CN102536901A - Adjusting device for elastic guide vanes at inlet of air compressor of automobile turbocharger - Google Patents
Adjusting device for elastic guide vanes at inlet of air compressor of automobile turbocharger Download PDFInfo
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- CN102536901A CN102536901A CN2012100094372A CN201210009437A CN102536901A CN 102536901 A CN102536901 A CN 102536901A CN 2012100094372 A CN2012100094372 A CN 2012100094372A CN 201210009437 A CN201210009437 A CN 201210009437A CN 102536901 A CN102536901 A CN 102536901A
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- stator
- elasticity
- air inlet
- inlet sleeve
- central shaft
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Abstract
The invention belongs to the field of automobile parts, and particularly relates to an adjustable guide vane structure at an inlet of an air compressor and provides an adjusting device for elastic guide vanes at an inlet of an air compressor of an automobile turbocharger. The adjusting device comprises an air inlet sleeve (1), a center shaft (6), guide vane supports (2), elastic guide vanes (4) and an adjusting ring (5). The air inlet sleeve (1) is connected with the center shaft (6) through guide vane supports (2) distributed at the same interval, the elastic guide vanes (4) are fixed on the center shaft (6) and the guide vane supports (2), and front edges (13) and roots (14) of the elastic guide vanes (4) are then fixed. The adjusting ring (5) controls the tail edges of the elastic guide vanes (4) to swing around the center shaft (6), and angle variation of an airflow outlet is increased from the roots to the tips of vanes gradually. The adjusting device is capable of reducing surge flow and simultaneously increasing efficiency of the air compressor.
Description
Technical field
The invention belongs to the auto parts and components field, be specifically related to a kind of compressor inlet adjustable vane structure.
Background technique
Surge is an incidental fault in the gas compressor operation process, and harmfulness is very big.Adopt the compressor inlet adjustable vane can effectively improve gas compressor slow-speed of revolution performance; Widened gas compressor stable operation border; To preventing that engine surge and raising engine performance from playing crucial effect, particularly can make the gas compressor performance that is operated in off-design point get a promotion.The compressor inlet adjustable vane generally all is after a certain regulating working conditions at present; How much angles, top immobilize from the root to the leaf; Though reduced the flow of surge so to a certain extent, but do not satisfy the characteristic that the gas compressor angle of attack distributes, reduced the efficient of gas compressor.Desirable entry guide vane is the efficient that can improve gas compressor when can enlarge gas compressor work border again, is not influence compressor efficiency or very little to its effectiveness affects at least.
Summary of the invention
The objective of the invention is: a kind of compressor inlet adjustable vane is provided; It has overcome existing stator airintake direction equal angles after regulating exit angle and has changed; The drawback that causes compressor efficiency to descend makes compressor efficiency and reduces the surge flow to be guaranteed simultaneously.
Technological scheme of the present invention is: a kind of vehicle turbocharger compressor inlet elasticity stator controlling device, and it comprises: total body support frame, elasticity stator and regulating ring;
Total body support frame adopts casting, and it comprises: air inlet sleeve, central shaft and stator support; Central shaft is positioned at the axial centre position of air inlet sleeve, and the stator support is along circumferentially linking together for even distribution and with air inlet sleeve and central shaft; The air inlet lower cartridge leaves fluting, and turning goes out a location shoulder on the air inlet sleeve above the fluting, and the top of central shaft is provided with flow deflecting cone;
The elasticity stator is provided with the rectangle chimb of one along its trailing edge direction, and folding along 1/2nd places that the rectangle chimb is high, folding direction is opposite with elasticity stator sense of rotation, and the rectangle convex edge after folding is divided into the stator controlling rod; The leading edge of elasticity stator is fixed on the stator support; The blade root of elasticity stator is fixed on the central shaft; The stator controlling rod passes fluting;
Regulating ring is enclosed within the outside of the fluting of air inlet sleeve, and its inboard has axial groove, and the stator controlling rod stretches into axial groove, and its outer circumference face is provided with a protruding structure, is used to drive regulating ring and moves into the air-casing tube and axially rotate.
