CN201071830Y - Centrifugal impeller - Google Patents
Centrifugal impeller Download PDFInfo
- Publication number
- CN201071830Y CN201071830Y CNU2007200641082U CN200720064108U CN201071830Y CN 201071830 Y CN201071830 Y CN 201071830Y CN U2007200641082 U CNU2007200641082 U CN U2007200641082U CN 200720064108 U CN200720064108 U CN 200720064108U CN 201071830 Y CN201071830 Y CN 201071830Y
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- China
- Prior art keywords
- impeller
- wheel body
- vanes
- inducer
- blade
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- Expired - Lifetime
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Abstract
The utility model relates to a receded disk impeller of a gas-turbine compressor, which comprises an impeller wheel body fixedly connected with an impeller shaft. 9 to 20 front row inducer vanes are positioned on the front end of the impeller wheel body, and 18 to 40 back row impeller vanes are positioned on the rear end of the impeller wheel body; a clearance is positioned in the axial position between the front row inducer vanes and the back row impeller vanes; the front row inducer vanes and the back row impeller vanes are positioned in series along the axial direction. The axial length can be shortened by 10 to 15 percent, so that the length of the flow path in the integral type receded disk impeller is reduced, the overzoom on the suction surface of the integral type vanes is effectively prevented or deferred, the loss of a boundary layer is reduced, the efficiency and the load of the receded disk impeller are increased, the applied range of the utility model is widened and the impeller wheel body can not only be a whole body, but also be a separable combination. When the flow capacity is equivalent to the pressure ratio, compared with a regular centrifugal compressor of the same size, the efficiency of the gas compressor is increased by 1 to 2 percent and the load can be increased by 5 to 10 percent.
Description
Technical field
The utility model relates to a kind of compressor of motor, specifically relates to the centrifugal impeller of gas-turbine compressor.
Background technique
In the receded disk impeller field that compressed fluid is used, the effect of centrifugal impeller is to utilize the turbine merit to improve the pressure of air.In prior art, adopt usually to add a short blade between two linear leafs and for the Centrifugal Impeller formula.Yet increase along with load (comprising flow, pressure ratio etc.), flow process increases in the integral wheel, the circumferential pressure gradient increases, intermediate portion at its integral blade often forms secondary flow, cause airflow breakaway, reduce the even flow field degree of impeller outlet, thereby reduced the efficient of self and subsequent diffuser element and whole centrifugal level, influence the raising of gas compressor load and efficient, and then influence its application area.
Summary of the invention
The purpose of this utility model is to provide a kind of tandem type centrifugal impeller for overcoming the existing in prior technology problem, in order to improve the load and the efficient of centrifugal impeller, widens its application area in the fluid compression field.
Centrifugal impeller of the present utility model is made up of impeller wheel body and impeller shaft, the impeller wheel body is fixed on the impeller shaft, its main points are that described impeller wheel body front end is provided with the front-seat inducer blade of 9-20 sheet, impeller blade is arranged after being provided with the 18---40 sheet in the rear end, and the gap of a 0.5----1.5mm is arranged in axial positions between front-seat inducer blade and the back row's impeller blade; Front-seat inducer blade and back row's impeller blade tandem are vertically arranged, and the angle that staggers.
Centrifugal impeller of the present utility model with the advantage that the integrated type centrifugal impeller is compared is: owing to adopted forward and backward row's blade tandem type design, reduced the length of flow process in the integrated type centrifugal impeller, effectively prevent or delay the airflow breakaway of integral blade suction surface, reduce the boundary layer loss, the even flow field of impeller outlet, improved the efficient and the load of centrifugal impeller, widened its application area, but the impeller wheel body both can be also split combination of integral body.Under the flow condition suitable with pressure ratio, compressor efficiency improves 1-2% than the conventional centrifugal compressor of same size, and load can improve 5-10%.
Description of drawings
Fig. 1 is a structural representation of the present utility model
Fig. 2 is the utility model embodiment 2 a structural representation
1, front-seat inducer blade, 2, the gap, 3, back row's impeller blade, 4, the impeller wheel body, 5, impeller shaft, 6, the inducer wheel body, 7, the active wheel wheel body, 8, clamping bolt.
Embodiment
As seen from Figure 1, centrifugal impeller of the present utility model is made up of impeller wheel body 4 and impeller shaft 5, and impeller wheel body 4 is fixed on the impeller shaft 5.Front end at impeller wheel body 4 is provided with 15 front-seat inducer blades 1, and its inlet radius is 70mm, and going out port radius is 80mm, and the axial length of front-seat inducer blade 1 is 30mm.Row's impeller blade 3 after the rear end is provided with 30, its inlet radius is 80mm, going out port radius is 120mm.The axial length of back row's impeller blade 3 is 40mm, and the axial length of impeller wheel body 4 is 80mm.The gap 2 that one 0.75mm is arranged at axial position between front-seat inducer blade 1 and the back row's impeller blade 3.Front-seat inducer blade 1 and back row's impeller blade 3 tandem are vertically arranged, and the angle that staggers (angular dimension is determined according to blade quantity), make front-seat inducer blade 1 outlet be positioned at inclined to one side 20% place of row's impeller blade 3 suction surfaces, back.
