CN101255873A - Blade tip alula of gas-pressing automotive leaf - Google Patents
Blade tip alula of gas-pressing automotive leaf Download PDFInfo
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- CN101255873A CN101255873A CNA2008100105154A CN200810010515A CN101255873A CN 101255873 A CN101255873 A CN 101255873A CN A2008100105154 A CNA2008100105154 A CN A2008100105154A CN 200810010515 A CN200810010515 A CN 200810010515A CN 101255873 A CN101255873 A CN 101255873A
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- suction surface
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Abstract
The present invention provides a tip vane of guided vane of compressor related to field of impeller machine, which comprises a front edge wing, a pressure surface wing, a pressure surface wing, a suction surface wing and a tail edge wing, the pressure surface wing and the suction surface wing are little vanes expended between front edge point A and tail edge point B of leaf along circumference, front edge point D and C of pressure surface wing and suction surface wing are lied on front edge point A or between front edge point A and most thickness part of guided vane; tail edge point F and E of pressure surface wing and suction surface wing are lied on tail edge point B or between tail edge point B and the most thickness part of guided vane; the front edge wing and tail edge wing are connected smoothly with the pressure surface wing and suction surface wing, and the front edge wing and tail edge wing are extended parts of pressure surface wing and suction surface wing at front edge and tail edge. The present invention reduces effect of flow field in channel by tip leakage, tip leakage vortex and scraping gyres, improves cascade flow field, and enhances mechanical efficiency of impeller at the same time.
Description
Technical field
The present invention relates to the turbomachine field, be specifically related to be applied to the design of the tip vane of various gas compressor moving blades.
Background technique
In gas compressor, it is very little that the physical dimension of the tip clearance between movable vane leaf top bit and the casing is compared with whole runner, but it exerts an influence to the mobile of nearly 20% zone in the blade passage, especially in the smaller gas compressor of size, blade tip clearance has following several adverse effect: the 1) existence of tip clearance, can cause the minimizing of working fluid actual flow, cause near the working fluid acting of blade tip minimizing, passage obstruction and cascade loss to increase; 2) tip leakage can form the tip leakage whirlpool at the movable vane suction surface, and tip leakage whirlpool and passage whirlpool interact, and makes the complexity more that flows in the blade grid passage, and flow losses increase, and have changed the flow outlet angle simultaneously; 3), form and wipe the stream whirlpool because rotor with respect to the motion of casing wall, causes casing wall boundary layer fricting movement.By three kinds of influences that tip clearance is brought, all changed the Flow Field Distribution in the compressor blade row to some extent, increase the air current flow loss in the gas compressor.The flow loss and the secondary flow losses such as tip leakage whirlpool and blade tip wiping stream whirlpool that are caused by tip clearance generally all occupy quite great proportion in the gas compressor total losses, their increase all can cause the increase of gas compressor total losses.If use integral shroud at the movable vane top, then integral shroud needs and outer casing adopt multi-sealed system, and integral shroud is under high speed rotating, and centrifugal force is bigger, can cause the increase of the suffered stress of movable vane, thereby reduces the reliability of gas compressor work to a certain extent.
Summary of the invention
The purpose of this invention is to provide a kind of design that is applied to the tip vane of various gas compressor moving blades, this design can reduce tip leakage, reduce the tip leakage whirlpool, wipe the influence of stream vortex pair runner flow field, improve cascade flow field simultaneously, improve the efficient of gas compressor, widen the stable operation range of gas compressor.
