CN111005770B - Centripetal turbine with splitter blades - Google Patents
Centripetal turbine with splitter blades Download PDFInfo
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- CN111005770B CN111005770B CN201911349318.XA CN201911349318A CN111005770B CN 111005770 B CN111005770 B CN 111005770B CN 201911349318 A CN201911349318 A CN 201911349318A CN 111005770 B CN111005770 B CN 111005770B
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- blade
- splitter
- blades
- main
- adjacent
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
Abstract
The invention aims to provide a centripetal turbine with splitter blades, which comprises a casing, a hub, main blades and splitter blades, wherein the main blades are arranged between the casing and the hub and arranged along the circumferential direction, the splitter blades are arranged on a channel formed by the hub between a suction surface of each main blade and a pressure surface of the adjacent main blade, the splitter blades are obliquely arranged in the channel relative to the two adjacent main blades, the front edges of the splitter blades are close to the main blades adjacent to the suction surface, and the tail edges of the splitter blades are close to the main blades adjacent to the pressure surface. The invention can inhibit circumferential separation of the main blade suction surface of the centripetal turbine, improve the blade load distribution, improve the turbine efficiency and work, and slightly expand the stable working range of the turbine.
Description
Technical Field
The invention relates to a turbine, in particular to a turbine for ships and aviation.
Background
The centripetal turbine has the advantages of simple structure, high reliability, high efficiency under the condition of small flow and the like, and is widely applied to the fields of ship power, aviation propulsion and the like. However, due to the characteristics of radial flow, high rotating speed and the like, the internal flow field of the turbine is relatively complex, and for a high-power miniature centripetal turbine, the flow field stability is damaged and the efficiency is reduced because of large separation flow caused by excessive expansion in a channel. Because the centripetal turbine has a compact structure and an active control mode is not easy to realize, a centripetal turbine for effectively and passively controlling flow separation is needed.
Disclosure of Invention
The invention aims to provide a centripetal turbine with splitter blades, which can inhibit circumferential separation of a suction surface of a main blade of the centripetal turbine, improve the load distribution of the blades, improve the efficiency and the work of the turbine and slightly expand the stable working range of the turbine.
The purpose of the invention is realized as follows:
the invention relates to a centripetal turbine with splitter blades, which is characterized in that: the main blades are arranged between the casing and the hub and arranged along the circumferential direction, the splitter blades are arranged on a channel formed by the hub between the suction surface of each main blade and the pressure surface of the adjacent main blade, the splitter blades are obliquely arranged in the channel relative to the two adjacent main blades, the front edges of the splitter blades are close to the main blades adjacent to the suction surface, and the tail edges of the splitter blades are close to the main blades adjacent to the pressure surface.
The present invention may further comprise:
1. the front edge of the splitter blade is positioned 0.05-0.15 axial chord length of the main blade before the starting point of the main blade separation area adjacent to the splitter blade, which is a suction surface.
2. The axial chord length of the splitter blade is 1-1.5 times of the axial chord length of the separation area of the suction surface of the main blade.
3. The height of the splitter blade is equal to the coaxial position of the adjacent main blade.
4. The maximum thickness of the splitter blade is 0.5-1 times of that of the main blade.
The invention has the advantages that: the invention installs splitter blades near the easy separation area of the suction surface of the main blade of the turbine. The front edge of the splitter blade is close to the pressure surface, the tail edge of the splitter blade is close to the suction surface of the adjacent blade, so that a diffusion structure is formed near the easy separation area of the suction surface of the main blade, the forward pressure gradient is reduced, the separation of the boundary layer caused by over acceleration is prevented, meanwhile, the pressure surface of the adjacent blade forms a spray pipe structure, the working amount of fluid is increased, meanwhile, the axial size and the turning angle of the splitter blade are smaller, the loss is not easy to increase due to the separation, and the influence on the weight of the turbine is smaller, so the structure can improve the pneumatic performance of the centripetal turbine on the whole.
Drawings
FIG. 1 is a cross-sectional view of the present invention.
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
referring to fig. 1, the invention comprises a casing 1, a hub 4, main blades 2 and splitter blades 3, wherein the main blades 2 are arranged between the casing 1 and the hub 4 and are uniformly arranged along the circumferential direction, the splitter blades 3 are arranged on the channel hub 4 between the suction surfaces and the pressure surfaces of two adjacent main blades 2, the front edges of the splitter blades 3 are close to the suction surfaces of the main blades 2, and the tail edges of the splitter blades are close to the pressure surfaces of the adjacent main blades 2. The front edge of the splitter blade 3 is located 0.05-0.15 axial chord length of the main blade 2 in front of the starting point of the separation area of the suction surface of the main blade 2. The axial chord length of the splitter blade 3 is 1-1.5 times of the axial chord length of the separation area of the suction surface of the main blade 2. The height of the splitter blade 3 is equal to the coaxial position of the main blade 2. The maximum thickness of the splitter blade 3 is 0.5-1 times of that of the main blade 2.
The specific design steps are as follows:
and determining the leading edge installation angle and the trailing edge installation angle of the splitter blade 3 according to the main flow airflow angle in front of the easy-separation area of the suction surface of the main turbine blade 2 and the pressure distribution condition of the pressure surface of the adjacent blade at the same axial position.