Working principle: through rotating adjustment ring; And then drive elasticity stator trailing edge is swung around central shaft; Because the leading edge and the blade root of elasticity stator are separately fixed on central shaft and the stator support, the angle change amount of flow outlet is according to being changed by the blade root rule that direction increases gradually to the leaf top.
The invention has the beneficial effects as follows: can accomplish that when regulating the stator angle leaf top and the non-isogonism of blade root change; Velocity attitude change amount increased gradually after air communication was crossed guide vane; Can not only regulate the range of flow of gas compressor like this; Can also satisfy the characteristic that the gas compressor angle of attack distributes, the efficient of gas compressor is guaranteed.
Description of drawings
Fig. 1 is the main generalized section of looking of the present invention;
Fig. 2 is a regulating ring schematic representation of the present invention;
Fig. 3 is a worm's eye view of the present invention;
Fig. 4 is an elasticity stator schematic representation of the present invention.
Wherein, 1-air inlet sleeve, 2-stator support, the 3-flow deflecting cone, 4-elasticity stator, the 5-regulating ring, the 6-central shaft, 7-is protruding, the 8-axial groove, the 9-square groove, 10-stator mounting groove, 11-locatees shoulder, 12-stator controlling rod, the leading edge of 13-stator, the blade root of 14-stator.
Embodiment
A kind of vehicle turbocharger compressor inlet elasticity stator controlling device, it comprises: total body support frame, elasticity stator 4 and regulating ring 5;
Total body support frame adopts casting, and it comprises: air inlet sleeve 1, central shaft 6 and stator support 2; Central shaft 6 is positioned at the axial centre position of air inlet sleeve 1, and stator support 2 is along circumferentially linking together for even distribution and with air inlet sleeve 1 and central shaft 6; Fluting 9 is left in air inlet sleeve 1 bottom, and turning goes out a location shoulder 11 on the air inlet sleeve 1 above the fluting 9; The top of central shaft 6 is provided with flow deflecting cone 3;
Claims (5)
1. a vehicle turbocharger compressor inlet elasticity stator controlling device is characterized in that it comprises: total body support frame, elasticity stator (4) and regulating ring (5);
Said total body support frame adopts casting, and it comprises: air inlet sleeve (1), central shaft (6) and stator support (2); Central shaft (6) is positioned at the axial centre position of air inlet sleeve (1), and said stator support (2) is along circumferentially linking together for even distribution and with said air inlet sleeve (1) and said central shaft (6); Fluting (9) is left in said air inlet sleeve (1) bottom, goes up turning at the air inlet sleeve (1) of the top of said fluting (9) and goes out a location shoulder (11); The top of said central shaft (6) is provided with flow deflecting cone (3);
Said elasticity stator (4) is provided with the rectangle chimb of one along its trailing edge direction, and folding along 1/2nd places that said rectangle chimb is high, folding direction is opposite with said elasticity stator (4) sense of rotation, and the rectangle convex edge after folding is divided into stator controlling rod (12); The leading edge (13) of said elasticity stator (4) is fixed on the said stator support (2); The blade root (14) of said elasticity stator (4) is fixed on the said central shaft (6); Said stator controlling rod (12) passes said fluting (9);
Said regulating ring (5) is sleeved on the outside of the fluting (9) of said air inlet sleeve (1), and its inboard has axial groove (8), and said stator controlling rod (12) stretches into said axial groove (8), and its outer circumference face is provided with a protruding structure (7).
2. a kind of vehicle turbocharger compressor inlet elasticity stator controlling device as claimed in claim 1; It is characterized in that; Said air inlet sleeve (1) adopts Spielpassung with the surface of contact of said regulating ring (5); Add lubricating grease therebetween, between the axial groove (8) of said stator controlling rod (12) and said regulating ring (5), also add lubricating grease.