In order to achieve the above object, technological scheme of the present invention is as follows:
Blade tip alula of gas-pressing automotive leaf mainly is made up of the leading edge wing 4, the pressure side wing 3, the suction surface wing 5 and the trailing edge wing 1 or the trailing edge wing 6, tip vane 7 is mainly used in gas compressor moving blade 8, its mounting point is the movable vane top, Placement can adopt and movable vane one processing generation, also can process tip vane separately, be connected with movable vane by modes such as welding then; Be connected transition between tip vane 7 and the gas compressor moving blade 8, can adopt chamfering transition, round-corner transition or adopt the free form surface smooth transition; The pressure side wing 3 and the suction surface wing 5 all can use separately, also can be used in combination with the other parts winglet, and when being used in combination, each winglet can generate in one processing, also can process separately, couples together by modes such as welding then; The suction surface wing 5 and the pressure side wing 3 are on the basis of gas compressor moving blade blade profile profile, the fin that along the circumferential direction expands between blade profile leading edge point A and trailing edge point B; The leading edge point C of the suction surface wing 5 and the pressure side wing 3 and leading edge point D are between gas compressor moving blade blade profile leading edge point A or leading edge point A and blade profile maximum ga(u)ge, the trailing edge point E of the suction surface wing 5 and the pressure side wing 3 and trailing edge point F are between trailing edge point B or blade profile maximum ga(u)ge and trailing edge point B, and the leading edge point of the suction surface wing 5 or the pressure side wing 3 and the optimum position of trailing edge point need to determine with test as calculated according to the actual requirements; The suction surface wing 5 can be identical along its leading edge to the trailing edge width with the pressure side wing 3, also can be different, and shape can be a regular shape, also can be the irregularly shaped of free form surface structure; The leading edge wing 4 and the trailing edge wing and the suction surface wing 5 and 3 smooth connections of the pressure side wing, the leading edge wing 4 and the trailing edge wing 1 or the trailing edge wing 6 are the extensions at leading edge and trailing edge place of the suction surface wing 5 and the pressure side wing 3, be generally the smooth structure that adopts free form surface, the trailing edge wing also can adopt the dovetail structure.The tip vane top has the curvature identical with outer casing, keeps very little even distance to guarantee tip vane when the work and between the outer casing, and minimizing pressure side air-flow leaks to suction surface.The tip vane top and outside gap control between the casing can adopt initiatively gap control or passive gap control according to the design needs, the inwall of casing is coated with last layer and easily grinds coating outside, the leakage loss outside interpolation high-abrasive material in the top of tip vane is controlled between casing and the tip vane top.
The invention has the beneficial effects as follows: adopt the design of tip vane on various gas compressor moving blades top, has the tip leakage of reducing, the effect in control tip leakage whirlpool and wiping stream whirlpool, can improve simultaneously fluid by blade root to the formed secondary of blade tip crossfire flow field, improve the efficient of gas compressor, widen the stable operation range of gas compressor, and the present invention compares integral shroud, have simple in structure, in light weight, reliability advantages of higher.
Description of drawings
Fig. 1 is gas compressor moving blade of the present invention and the tip vane top view with the leading edge wing, smooth structure trailing edge wing.
Fig. 2 is gas compressor moving blade of the present invention and the tip vane top view with the leading edge wing, dovetail structure trailing edge wing.
Fig. 3 is the 3-D view of gas compressor moving blade of the present invention and tip vane.
Fig. 4 be gas compressor moving blade of the present invention and tip vane longshore current to sectional view.
Fig. 5 is a blade tip flow field structure schematic representation of not being with tip vane.
Fig. 6 is the blade tip flow field structure schematic representation of band tip vane of the present invention.
Among the figure: 1, the smooth structure trailing edge wing, 2, the blade profile profile line, 3, the pressure side wing, 4, the leading edge wing, 5, the suction surface wing, 6, the dovetail structure trailing edge wing, 7, tip vane, 8, gas compressor moving blade.
