CN203272243U - Treated casing for gas aeroengines - Google Patents
Treated casing for gas aeroengines Download PDFInfo
- Publication number
- CN203272243U CN203272243U CN2012207408569U CN201220740856U CN203272243U CN 203272243 U CN203272243 U CN 203272243U CN 2012207408569 U CN2012207408569 U CN 2012207408569U CN 201220740856 U CN201220740856 U CN 201220740856U CN 203272243 U CN203272243 U CN 203272243U
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- Prior art keywords
- circumferential
- slot
- groove
- processor
- processor box
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A treated casing for rotor blades of gas aeroengines is provided with a sunken circumferential through groove, wherein the circumferential through groove is a smooth curve on the meridian section, and moreover, on a direction parallel with the axial direction of main gas flow, the width of the opening of the circumferential through groove is less than the maximum width in the circumferential through groove. The standing vortex type treated casing has a remarkable effect of improving the tip flow field of a gas compressor, so that the flow in tip areas is more reasonable, so the treated casing can more remarkably increase the stability margin of the gas compressor and achieve higher adiabatic efficiency and higher pressure ratio characteristic in comparison with conventional circumferential groove treated casings.
Description
Technical field
The utility model relates to a kind of processor box, belongs to impeller machinery technical field.
Background technique
Turbomachine is used in the fields such as aeroengine and industry gas turbine in a large number.But at work, gas compressor tends to produce unstable period due to the variation of internal work state or external environment, and as rotating stall, surge etc., this has also limited the further lifting of Capability of Compressor.When rotating stall or during surge, the performance of turbine can descend suddenly, flow, pressure ratio and efficient sharply reduce, and the gas compressor blade sector-meeting is subject to the effect of periodic excitation force, structural strength, life-span to gas compressor produce and have a strong impact on, in case occur on aeroengine, just may cause fatal crass's accident, very harmful.Therefore people have taked a lot of methods to postpone gas compressor and have rotated the wild effects such as stall, surge, to enlarge its stable operation nargin.
The steady effect of the expansion of processor box technology is very obvious, simultaneously, because processor box is just processed the interior casing of gas compressor, does not need the changing of compressor blade itself, and practicability is very strong, has obtained using more widely.Lot of domestic and international advanced aero engine machine gas compressor used has adopted this technology at present.
Fig. 1-Fig. 3 has provided three kinds of typical processor casing structure forms.
As shown in Figure 1, axial chute processor casing 12 is axially grooved along gas compressor on casing, radially form an angle (being generally 60 degree) of its groove depth direction and gas compressor.When the groove depth direction aimed at flow path direction, no matter incoming flow was uniform-flow or the import distortion occurs, and stability margin has larger improvement.But the shortcoming of this class processor box is, the improvement of stability margin is take the efficient of loss gas compressor as cost.
As shown in Figure 2, tangential chute processor casing 14 be on casing along the tangential fluting of blade tip primitive, the groove depth direction can have different angles.In the uniform incoming flow situation, the growth of stability margin is only second to axial chute processor casing, and the loss of compressor efficiency is also lacked than axial chute.
As shown in Figure 3, peripheral groove processor box 16 is to slot along circumferential on casing, and the groove depth direction can have different angles.This processor box is less to the loss in efficiency of gas compressor.
In sum, conventional process casing technology is difficult to improve simultaneously stability margin and the adiabatic efficiency of gas compressor.Comprise most of processor box of above-mentioned front two kinds of typical structure processor boxes when enlarging the gas compressor stability margin, usually can reduce the efficient 1%-3% left and right of gas compressor.On aeroengine, the decline of the adiabatic efficiency of gas compressor means that fuel consume can be more, and this is particularly important to civil aviation motor or gas turbine.
The model utility content
For the shortcoming that above-mentioned conventional process casing technology exists, the utility model provides that a kind of can to form stable whirlpool and the cross section stayed in treatment trough be major arc or highly greater than the peripheral groove processor box of the truncated ellipsoid of semi-major axis.The utility model can improve stability margin and the efficient of processor box.
