CN102889237B - Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor - Google Patents

Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor Download PDF

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Publication number
CN102889237B
CN102889237B CN201210193389.7A CN201210193389A CN102889237B CN 102889237 B CN102889237 B CN 102889237B CN 201210193389 A CN201210193389 A CN 201210193389A CN 102889237 B CN102889237 B CN 102889237B
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wedge angle
place
leading edge
suction surface
small
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CN102889237A (en
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郭宝亭
陶海亮
陈巍
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Institute of Engineering Thermophysics of CAS
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Institute of Engineering Thermophysics of CAS
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Abstract

The invention discloses a blade wheel with large blades and small blades applying front edges with sharp corners and an air compressor. The blade wheel comprises the large blades and the small blades, wherein the front edges of the large blades and the front edges of the small blades have sharp corner structures; the blade wheel is of an axial flow type or a radial flow type; the blades comprise the large blades and the small blades; and the front edges of the large blades are the sharp corners, or the small blades can be also provided with the sharp corners, or the front edges of the large blades and the front edges of the small edges are the sharp corners. The front edges of the blades are the sharp corners, the sizes and the strength of a horseshoe vortex and a channel vortex can be reduced, secondary flow loss is reduced, total pressure loss is reduced, and the flow efficiency is improved; and moreover, stress concentration at the front edges of the blades is reduced.