Embodiment
Below in conjunction with accompanying drawing the present invention is done description in further detail:
As shown in Figures 1 to 4, blade tip alula of gas-pressing automotive leaf of the present invention is mainly by the leading edge wing 4, the pressure side wing 3, the suction surface wing 5 and the trailing edge wing are formed, the suction surface wing 5 and the pressure side wing 3 are on the basis of gas compressor moving blade blade profile profile, the little fin that between blade profile leading edge point A and trailing edge point B, along the circumferential direction expands, the leading edge point C of the suction surface wing 5 and the pressure side wing 3 and leading edge point D are between gas compressor moving blade blade profile leading edge point A or leading edge point A and blade profile maximum ga(u)ge, and the trailing edge point E of the suction surface wing 5 and the pressure side wing 3 and trailing edge point F are between gas compressor moving blade blade profile trailing edge point B or trailing edge point B and blade profile maximum ga(u)ge; The leading edge wing 4 and the trailing edge wing all with the suction surface wing 5 and 3 smooth connections of the pressure side wing, the leading edge wing 4 and the trailing edge wing all are the extensions at leading edge place and trailing edge place of the suction surface wing 5 and the pressure side wing 3.
As shown in Figure 5, in not having the normal blade tip flow field of tip vane, pressure side side high-pressure liquid flows to suction surface side low pressure area, casing wall place easily forms and wipes the stream whirlpool outside the pressure side side, will be in the pointed one-tenth tip leakage of suction surface lateral lobe whirlpool in the suction surface side owing to leaking the high-speed jet fluid that forms by tip clearance, might interact with the end wall boundary layer, form large size and separate.
As shown in Figure 6, in having used the blade tip flow field of tip vane, the pressure side side is because the effect of passage whirlpool, the secondary flow that existence is flowed to blade tip by the movable vane middle part, this fluid is when blade tip runs into tip vane, air-flow is forced to turn to, and is opposite with the leak fluid direction of pressure side side direction suction surface side flow, and both interact, weakened tip leakage, simultaneously, owing to there is tip vane, runner increases in the tip clearance, frictional resistance increases, the leak fluid flow velocity descends a lot, and leakage flow thereby minimizing are a lot, and this has also controlled the leakage vortex influence degree of suction surface side to a certain extent.
Claims (5)
1, blade tip alula of gas-pressing automotive leaf, it is characterized in that, this tip vane is mainly by the leading edge wing (4), the pressure side wing (3), the suction surface wing (5) and the trailing edge wing are formed, the suction surface wing (5) and the pressure side wing (3) are on the basis of gas compressor moving blade blade profile profile, the little fin that between blade profile leading edge point A and trailing edge point B, along the circumferential direction expands, the leading edge point C of the suction surface wing (5) and the pressure side wing (3) and leading edge point D are between gas compressor moving blade blade profile leading edge point A or leading edge point A and blade profile maximum ga(u)ge, and the trailing edge point E of the suction surface wing (5) and the pressure side wing (3) and trailing edge point F are between gas compressor moving blade blade profile trailing edge point B or trailing edge point B and blade profile maximum ga(u)ge; The leading edge wing (4) and the trailing edge wing all with the suction surface wing (5) and smooth connection of the pressure side wing (3), the leading edge wing (4) and the trailing edge wing all are the extensions at leading edge place and trailing edge place of the suction surface wing (5) and the pressure side wing (3).
2, blade tip alula of gas-pressing automotive leaf as claimed in claim 1 is characterized in that, the described trailing edge wing is for adopting the smooth structure trailing edge wing (1) or the dovetail structure trailing edge wing (6) of free form surface.
3, blade tip alula of gas-pressing automotive leaf as claimed in claim 1 is characterized in that, the described suction surface wing (5) and the pressure side wing (3) width along its leading edge to trailing edge is identical or different, and it is shaped as the irregularly shaped of regular shape or free form surface structure.
4, blade tip alula of gas-pressing automotive leaf as claimed in claim 1 is characterized in that, the Placement of described tip vane and gas compressor moving blade adopts chamfering transition, round-corner transition or adopts the free form surface smooth transition.