And determining the maximum thickness of the splitter blade according to the structural factors such as the flow working range of the turbine, the weight of the blade and the like.
The axial chord length of the splitter blade is determined according to the flow field distribution in the turbine channel, and the actual three-dimensional structure of the splitter blade is finely adjusted by means of research methods such as tests or numerical simulation.
According to the flow field condition in the channel, the front edge of the splitter blade 3 is positioned 0.05-0.15 axial chord length of the main blade 2 in front of the starting point of the separation area of the suction surface of the main blade 2. The axial chord length of the splitter blade 3 is 1-1.5 times of the axial chord length of the separation area of the suction surface of the main blade 2, if the axial chord length is too long, the improvement condition of the separation flow is limited, the weight of the turbine is increased, if the axial chord length is too short, the influence on the separation flow is small, and the control effect is weakened. The splitter blade 3 is the same height as the main blade 2 in the same axial position. The maximum width of the splitter blade 3 is 0.5-1 times of that of the main blade.
In summary, the object of the present invention is to provide a radial inflow turbine with splitter blades arranged downstream in the hub endwall, comprising a casing 1, main blades 2, splitter blades 3 and a hub 4. Turbine main blades 2 are uniformly arranged between the casing 1 and the hub 4 along the circumferential direction, and splitter blades 3 are arranged on the end wall of the hub 4 between the turbine main blades 2. The centripetal turbine with the splitter blades 3 arranged between the main blades 2 designed by the invention can obviously improve the flow stability in the moving blade channel, improve the load distribution on two sides of the main blades 2 and reduce the loss caused by separation vortex, thereby improving the stable working range, efficiency and work capacity of the turbine.
Claims (5)
1. A centripetal turbine with splitter blades is characterized in that: the main blades are arranged between the casing and the hub and arranged along the circumferential direction, the splitter blade is arranged on a channel formed by the hub between the suction surface of each main blade and the pressure surface of the adjacent main blade, the splitter blades are obliquely arranged in the channel relative to the two adjacent main blades, the front edge of each splitter blade is close to the main blade adjacent to the suction surface, and the tail edge of each splitter blade is close to the main blade adjacent to the pressure surface;
the front edge of the splitter blade is located 0.05-0.15 time of the axial chord length of the main blade before the starting point of the main blade separation area adjacent to the splitter blade, wherein the starting point of the main blade separation area is a suction surface.
2. A centripetal turbine with splitter blades according to claim 1, wherein: the axial chord length of the splitter blade is 1-1.5 times of the axial chord length of the separation area of the suction surface of the main blade.
3. A centripetal turbine with splitter blades according to claim 1 or 2, wherein: the height of the splitter blade is equal to the coaxial position of the adjacent main blade.
4. A centripetal turbine with splitter blades according to claim 1 or 2, wherein: the maximum thickness of the splitter blade is 0.5-1 times of that of the main blade.
5. A centripetal turbine with splitter blades according to claim 3, wherein: the maximum thickness of the splitter blade is 0.5-1 times of that of the main blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911349318.XA CN111005770B (en) | 2019-12-24 | 2019-12-24 | Centripetal turbine with splitter blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911349318.XA CN111005770B (en) | 2019-12-24 | 2019-12-24 | Centripetal turbine with splitter blades |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111005770A CN111005770A (en) | 2020-04-14 |
| CN111005770B true CN111005770B (en) | 2022-06-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911349318.XA Active CN111005770B (en) | 2019-12-24 | 2019-12-24 | Centripetal turbine with splitter blades |
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| CN (1) | CN111005770B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113513368B (en) * | 2021-07-08 | 2022-09-02 | 哈尔滨工程大学 | Turbine capable of directly backing with primary and secondary moving blade structures |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102251811A (en) * | 2011-07-13 | 2011-11-23 | 哈尔滨工程大学 | Radial flow type turbine with splitter blade |
| CN106481369A (en) * | 2016-11-01 | 2017-03-08 | 南京航空航天大学 | A kind of shunting leaflet structure controlling stators flow separation |
| JP2017203410A (en) * | 2016-05-11 | 2017-11-16 | 株式会社豊田自動織機 | Supercharger |
| CN207554416U (en) * | 2017-12-04 | 2018-06-29 | 中国人民解放军总参谋部第六十研究所 | A kind of centrifugal impeller of splitterr vanes |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8961107B2 (en) * | 2012-05-17 | 2015-02-24 | Adda Corp. | Heat-dissipation fan |
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2019
- 2019-12-24 CN CN201911349318.XA patent/CN111005770B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102251811A (en) * | 2011-07-13 | 2011-11-23 | 哈尔滨工程大学 | Radial flow type turbine with splitter blade |
| JP2017203410A (en) * | 2016-05-11 | 2017-11-16 | 株式会社豊田自動織機 | Supercharger |
| CN106481369A (en) * | 2016-11-01 | 2017-03-08 | 南京航空航天大学 | A kind of shunting leaflet structure controlling stators flow separation |
| CN207554416U (en) * | 2017-12-04 | 2018-06-29 | 中国人民解放军总参谋部第六十研究所 | A kind of centrifugal impeller of splitterr vanes |
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| CN111005770A (en) | 2020-04-14 |
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