As seen from Figure 2, centrifugal impeller of the present utility model is a separate assembling.Be made up of inducer wheel body 6, active wheel wheel body 7 and impeller shaft 5, inducer wheel body 6 and active wheel wheel body 7 are tightened up by clamping bolt 8 and are combined on the impeller shaft 5.Inducer wheel body 6 is provided with 15 front-seat inducer blades 1, and its inlet radius is 70mm, and going out port radius is 80mm, and the axial length of front-seat inducer blade 1 is 30mm.Row's impeller blade 3 after active wheel wheel body 7 is provided with 30, its inlet radius is 80mm, and going out port radius is 120mm, and the wheel body axial length after inducer wheel body 6 and 7 combinations of active wheel wheel body is 80mm.The gap 2 that one 0.75mm is arranged at axial position between front-seat inducer blade 1 and the back row's impeller blade 3.Front-seat inducer blade 1 and back row's impeller blade 3 tandem are vertically arranged, and the angle that staggers (angular dimension is determined according to blade quantity), make front-seat inducer blade 1 outlet be positioned at inclined to one side 20% place of row's impeller blade 3 suction surfaces, back.
Claims (3)
1. centrifugal impeller, form by impeller wheel body (4) and impeller shaft (5), impeller wheel body (4) is fixed on the impeller shaft (5), it is characterized in that: described impeller wheel body (4) front end is provided with the front-seat inducer blade (1) of 9-20 sheet, impeller blade (3) is arranged after being provided with the 18---40 sheet in the rear end, and the gap (2) of a 0.15----0.55mm is arranged in axial positions between front-seat inducer blade (1) and the back row's impeller blade (3).
2. centrifugal impeller according to claim 1 is characterized in that: front-seat inducer blade (1) and back row's impeller blade (3) tandem are vertically arranged and the angle that staggers.
3. centrifugal impeller according to claim 1 is characterized in that: inducer wheel body (6) and active wheel wheel body (7) are fixed tightly on the impeller shaft 5 by clamping bolt (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200641082U CN201071830Y (en) | 2007-08-10 | 2007-08-10 | Centrifugal impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200641082U CN201071830Y (en) | 2007-08-10 | 2007-08-10 | Centrifugal impeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201071830Y true CN201071830Y (en) | 2008-06-11 |
Family
ID=39550388
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007200641082U Expired - Lifetime CN201071830Y (en) | 2007-08-10 | 2007-08-10 | Centrifugal impeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201071830Y (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102588329A (en) * | 2012-03-13 | 2012-07-18 | 张仁田 | Axial-flow type water pump with blade-type adjustable line segment |
| CN103306739A (en) * | 2013-07-04 | 2013-09-18 | 中国航空动力机械研究所 | Centripetal impeller for gas turbine engine |
| CN103967837A (en) * | 2014-05-09 | 2014-08-06 | 中国航空动力机械研究所 | Compressor centrifugal vane wheel of aircraft engine |
| CN105298911A (en) * | 2015-12-03 | 2016-02-03 | 中国航空动力机械研究所 | Hollow centrifugal impeller |
| CN116291743A (en) * | 2023-05-18 | 2023-06-23 | 融通航空发动机科技有限公司 | Auxiliary power device for aircraft and combined mixed-flow turbine |
-
2007
- 2007-08-10 CN CNU2007200641082U patent/CN201071830Y/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102588329A (en) * | 2012-03-13 | 2012-07-18 | 张仁田 | Axial-flow type water pump with blade-type adjustable line segment |
| CN103306739A (en) * | 2013-07-04 | 2013-09-18 | 中国航空动力机械研究所 | Centripetal impeller for gas turbine engine |
| CN103306739B (en) * | 2013-07-04 | 2015-12-23 | 中国航空动力机械研究所 | A kind of gas turbine engine radial impeller |
| CN103967837A (en) * | 2014-05-09 | 2014-08-06 | 中国航空动力机械研究所 | Compressor centrifugal vane wheel of aircraft engine |
| CN105298911A (en) * | 2015-12-03 | 2016-02-03 | 中国航空动力机械研究所 | Hollow centrifugal impeller |
| CN105298911B (en) * | 2015-12-03 | 2017-11-24 | 中国航空动力机械研究所 | Hollow centrifugal impeller |
| CN116291743A (en) * | 2023-05-18 | 2023-06-23 | 融通航空发动机科技有限公司 | Auxiliary power device for aircraft and combined mixed-flow turbine |
| CN116291743B (en) * | 2023-05-18 | 2023-07-21 | 融通航空发动机科技有限公司 | Auxiliary power device for aircraft and combined mixed-flow turbine |
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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 |
Granted publication date: 20080611 |
|
| CX01 | Expiry of patent term |