Description

A kind of big and small blade impeller of application band wedge angle leading edge and gas compressor
Technical field
The turbomachine that the invention belongs to field of fluid machinery is pneumatic, structural design, relates to a kind of blade impellers mechanical device, particularly relates to a kind of big and small blade impeller and gas compressor thereof of application band wedge angle leading edge.
Background technique
Miniature gas turbine is low profile thermal force engine, its single-machine capacity scope is 25 ~ 500kW, its basic principle is identical with conventional gas turbines, and basic technical features adopts radial flow impeller machinery (centrifugal-flow compressor and inward flow turbine) and extraction cycle.Modern miniature gas turbine, as the major impetus machine of distributing-supplying-energy system, has many advantages compared with other power equipment.Modern advanced micro fuel engine have structure simple, can use or a series of advanced technology feature such as multiple stage is integrated, be applicable to pluralities of fuel, the high and low discharge of the thermal efficiency, low noise, low vibration, low maintenance rate, automaticity are high by separate unit, be to provide clean, safe, reliably and the best mode of high quality energy supply.
Guaranteeing that miniature gas turbine is stablized on the basis of effectively work, the efficiency improving gas turbine becomes the emphasis of gas turbine research concern.In several large parts of gas turbine, the efficiency of gas compressor is relatively low, is also the key factor affecting overall efficiency.Usually there is clearance leakage loss in compressor part, secondary flow loss etc., because gas compressor internal flow is relatively complicated, the efficiency how improving gas compressor is a great problem that artificer faces.At present, the working speed of miniature gas turbine is relatively high, is subject to the strength problem that centrifugal force causes while making compressor blade subject Pneumatic immpacting, root of blade and this problem of wheel disc jointing place especially outstanding.
The secondary flow loss existed in gas compressor is caused by horseshoe vortex, Passage Vortex etc. usually.Due to main flow field and near wall boundary layer place, there is certain pressure gradient radially, radially flow towards wall at the effect next part air-flow of this pressure gradient, form horseshoe vortex, cause secondary flow loss, horseshoe vortex produces in the jointing place of blade and wall usually.Because in gas compressor, the pressure of pressure side is greater than the pressure of suction surface, cause pressure gradient circumferentially.Air-flow produces certain centrifugal force when passage moves, when air-flow velocity is larger, this centrifugal force can balance pressure gradient, and the impact near wall place due to boundary layer, airspeed is relatively low, and the centrifugal force of generation cannot balance pressure gradient, thus causes the lateral flow circumferentially of air-flow, namely define Passage Vortex, cause secondary flow loss.
As fully visible, reduce secondary flow loss, improve circulation efficiency, improving blade strength is the problem that the pneumatic and structural design of gas compressor is mainly considered.The present invention proposes an impeller to blade inlet edge and wall joint appropriate design, edge arranges a wedge angle in front of the blade.The existence of this wedge angle improves the airspeed at blade and wall jointing place, and the raising of the airspeed of blade and wall jointing place inhibits the formation along blade surface pressure gradient, and namely this pressure gradient is cause the main cause of horseshoe vortex and Passage Vortex.Thus, this invention can reduce intensity and the size of the horseshoe vortex of blade profile leading edge, can reduce the intensity of Passage Vortex simultaneously, improves flow efficiency, reduces secondary flow loss, thus the pitot loss caused due to Passage Vortex can be reduced accordingly.
Summary of the invention
Object of the present invention is lack for domestic miniature gas turbine radial-flow type Machine Design experience, for improving impeller flow efficiency, reducing aerodynamic loss, increasing blade strength, effectively increasing the service life and provide a kind of Impeller Design scheme.
The present invention devises a kind of impeller with wedge angle leading edge, arranges a kind of horn structure in described compressor blade leading edge.Due to the existence of this horn structure, improve the airspeed of blade and wall jointing place on the one hand, reduce intensity and the size of horseshoe vortex, the intensity of Passage Vortex can be reduced simultaneously, thus the pitot loss caused due to Passage Vortex can be reduced accordingly; The jointing place of blade inlet edge and wall is also the weakness zone of Intensity Design on the other hand, and the existence of this structure strengthens the intensity of blade inlet edge and wall jointing place, and stress concentration phenomenon is improved.
In order to achieve the above object, the present invention adopts following technical solution:
A big and small blade impeller for application band wedge angle leading edge, comprises multiple large and small blade and wheel disc, and described big leaf's slice and the spaced layout of small leaf, is characterized in that,
Extend a wedge angle in described big leaf's slice and/or the leading edge of small leaf and the jointing place of wheel disc, described wedge angle comprises pressure side and suction surface, the pressure side of described wedge angle and suction surface all arcuately:
The pressure side of described wedge angle originates in described wedge angle and the jointing place of wheel disc, and to extend a segment distance crossing to the pressure side place of blade, and the suction surface of described wedge angle originates in described wedge angle and the jointing place of wheel disc, and to extend a segment distance crossing to the suction surface place of blade;
The length of described wedge angle is greater than its height, its be highly the leaf of blade high 5% ~ 10%.
Preferably, when only having the leading edge of small leaf to arrange wedge angle, the leading edge of described big leaf's slice can be common rounding.Or when only having the leading edge of big leaf's slice to arrange wedge angle, the leading edge of described small leaf can be common rounding.
Preferably, the pressure side of described wedge angle and the projection plane of suction surface in wheel card are all in incomplete ellipse, and namely pressure side and the projection plane of suction surface in wheel card are all oval parts.
Further, the separating surface between the pressure side of described wedge angle and suction surface is arranged on blade generation stagnation place, and namely described separating surface crosses the stagnation line of blade.
Further, the major axis of the ellipse at projection plane its place of major axis specific pressure face in wheel card of the ellipse at projection plane its place of suction surface in wheel card of described wedge angle is long, and the minor axis of the ellipse at projection plane its place of minor axis specific pressure face in wheel card of the ellipse at projection plane its place of suction surface in wheel card of described wedge angle is long.
Further, the pressure side of described wedge angle is connected with the leading edge place smooth transition of suction surface at wedge angle.
Further, the pressure side of described wedge angle and suction surface, separating surface place smooth transition between connects.
Further, the ellipse at the pressure side of described wedge angle its place, projection plane in wheel card and the ellipse at projection plane its place of suction surface in wheel card, two oval elliptical center points do not overlap.
Preferably, the big and small blade impeller of described application band wedge angle leading edge is axial flow or radial flow impeller.
The present invention is claimed a kind of gas compressor also, and it comprises the big and small blade impeller of above-mentioned application band wedge angle leading edge.
Advantage of the present invention:
(1) blade inlet edge pointed design structure of the present invention is simple, and design is convenient, is applicable to engineer applied.
(2) the present invention suppresses Secondary Flow Be very effective, improves obviously root stress situation.By the blade of application band wedge angle leading edge in impeller, reduce horseshoe vortex, the size of Passage Vortex and intensity on the one hand, decrease Secondary Flow, improve the flow efficiency of impeller; The stress reducing root of blade is on the other hand concentrated, and improves the intensity of root of blade, improves the useful working life of blade.
Accompanying drawing explanation
Fig. 1 centrifugal compressor meridional section schematic diagram;
The CONSTRUCTED SPECIFICATION figure of Fig. 2 centrifugal compressor isometric view and band wedge angle leading edge blade;
Fig. 3 sharp corner details enlarged view.
Embodiment
For making object of the present invention, technological scheme and advantage clearly understand, to develop simultaneously embodiment referring to accompanying drawing, the present invention is described in more detail.
The invention provides a kind of big and small blade impeller and gas compressor of application band wedge angle leading edge, the meridional section schematic diagram of described centrifugal compressor rotor, as shown in Figure 1.Described gas compressor forms by primarily of blade 1, impeller 2.Described gas compressor operationally forms certain blade tip clearance with casing 3.Described compressor blade 1 is divided into big leaf's slice 101 and small leaf 102, and big leaf's slice 101 and the spaced layout of small leaf 102, extend a wedge angle 7 at the described blade inlet edge of small leaf 102 and the jointing place of wheel disc.Described small leaf 102 is divided into pressure side 11 and suction surface 12 by stagnation line 42.Described wedge angle 7 is divided into wedge angle pressure side 72 and wedge angle suction surface 74 by separating surface 76.
In actual applications, wedge angle 7 can be adopted longitudinally to extend in the leading edge of small leaf 102, extend along short transverse in the leading edge of small leaf 102 equally.Separating surface 76 designs usually at blade generation stagnation place, i.e. the usual stagnation line 42 crossing small leaf of separating surface.The pressure side 72 of wedge angle 7 is arc, and outside place extension one segment distance originating in wedge angle 7 intersects to pressure side 11 place of small leaf 102.The suction surface 74 of wedge angle 7 is also arc, and outside place extension one segment distance originating in wedge angle 7 intersects to suction surface 12 place of small leaf 10.The length of wedge angle 7 is greater than its height, and the height of wedge angle 7 can in high 5% ~ 10% value of leaf.
Shown in Fig. 3, the pressure side 72 of wedge angle 7 and the projection of suction surface 74 in wheel card are in fact all incomplete ellipses, are all oval parts.The elliptical center point (Css) that suction surface 74 projects, minor axis length (Sss), long axis length (Lss).The elliptical center point (Cps) that pressure side 72 projects, minor axis length (Sps), long axis length (Lps).The suction surface 74 of wedge angle and the main axis of pressure side 72 are on separating surface 76.The major axis in the major axis specific pressure face 72 of suction surface 74 will be grown (Lss > Lps).The minor axis long (Sss > Sps) on the projection plane in the minor axis specific pressure face 72 on the projection plane of suction surface 74.Oval pressure side 72 and suction surface 74 are at the outside place of wedge angle 7, i.e. leading edge place, and smooth transition connects.In actual mechanical process, do mid point with Css and Cps respectively and make elliptic arc, adopt identical curvature in two oval jointing places, to ensure that theirs is tangent.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within the scope of the present invention.

