CN203500120U - Centrifugal compressor diffuser blade structure - Google Patents
Centrifugal compressor diffuser blade structure Download PDFInfo
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- CN203500120U CN203500120U CN201320602739.0U CN201320602739U CN203500120U CN 203500120 U CN203500120 U CN 203500120U CN 201320602739 U CN201320602739 U CN 201320602739U CN 203500120 U CN203500120 U CN 203500120U
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- diffuser
- centrifugal compressor
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- blade structure
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Abstract
The utility model belongs to the technical field of centrifugal compressors, particularly relates to a centrifugal compressor diffuser blade structure, wherein a plurality of diffuser blades are uniformly distributed on a blade plate along the peripheral direction, and are of an arc shape, and cone-shaped structures are arranged on the front edges of the diffuser blades. The front ends of the diffuser blades comprise top sides, pressure surface sides and suction surface sides, and the top sides, the pressure surface sides and the suction surface sides are chamfered to form the cone-shaped structures. The centrifugal compressor diffuser blade structure is applied in a big centrifugal air compressor unit, can effectively reduce total vibration of pipelines, in particular to vibration amplitude of the blades under frequency, and prevents shut-down accidents of centrifugal compressors caused by damage of pipelines from happening.
Description
Technical field
The utility model belongs to centrifugal compressor diffuser technical field, specifically a kind of centrifugal compressor diffuser blade structure.
Background technique
Diffuser is the critical component of centrifugal compressor, and it can make from impeller the air-flow with fair speed out slow down, and makes kinetic energy effectively be converted into pressure energy, particularly vane diffuser, remarkable to improving the whole efficiency effect of compressor.
In compressor operation process, diffuser vane and impeller blade mutually coupling will cause larger pressure pulsation, and this pressure pulsation is mainly blade pass overdriving, and its frequency is blade passing frequency, and concrete numerical value is that rotor speed is multiplied by impeller blade number.Noise size and the outlet conduit vibratory output of compressor controlled in blade pass overdriving, i.e. blade pass overdriving is larger, and compressor noise is larger, pipe vibration is also larger, and vice versa, under extreme conditions, it even can cause export pipeline to destroy, the tube wall vibration shape that the mode of its destruction is high frequency.
Solve the Compressor Pipes destruction or the noise problems of too that because of diffuser vane, cause both at home and abroad and have following several method: change vane diffuser into vaneless diffuser, this method is the most thorough for solving problems, but it affects the whole efficiency of compressor greatly, some producers are forced to change the vane diffuser of overall height into half high diffuser vane, but decrease in efficiency is still obvious; Another kind of solution pipe vibration and the excessive method of noise are on Diffuser, to add Helmholtz resonator, and experiment shows that adding such device can make compressor overall noise reduce about 10dBA, but such device processed complex and expense are higher.Also having a kind of method that solves pipe vibration and noise problems of too is to add sound absorption structure at pipe interior, but the operability of such problem and practical effect need further to be proved.
Model utility content
For the problems referred to above, the purpose of this utility model is to provide a kind of centrifugal compressor diffuser blade structure.This centrifugal compressor diffuser blade structure can improve the Flow Field Distribution of diffuser vane leading edge, solves centrifugal compressor pipe vibration problem, is mainly used among large centrifugal air compressor group.
To achieve these goals, the utility model is by the following technical solutions:
A centrifugal compressor diffuser blade structure, is along the circumferential direction evenly equipped with a plurality of diffuser vanes on leaf dish, described diffuser vane is that arc leading edge are cone structure.
The leading edge of described diffuser vane comprises top side, pressure side side and suction surface side, and described top side, pressure side side and suction surface side are all cut sth. askew and formed described cone structure.
The 10%-25% of the blade chord length that the pressure side lateral lobe sheet resection length of described pressure side side is diffuser vane, the suction surface lateral lobe sheet resection length of described suction surface side is the twice of the pressure side lateral lobe sheet resection length of pressure side side.The 30%-50% that the blade inlet edge end height of described leading edge is original height.
On described leaf dish, be along the circumferential direction evenly equipped with 22 diffuser vanes, described diffuser vane is wing blade diffuser vane.