Particularly, the utility model discloses a kind of processor box of the rotor blade for the aviation gas engine, processor box has inwardly recessed circumferential through slot, wherein, circumferentially through slot is smoothed curve on the meridian cross section, and on being parallel to the main air flow axial direction circumferentially the width of rebate of through slot less than the maximum groove width in the groove of circumferential through slot.
Selectively, circumferentially the meridian cross section of through slot is circular arc.
Preferably, be parallel on the main air flow axial direction, the groove width of notch is the 8%-12% of the chord length of rotor blade.
More preferably, the central angle of circular arc is not less than 240 °.
Particularly, circumferentially through slot is arranged as one or more corresponding to each rotor blade.
Selectively, circumferentially the meridian cross section of through slot is the ellipse of butt.
Preferably, circumferentially the groove depth of through slot is not less than 0.75 times of oval major axis.
More preferably, the angle of the long axis direction of the ellipse of butt and main air flow axial direction is between 60 °-120 °.
Particularly, circumferentially through slot is furnished with a plurality of corresponding to each rotor blade.
Preferably, circumferentially the flute wall surfaces of through slot is coarse.
Particularly, rotor blade is fan propeller or compressor rotor blade.
When this processor box of formula in the whirlpool uses in gas compressor, can form the vortex in the stable single whirlpool with certain circumferential speed in treatment trough, compare with the conventional process casing, flow in groove more stable, can obtain better to expand steady effect, higher efficient, simultaneously, the axial Extreme breadth of this processor box position is in groove, and this makes notch flow to flow on interface with main flow area velocity attitude more consistent, has reduced the loss that brings due to blending.Thereby the expansion that realizes improving processor box is steady and the effect of efficiency characteristic.
This processor box of formula in the whirlpool can be to the obvious improvement effect of blade tip flow field generation of gas compressor, make flowing of blade tip zone more reasonable, thereby can obtain the stability margin that more significantly improves gas compressor than traditional peripheral groove processor box, higher adiabatic efficiency, higher pressure ratio characteristic.
Description of drawings
In order to explain the utility model, its illustrative embodiments will be described with reference to the drawings hereinafter, in accompanying drawing:
Fig. 1 schematically shows the axial groove processor box of prior art;
Fig. 2 schematically shows the tangential groove processor box of prior art;
Fig. 3 schematically shows the peripheral groove processor box of prior art;
Fig. 4 schematically shows the major arc groove processor box of a kind of mode of execution of the present utility model;
Fig. 5 schematically shows the butt oval groove processor box of another kind of mode of execution of the present utility model.
Similar features in different figure is by similar reference character indication.
Embodiment
In the detailed description of following mode of execution, the accompanying drawing that reference consists of the part of this description describes.Accompanying drawing shows specific mode of execution in the mode of example, and the utility model is implemented in these mode of executions.Shown mode of execution is not according to all mode of executions of the present utility model for limit.The mode of execution that is appreciated that other can be utilized, and change structural or logicality can be made under the prerequisite that does not break away from scope of the present utility model.For accompanying drawing, the term of directivity, such as D score, " on " etc., with reference to the orientation of described accompanying drawing using.Because the assembly of mode of execution of the present utility model can be implemented with multiple orientation, these directional terminology are the purposes for explanation, rather than the purpose of restriction.Therefore, following embodiment is not the meaning as restriction, and scope of the present utility model is limited by appending claims.
Referring to Fig. 4, it shows the processor box 100 of the first mode of execution of the present invention, and the treatment trough 102 on this processor box 100 is circumferential through slot, and the meridian cross section of this circumferential through slot is major arc.