5, the described blade tip alula of gas-pressing automotive leaf of claim 1 is characterized in that, the described suction surface wing (5) and the pressure side wing (3) use separately or be used in combination with other winglet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008100105154A CN101255873B (en) | 2008-02-28 | 2008-02-28 | Blade tip alula of gas-pressing automotive leaf |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008100105154A CN101255873B (en) | 2008-02-28 | 2008-02-28 | Blade tip alula of gas-pressing automotive leaf |
Publications (2)
| Publication Number | Publication Date |
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| CN101255873A true CN101255873A (en) | 2008-09-03 |
| CN101255873B CN101255873B (en) | 2010-06-09 |
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| CN2008100105154A Active CN101255873B (en) | 2008-02-28 | 2008-02-28 | Blade tip alula of gas-pressing automotive leaf |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9593584B2 (en) | 2012-10-26 | 2017-03-14 | Rolls-Royce Plc | Turbine rotor blade of a gas turbine |
| CN111219362A (en) * | 2018-11-27 | 2020-06-02 | 中国航发商用航空发动机有限责任公司 | Axial compressor blade, axial compressor and gas turbine |
| CN112283161A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Axial compressor and compressor rotor blade thereof |
| CN112283160A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor rotor blade and design method thereof |
| CN112283162A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor rotor blade and design method thereof |
| CN113202789A (en) * | 2021-06-09 | 2021-08-03 | 清华大学 | Impeller for centrifugal compressor and centrifugal compressor |
| CN115977999A (en) * | 2023-01-12 | 2023-04-18 | 山东科技大学 | Subsonic compressor, rotor blade and flow stability expansion control method |
| CN116066410A (en) * | 2023-02-02 | 2023-05-05 | 广东肇庆德通有限公司 | Axial fan for ventilation |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2669686B1 (en) * | 1990-11-28 | 1994-09-02 | Snecma | BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE. |
| MXPA02006864A (en) * | 2000-01-14 | 2002-10-23 | Alliedsignal Turbo S A | Turbocharger with sliding blades having combined dynamic surfaces and heat screen and uncoupled axial actuating device. |
| CN1847664A (en) * | 2006-04-07 | 2006-10-18 | 刘昌喆 | Radial cascade air compressor |
| CN201159202Y (en) * | 2008-02-28 | 2008-12-03 | 大连海事大学 | Moving blade tip winglet of compressor |
-
2008
- 2008-02-28 CN CN2008100105154A patent/CN101255873B/en active Active
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9593584B2 (en) | 2012-10-26 | 2017-03-14 | Rolls-Royce Plc | Turbine rotor blade of a gas turbine |
| US10641107B2 (en) | 2012-10-26 | 2020-05-05 | Rolls-Royce Plc | Turbine blade with tip overhang along suction side |
| CN111219362A (en) * | 2018-11-27 | 2020-06-02 | 中国航发商用航空发动机有限责任公司 | Axial compressor blade, axial compressor and gas turbine |
| CN112283161A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Axial compressor and compressor rotor blade thereof |
| CN112283160A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor rotor blade and design method thereof |
| CN112283162A (en) * | 2020-12-24 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor rotor blade and design method thereof |
| CN112283161B (en) * | 2020-12-24 | 2021-03-16 | 中国航发上海商用航空发动机制造有限责任公司 | Axial compressor and compressor rotor blade thereof |
| CN112283162B (en) * | 2020-12-24 | 2021-03-26 | 中国航发上海商用航空发动机制造有限责任公司 | Compressor rotor blade and design method thereof |
| CN113202789A (en) * | 2021-06-09 | 2021-08-03 | 清华大学 | Impeller for centrifugal compressor and centrifugal compressor |
| CN115977999A (en) * | 2023-01-12 | 2023-04-18 | 山东科技大学 | Subsonic compressor, rotor blade and flow stability expansion control method |
| CN116066410A (en) * | 2023-02-02 | 2023-05-05 | 广东肇庆德通有限公司 | Axial fan for ventilation |
| CN116066410B (en) * | 2023-02-02 | 2023-08-04 | 广东肇庆德通有限公司 | Axial fan for ventilation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101255873B (en) | 2010-06-09 |
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