 5 C, but suction surface is not arranged, suction surface keeps the curved-surface structure similar to vane nose.
Another embodiment is, be only furnished with winglet at turbine blade back suction surface, as shown in Figure 5 B, but pressure side is not arranged, pressure side keeps the curved-surface structure similar to vane nose.
Claims (4)
1. turbine blade back has a centripetal turbine for little wing structure, described turbine is used for the turbosupercharger of aviation piston engine, it is characterized in that: the winglet being approximately perpendicular to blade tangent plane at described turbine blade back structure.Winglet width is 1-1.5 times of vane thickness, winglet height is 1.5-2.2 times of vane thickness, winglet and spoon of blade knuckle radius are 1.2-1.5 times of vane thickness, winglet tip is wedge shape and has knuckle radius to be vane thickness 1.0-1.33 fillet doubly, and blade integral is the wedge-shaped structure that angle is about 7.5-10 degree.Winglet is equal with gap, blade back with the gap at back.
2. centripetal turbine as claimed in claim 1, is characterized in that: be all furnished with described winglet in described turbine blade backside pressure face and suction surface.
3. centripetal turbine as claimed in claim 1, is characterized in that: be only furnished with winglet in described turbine blade backside pressure face, and its suction surface is not arranged, described suction surface keeps the curved-surface structure similar to vane nose.
4. centripetal turbine as claimed in claim 1, is characterized in that: at described turbine blade back, suction surface is furnished with winglet, and its pressure side is not arranged, described pressure side keeps the curved-surface structure similar to vane nose.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410478612.1A CN104234755A (en) | 2014-09-18 | 2014-09-18 | Centripetal turbine blade back small wing structure capable of inhibiting clearance leakage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410478612.1A CN104234755A (en) | 2014-09-18 | 2014-09-18 | Centripetal turbine blade back small wing structure capable of inhibiting clearance leakage |
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| CN104234755A true CN104234755A (en) | 2014-12-24 |
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| CN201410478612.1A Pending CN104234755A (en) | 2014-09-18 | 2014-09-18 | Centripetal turbine blade back small wing structure capable of inhibiting clearance leakage |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105604611A (en) * | 2016-03-03 | 2016-05-25 | 哈尔滨工程大学 | Variable-geometry turbine with strake wing structure of moving blade |
| CN106870013A (en) * | 2017-02-21 | 2017-06-20 | 戴劲松 | The turbine rotor blade of inter-blade channel expansion |
| CN106979174A (en) * | 2017-05-12 | 2017-07-25 | 中国航发湖南动力机械研究所 | centripetal turbine frequency modulation method, device and centripetal turbine |
| CN113062774A (en) * | 2021-04-25 | 2021-07-02 | 中国航发湖南动力机械研究所 | Semi-open centripetal turbine and gas turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4066381A (en) * | 1976-07-19 | 1978-01-03 | Hydragon Corporation | Turbine stator nozzles |
| WO2003010433A1 (en) * | 2001-07-23 | 2003-02-06 | Ramgen Power Systems, Inc. | Radial impulse turbine for rotary ramjet engine |
| CN101178011A (en) * | 2007-11-23 | 2008-05-14 | 西安交通大学 | Impeller structure of centripetal turbine |
| CN102691527A (en) * | 2012-06-12 | 2012-09-26 | 中国科学院工程热物理研究所 | Groove structure on back of open centripetal turbine blade |
-
2014
- 2014-09-18 CN CN201410478612.1A patent/CN104234755A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4066381A (en) * | 1976-07-19 | 1978-01-03 | Hydragon Corporation | Turbine stator nozzles |
| WO2003010433A1 (en) * | 2001-07-23 | 2003-02-06 | Ramgen Power Systems, Inc. | Radial impulse turbine for rotary ramjet engine |
| CN101178011A (en) * | 2007-11-23 | 2008-05-14 | 西安交通大学 | Impeller structure of centripetal turbine |
| CN102691527A (en) * | 2012-06-12 | 2012-09-26 | 中国科学院工程热物理研究所 | Groove structure on back of open centripetal turbine blade |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105604611A (en) * | 2016-03-03 | 2016-05-25 | 哈尔滨工程大学 | Variable-geometry turbine with strake wing structure of moving blade |
| CN106870013A (en) * | 2017-02-21 | 2017-06-20 | 戴劲松 | The turbine rotor blade of inter-blade channel expansion |
| CN106979174A (en) * | 2017-05-12 | 2017-07-25 | 中国航发湖南动力机械研究所 | centripetal turbine frequency modulation method, device and centripetal turbine |
| CN113062774A (en) * | 2021-04-25 | 2021-07-02 | 中国航发湖南动力机械研究所 | Semi-open centripetal turbine and gas turbine |
| CN113062774B (en) * | 2021-04-25 | 2022-06-21 | 中国航发湖南动力机械研究所 | Semi-open centripetal turbine and gas turbine |
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Application publication date: 20141224 |