Particularly, this treatment trough 102 is generally over against the rotor blade blade tip, relatively rotor blade be arranged on sharf before the center of chord length (namely, slightly near the upstream), also can be arranged on sharf (that is, slightly near the downstream) after the center of chord length or its center, preferably, in transonic compressor, this treatment trough 102 is arranged on sharf after the center of chord length.The number of this treatment trough 102 can for one also can be for a plurality of, this depends on the groove width for the treatment of trough 102 itself, general, the number of this treatment trough 102 is not more than 7.On the meridian cross section, the axial length L that this treatment trough 102 contacts with main air flow at the notch place is about the 8%-12% left and right of the axial chord length of blade, and, because the meridian cross section of this treatment trough 102 is major arc, namely, the corresponding central angle angle of circular arc institute is more than or equal to 240 °, on being parallel to the main air flow axial direction width of rebate of this treatment trough 102 less than the maximum groove width in the groove for the treatment of trough 102.Can determine the radius of arc for the treatment of trough 102 according to central angle and base surface axial length, single groove can promote the voltage rise nargin of 4% left and right, and guaranteed efficiency is constant simultaneously even slightly is improved, and is applicable to expanding in the not too large gas compressor of steady demand.
With the difference of traditional curvilinerar figure treatment trough be, be parallel in this treatment trough 102 grooves the vat insied width of main air flow direction greater than with the width at main air flow interface (notch place), can guarantee like this its inner vortex stability of staying, this form need to be achieved by corrosion or other processing technologys it.The certain roughness of the computational chart interior assurance of bright treatment trough 102 more is conducive to its raising efficiency.Adopt a plurality for the treatment of troughs 102 can realize that the nargin of 12% left and right promotes in gas compressor.
Referring to Fig. 5, it shows the processor box 200 of the second mode of execution of the present invention, and the treatment trough 202 on this processor box 200 is circumferential through slot, and the meridian cross section of this circumferential through slot is that butt is oval.So-called " butt is oval " refers to the shape that complete ellipse is clipped the remaining end opening of a part herein.
Particularly, this treatment trough 202 is generally over against the rotor blade blade tip, relatively rotor blade be arranged on sharf before the center of chord length (namely, slightly near the upstream), also can be arranged on sharf after the center of chord length or its center (namely, slightly near the downstream), preferably, this treatment trough 202 is arranged on sharf after the center of chord length.The number of this treatment trough 202 is preferably a plurality of, arranges along the main air flow axial direction in parallel with each other, and usually, the number of this treatment trough 202 is not more than 7.The long axis direction of this butt ellipse can with the main air flow 60 °≤α in angular separation≤120 °, the groove depth for the treatment of trough 202 is easily sayed it more than or equal to 1.5 times of the semi-major axis height, is not less than 0.75 times of major axis.By this, on being parallel to the main air flow axial direction width of rebate of this treatment trough 202 less than the maximum groove width in the groove for the treatment of trough 202.
With the difference of traditional curvilinerar figure treatment trough be, be parallel in this treatment trough 202 grooves the vat insied width of main air flow direction greater than with the width at main air flow interface (notch place), can guarantee like this its inner vortex stability of staying, this form need to be achieved by corrosion or other processing technologys it.The certain roughness of the computational chart interior assurance of bright treatment trough 202 more is conducive to its raising efficiency.Adopt a plurality for the treatment of troughs 202 can realize that the nargin of 12% left and right promotes in gas compressor.
It will be appreciated by those skilled in the art that, the stable whirlpool of staying can also be realized by wall or the increasing groove depth that adopts other curve forms, but the two might make the flow losses of processor box increase, therefore, for balance nargin promotes and flow losses, need select suitable meridian sectional shape and design suitable groove depth.Yet, in any case design the different treatment troughs of formula in the whirlpool, the Extreme breadth that is parallel to main flow direction in this groove all should greater than with the width of main flow surface of contact.
The those skilled in the art of those the art can be by research specification, disclosed content and accompanying drawing and appending claims, understanding and enforcement other changes to the mode of execution of disclosure.In the claims, word " comprises " element and the step of not getting rid of other, and wording " one " is not got rid of plural number.In the practical application of model utility, the function of a plurality of technical characteristicss of quoting during a part possibility enforcement of rights requires.Any reference character in claim should not be construed as the restriction to scope.