Claims (7)

1. apply a big and small blade impeller for band wedge angle leading edge, comprise multiple large and small blade and wheel disc, described big leaf's slice and the spaced layout of small leaf, is characterized in that,
Extend a wedge angle in described big leaf's slice and/or the leading edge of small leaf and the jointing place of wheel disc, described wedge angle comprises pressure side and suction surface, and the pressure side of described wedge angle and suction surface are all arcuately;
The pressure side of described wedge angle originates in described wedge angle and the jointing place of wheel disc, and to extend a segment distance crossing to the pressure side place of blade, and the suction surface of described wedge angle originates in described wedge angle and the jointing place of wheel disc, and to extend a segment distance crossing to the suction surface place of blade;
The length of described wedge angle is greater than its height, its be highly the leaf of blade high 5% ~ 10%;
The pressure side of described wedge angle and the projection plane of suction surface in wheel card are all in incomplete ellipse, and namely pressure side and the projection plane of suction surface in wheel card are all oval parts;
The ellipse at the pressure side of described wedge angle its place, projection plane in wheel card and the ellipse at projection plane its place of suction surface in wheel card, two oval elliptical center points do not overlap;
The major axis of the ellipse at projection plane its place of major axis specific pressure face in wheel card of the ellipse at projection plane its place of suction surface in wheel card of described wedge angle is long, and the minor axis of the ellipse at projection plane its place of minor axis specific pressure face in wheel card of the ellipse at projection plane its place of suction surface in wheel card of described wedge angle is long.
2. the big and small blade impeller of application band wedge angle leading edge according to claim 1, is characterized in that, when only having the leading edge of small leaf to arrange wedge angle, the leading edge of described big leaf's slice is rounding.
3. the big and small blade impeller of application band wedge angle leading edge according to claim 1, is characterized in that, when only having the leading edge of big leaf's slice to arrange wedge angle, the leading edge of described small leaf is rounding.
4. the big and small blade impeller of application band wedge angle leading edge according to claim 1, it is characterized in that, the separating surface between the pressure side of described wedge angle and suction surface is arranged on blade generation stagnation place, and namely described separating surface crosses the stagnation line of blade.
5. the big and small blade impeller of application band wedge angle leading edge according to claim 1, is characterized in that, the pressure side of described wedge angle is connected with the leading edge place smooth transition of suction surface at wedge angle.
6. the big and small blade impeller of application band wedge angle leading edge according to claim 1, is characterized in that, the pressure side of described wedge angle and suction surface, and separating surface place smooth transition between connects.
7. a gas compressor, is characterized in that, comprises the big and small blade impeller of the application band wedge angle leading edge described in any one of claim 1 to 6.
CN201210193389.7A 2012-06-12 2012-06-12 Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor Active CN102889237B (en)

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CN104989672B (en) * 2015-06-19 2017-06-23 中国航空动力机械研究所 A kind of treated casing structure and compressor for improving one-stage centrifugal compressor surge nargin

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CN101173680A (en) * 2007-11-29 2008-05-07 北京航空航天大学 Forward-sweeping big and small blade transonic impeller and axial flow air compressor and inclined flow air compressor
CN101994710A (en) * 2009-08-11 2011-03-30 珠海格力电器股份有限公司 Low-compression ratio centrifugal compressor and air conditioning unit using same
CN102333961A (en) * 2009-10-07 2012-01-25 三菱重工业株式会社 Impeller of centrifugal compressor

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CN101173680A (en) * 2007-11-29 2008-05-07 北京航空航天大学 Forward-sweeping big and small blade transonic impeller and axial flow air compressor and inclined flow air compressor
CN101994710A (en) * 2009-08-11 2011-03-30 珠海格力电器股份有限公司 Low-compression ratio centrifugal compressor and air conditioning unit using same
CN102333961A (en) * 2009-10-07 2012-01-25 三菱重工业株式会社 Impeller of centrifugal compressor

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