Advantage of the present utility model and produce effect and be:
1. the utility model can be applicable in large centrifugal air compressor unit, and it can effectively reduce the vibration amplitude under pipe vibration total amount, particularly blade passing frequency, avoids causing due to pipeline damage the appearance of centrifugal compressor parking accident.
2. the utility model is compared with former overall height diffuser vane, and not only compressor aeroperformance keeps previous level, and has effectively widened the condition range of compressor bank.
Accompanying drawing explanation
Fig. 1 a is structural representation of the present utility model;
Fig. 1 b is A-A sectional view in Fig. 1 a;
Fig. 2 a is schematic three dimensional views of the present utility model;
Fig. 2 b is the A place enlarged diagram in Fig. 2 a;
Fig. 3 is the internal structure schematic diagram of the utility model centrifugal compressor;
Fig. 4 is for being used the outlet conduit result of oscillation figure of overall height diffuser vane;
Fig. 5 is for being used outlet conduit result of oscillation figure of the present utility model.
Wherein: 1 is diffuser vane, 2 is leaf dish, and 3 is leading edge, and 4 is suction surface side, and 5 is pressure side side, and 6 is bolt, and 7 is impeller, and L is blade chord length, and L1 is pressure side lateral lobe sheet resection length, and L2 is suction surface lateral lobe sheet resection length, and H is blade inlet edge end height.
Embodiment
Below in conjunction with drawings and Examples, the utility model is described in further detail.
As shown in Fig. 1 a-2b, the utility model comprises leaf dish 2 and diffuser vane 1, and wherein diffuser vane 1 is wing blade diffuser vane.On leaf dish 2, be along the circumferential direction evenly equipped with 22 diffuser vanes 1, arc leading edge 3 that described diffuser vane 1 is L for chord length are cone structure.
The leading edge 3 of described diffuser vane 1 comprises top side, pressure side side 4 and suction surface side 5, and described top side, pressure side side 4 and suction surface side 5 are all cut sth. askew and formed described cone structure.The pressure side lateral lobe sheet resection length L1 of described pressure side side 4 is the 10%-25% of the blade chord length L of diffuser vane 1, and the suction surface lateral lobe sheet resection length L2 of described suction surface side 5 is the twice of the pressure side lateral lobe sheet resection length L1 of pressure side side 4.The 30%-50% that the blade inlet edge end height H of leading edge 3 is former height.
Embodiment
As shown in Figure 3, diffuser vane 1 is arranged on the downstream of half-opened impeller 7, and impeller blade number is 13, and rotor speed is 22210RPM.Leaf dish 2 is fixed on baffle plate by bolt 6, and wherein the external diameter of half-opened impeller 7 is 240mm, and the diameter at leading edge 3 places of diffuser vane 1 is 270mm, and the former height of diffuser vane 1 is 20mm, and blade chord length L is 91.5mm.Top side, pressure side side 4 and suction surface side 5 in the leading edge 3 of diffuser vane 1 are cut sth. askew respectively, and blade inlet edge end height H is former height 40%, are 8mm; Pressure side lateral lobe sheet resection length L1 is 20% of blade chord length L, and pressure side lateral lobe sheet resection length L1 is 18.3mm; Suction surface lateral lobe sheet resection length L2 is the twice of pressure side lateral lobe sheet resection length L1, and suction surface lateral lobe sheet resection length L2 is 36.6mm.
The present embodiment has carried out testing property and pipe vibration testing experiment, the flange that the point position of pipe vibration is connected with spiral case at outlet conduit, the test result of the test result of the utility model diffuser vane and overall height diffuser vane is carried out to comparative study, and comparing result as shown in Figure 4, Figure 5.Result shows, uses the pipe Vibration momentum of the utility model diffuser vane to have more obviously decline, and particularly the vibration amplitude at blade passing frequency place significantly reduces.Compare with former overall height diffuser vane, use after diffuser vane of the present utility model, not only compressor aeroperformance keeps previous level, and has effectively widened the condition range of compressor bank.
The novel diffuser vane structure of the utility model based on large centrifugal air compressor unit, by CFD calculation and test method validation the effect of the utility model diffuser vane structure, significant and application prospect widely.
Claims (6)
1. a centrifugal compressor diffuser blade structure, is characterized in that: on leaf dish (2), be along the circumferential direction evenly equipped with a plurality of diffuser vanes (1), described diffuser vane (1) is that arc leading edge (3) are cone structure.