The utility model is limited to the illustrative embodiments that presents never in any form in specification and accompanying drawing.Within all combinations of the mode of execution that illustrates and describe (part) are interpreted as clearly and incorporate this specification into and be interpreted as clearly and fall in scope of the present utility model.And in the scope of the present utility model of summarizing as claims, a lot of distortion are possible.In addition, any reference mark in claims should be configured to limit scope of the present utility model.
Claims (11)
1. processor box that is used for the rotor blade of aviation gas engine, described processor box has inwardly recessed circumferential through slot, it is characterized in that, described circumferential through slot is smoothed curve on the meridian cross section, and at the width of rebate that is parallel to the above circumferential through slot of main air flow axial direction less than the maximum groove width in the groove of described circumferential through slot.
2. processor box according to claim 1, is characterized in that, the meridian cross section of described circumferential through slot is circular arc.
3. processor box according to claim 1, is characterized in that, is being parallel on the main air flow axial direction, and the groove width of described notch is the 8%-12% of the chord length of described rotor blade.
4. processor box according to claim 2, is characterized in that, the central angle of described circular arc is not less than 240 °.
5. according to claim 2 or 3 described processor boxes, is characterized in that, described circumferential through slot is furnished with 1-7 corresponding to each rotor blade.
6. processor box according to claim 1, is characterized in that, the meridian cross section of described circumferential through slot is the ellipse of butt.
7. processor box according to claim 6, is characterized in that, the groove depth of described circumferential through slot is not less than 0.75 times of major axis of described ellipse.
8. according to claim 6 or 7 described processor boxes, is characterized in that, the angle of the long axis direction of the ellipse of described butt and described main air flow axial direction is between 60 °-120 °.
9. according to claim 6 or 7 described processor boxes, is characterized in that, described circumferential through slot is furnished with 1-7 corresponding to each rotor blade.
10. according to claim 2 or 6 described processor boxes, is characterized in that, the flute wall surfaces of described circumferential through slot is coarse.
11. processor box according to claim 1 is characterized in that, described rotor blade is fan propeller or compressor rotor blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012207408569U CN203272243U (en) | 2012-12-28 | 2012-12-28 | Treated casing for gas aeroengines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012207408569U CN203272243U (en) | 2012-12-28 | 2012-12-28 | Treated casing for gas aeroengines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203272243U true CN203272243U (en) | 2013-11-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012207408569U Expired - Lifetime CN203272243U (en) | 2012-12-28 | 2012-12-28 | Treated casing for gas aeroengines |
Country Status (1)
| Country | Link |
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| CN (1) | CN203272243U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105298923A (en) * | 2014-06-17 | 2016-02-03 | 中国科学院工程热物理研究所 | Front seam and rear groove type casing treatment stability enhancement device for gas compressor |
| CN112283167A (en) * | 2020-11-20 | 2021-01-29 | 西安热工研究院有限公司 | Circumferential groove type casing treatment design method for axial flow compressor |
-
2012
- 2012-12-28 CN CN2012207408569U patent/CN203272243U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105298923A (en) * | 2014-06-17 | 2016-02-03 | 中国科学院工程热物理研究所 | Front seam and rear groove type casing treatment stability enhancement device for gas compressor |
| CN105298923B (en) * | 2014-06-17 | 2018-01-02 | 中国科学院工程热物理研究所 | Slot type treated casing expands stabilization device after being stitched before compressor |
| CN112283167A (en) * | 2020-11-20 | 2021-01-29 | 西安热工研究院有限公司 | Circumferential groove type casing treatment design method for axial flow compressor |
| CN112283167B (en) * | 2020-11-20 | 2022-04-01 | 西安热工研究院有限公司 | Circumferential groove type casing treatment design method for axial flow compressor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20131106 |
|
| CX01 | Expiry of patent term |