3. according to claim 1 or claim 2 a kind of vehicle turbocharger compressor inlet elasticity stator controlling device; It is characterized in that; Have stator mounting groove (10) on said central shaft (6) and the said stator support (2), the outer surface of the internal surface of said stator mounting groove (10) and said elasticity stator (4) is an interference fit.
4. according to claim 1 or claim 2 a kind of vehicle turbocharger compressor inlet elasticity stator controlling device, its said air inlet sleeve (1) bottom leave fluting (9) for along circumferential opening slot.
5. a kind of vehicle turbocharger compressor inlet elasticity stator controlling device as claimed in claim 3, its said air inlet sleeve (1) bottom leave fluting (9) and are the circumferential opening slot in edge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100094372A CN102536901A (en) | 2012-01-12 | 2012-01-12 | Adjusting device for elastic guide vanes at inlet of air compressor of automobile turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100094372A CN102536901A (en) | 2012-01-12 | 2012-01-12 | Adjusting device for elastic guide vanes at inlet of air compressor of automobile turbocharger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102536901A true CN102536901A (en) | 2012-07-04 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012100094372A Pending CN102536901A (en) | 2012-01-12 | 2012-01-12 | Adjusting device for elastic guide vanes at inlet of air compressor of automobile turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102536901A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102840159A (en) * | 2012-09-26 | 2012-12-26 | 北京理工大学 | Negative pressure adjusting device for inlet of compressor with variable diameter |
| CN103352864A (en) * | 2013-08-05 | 2013-10-16 | 上虞专用风机有限公司 | Civil fan pressurization mechanism and fan system |
| CN108626141A (en) * | 2017-03-24 | 2018-10-09 | 现代自动车株式会社 | Compressor |
| CN109098857A (en) * | 2018-08-24 | 2018-12-28 | 西安航天动力研究所 | A kind of rocket engine turbine inlet pipe structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB606560A (en) * | 1945-03-20 | 1948-08-17 | Power Jets Res & Dev Ltd | Improvements relating to axial flow compressors |
| CN2357132Y (en) * | 1998-11-06 | 2000-01-05 | 淄博矿山节能技术研究所 | Radial shaft mixed-flow ventilator for mine |
| CN101634305A (en) * | 2009-08-13 | 2010-01-27 | 寿光市康跃增压器有限公司 | Rotary diffusing wall type adjustable compressor device |
| CN101975190A (en) * | 2010-09-30 | 2011-02-16 | 北京理工大学 | Differential guide vane section and guide vane adjusting device for vane compressor |
-
2012
- 2012-01-12 CN CN2012100094372A patent/CN102536901A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB606560A (en) * | 1945-03-20 | 1948-08-17 | Power Jets Res & Dev Ltd | Improvements relating to axial flow compressors |
| CN2357132Y (en) * | 1998-11-06 | 2000-01-05 | 淄博矿山节能技术研究所 | Radial shaft mixed-flow ventilator for mine |
| CN101634305A (en) * | 2009-08-13 | 2010-01-27 | 寿光市康跃增压器有限公司 | Rotary diffusing wall type adjustable compressor device |
| CN101975190A (en) * | 2010-09-30 | 2011-02-16 | 北京理工大学 | Differential guide vane section and guide vane adjusting device for vane compressor |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102840159A (en) * | 2012-09-26 | 2012-12-26 | 北京理工大学 | Negative pressure adjusting device for inlet of compressor with variable diameter |
| CN102840159B (en) * | 2012-09-26 | 2015-04-29 | 北京理工大学 | Negative pressure adjusting device for inlet of compressor with variable diameter |
| CN103352864A (en) * | 2013-08-05 | 2013-10-16 | 上虞专用风机有限公司 | Civil fan pressurization mechanism and fan system |
| CN108626141A (en) * | 2017-03-24 | 2018-10-09 | 现代自动车株式会社 | Compressor |
| CN109098857A (en) * | 2018-08-24 | 2018-12-28 | 西安航天动力研究所 | A kind of rocket engine turbine inlet pipe structure |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20120704 |