2. by centrifugal compressor diffuser blade structure claimed in claim 1, it is characterized in that: the leading edge (3) of described diffuser vane (1) comprises top side, pressure side side (4) and suction surface side (5), described top side, pressure side side (4) and suction surface side (5) are all cut sth. askew and are formed described cone structure.
3. by centrifugal compressor diffuser blade structure claimed in claim 2, it is characterized in that: the 10%-25% of the blade chord length (L) that the pressure side lateral lobe sheet resection length (L1) of described pressure side side (4) is diffuser vane (1), the suction surface lateral lobe sheet resection length (L2) of described suction surface side (5) is the twice of the pressure side lateral lobe sheet resection length (L1) of pressure side side (4).
4. by centrifugal compressor diffuser blade structure claimed in claim 2, it is characterized in that: the blade inlet edge end height (H) of described leading edge (3) is the 30%-50% of original height, and described original height is 20mm.
5. by centrifugal compressor diffuser blade structure claimed in claim 1, it is characterized in that: on described leaf dish (2), be along the circumferential direction evenly equipped with 22 diffuser vanes (1).
6. by the centrifugal compressor diffuser blade structure described in claim 1-5 any one, it is characterized in that: described diffuser vane (1) is wing blade diffuser vane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320602739.0U CN203500120U (en) | 2013-09-27 | 2013-09-27 | Centrifugal compressor diffuser blade structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320602739.0U CN203500120U (en) | 2013-09-27 | 2013-09-27 | Centrifugal compressor diffuser blade structure |
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| Publication Number | Publication Date |
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| CN203500120U true CN203500120U (en) | 2014-03-26 |
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| CN201320602739.0U Expired - Lifetime CN203500120U (en) | 2013-09-27 | 2013-09-27 | Centrifugal compressor diffuser blade structure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105298921A (en) * | 2014-12-17 | 2016-02-03 | 北京航空航天大学 | Inter-stage U-shaped mixing diffuser for two-stage centrifugal gas compressor |
| CN106089808A (en) * | 2016-07-28 | 2016-11-09 | 中南大学 | A kind of blade diffuser with trailing edge structures before swallow-tail form and formative method thereof |
| CN111022376A (en) * | 2019-12-30 | 2020-04-17 | 陕西鼓风机（集团）有限公司 | Combined type blade, compressor blade diffuser |
| CN111556926A (en) * | 2018-01-10 | 2020-08-18 | Abb涡轮系统有限公司 | Filter muffler for an exhaust gas turbocharger of an internal combustion engine |
-
2013
- 2013-09-27 CN CN201320602739.0U patent/CN203500120U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105298921A (en) * | 2014-12-17 | 2016-02-03 | 北京航空航天大学 | Inter-stage U-shaped mixing diffuser for two-stage centrifugal gas compressor |
| CN105298921B (en) * | 2014-12-17 | 2017-07-04 | 北京航空航天大学 | U-shaped mixing diffuser between two-stage centrifugal compressor stage |
| CN106089808A (en) * | 2016-07-28 | 2016-11-09 | 中南大学 | A kind of blade diffuser with trailing edge structures before swallow-tail form and formative method thereof |
| CN106089808B (en) * | 2016-07-28 | 2018-11-16 | 中南大学 | A kind of blade diffuser and its formative method with trailing edge structures before swallow-tail form |
| CN111556926A (en) * | 2018-01-10 | 2020-08-18 | Abb涡轮系统有限公司 | Filter muffler for an exhaust gas turbocharger of an internal combustion engine |
| CN111556926B (en) * | 2018-01-10 | 2022-03-22 | Abb瑞士股份有限公司 | Filter mufflers for exhaust gas turbochargers of internal combustion engines |
| US11549471B2 (en) | 2018-01-10 | 2023-01-10 | Abb Schweiz Ag | Filter muffler for an exhaust gas turbocharger of an internal combustion engine |
| CN111022376A (en) * | 2019-12-30 | 2020-04-17 | 陕西鼓风机（集团）有限公司 | Combined type blade, compressor blade diffuser |
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Granted publication date: 20140326 |
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| CX01 | Expiry of patent term |