CN103867235B - A kind of tubular type subtracts whirlpool device bleed air system - Google Patents
A kind of tubular type subtracts whirlpool device bleed air system Download PDFInfo
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- CN103867235B CN103867235B CN201210552768.0A CN201210552768A CN103867235B CN 103867235 B CN103867235 B CN 103867235B CN 201210552768 A CN201210552768 A CN 201210552768A CN 103867235 B CN103867235 B CN 103867235B
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- scroll
- subtracting
- air system
- tubular type
- whirlpool device
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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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Rotary Pumps (AREA)
Abstract
The invention provides a kind of tubular type for aeroengine and subtract whirlpool device bleed air system, comprise the right dish of gas compressor (1) forming compressor disc chamber, the left dish of gas compressor (2) and the support ring (7) be connected and fixed with the right dish of described gas compressor (1), multiple scroll (4) radial direction that subtracts to be arranged in compressor disc chamber and to be fixed on described support ring (7), wherein, described entrance (401) the circumferentially deflection angle α subtracting scroll (4), the inlet air flow relative velocity direction that described angle [alpha] equals to subtract scroll (4) and the angle of radial direction at fixed position place subtracting scroll (4).The form that the present invention passes through the air flow inlet section subtracting scroll to be designed to deflect to some extent to circumference, with just to airflow direction, effectively can reduce the pressure loss, ensure that aeroengine air system cooling supply gas pressure.
Description
Technical field
The present invention relates in aero engine technology field, particularly engine air system the design subtracting whirlpool device bleed stream.
Background technique
One of target of the bleed flow path designs of aeroengine air system is the reduction pressure loss, ensures the pressure of high-temperature component cooling air feed and pressure of obturaging.
Traditional bleed air system realizes by arranging exterior line, and this all brings adverse effect to engine weight and exterior line layout.The form of the motor employing gas compressor drum barrel perforate that present stage is comparatively advanced achieves inner bleed, avoids these unfavorable factors.But, in inner bleed process, because the high radial location in gas from gas compressor dish chamber flows to low radial location, free vortex development is violent, cause flow losses comparatively large, effectively can weaken the violent development of eddy current by installing the mode subtracting whirlpool device, thus reduce the pressure loss.The design subtracting whirlpool device thus has a certain impact for modern aeroengine performance tool.
Patent documentation US7086830 discloses a kind of tubular type and subtracts whirlpool device structure, until in center cavity after this structure directly subtracts scroll the introducing of the gas of gas compressor sprue, this mode makes to subtract scroll inlet end and fixes, cause air-flow to arrive in center cavity with forced vortex state, flow losses are larger than the transition status from free vortex to forced vortex.Patent documentation US7159402 discloses another kind of tubular type and subtracts whirlpool device structure, and this subtracts whirlpool device inlet end is cantilever structure, and than being directly installed on, drum barrel place (US7086830) pressure loss is little.But these existing tubular types subtract whirlpool device still can not be satisfactory to the effect reducing the pressure loss.
Summary of the invention
The present invention propose on the basis of existing technology a kind of newly subtract whirlpool device bleed air system form, taken into full account aerodynamic characteristic, can realize reducing the object of flow losses.
Tubular type for aeroengine according to the present invention subtracts whirlpool device bleed air system and comprises the support ring forming the right dish of gas compressor in compressor disc chamber, the left dish of gas compressor and be connected and fixed with the right dish of described gas compressor, multiple scroll radial direction that subtracts to be arranged in compressor disc chamber and to be fixed on described support ring, wherein, the described entrance circumferentially deflection angle α subtracting scroll, the inlet air flow relative velocity direction that described angle [alpha] equals to subtract scroll and the angle of radial direction at fixed position place subtracting scroll.
According to a kind of mode of execution, when subtracting the circumferential speed of scroll described in inlet air flow circumferential speed is less than, subtract the described entrance of scroll to engine rotor sense of rotation deflection angle α.
According to another kind of mode of execution, when subtracting the circumferential speed of scroll described in inlet air flow circumferential speed is greater than, subtract the described entrance of scroll in contrast to engine rotor sense of rotation deflection angle α.
Advantageously, described angle [alpha] is 5 ° ~ 85 °.More preferably, described angle [alpha] is 10 ° ~ 80 °.Best, described angle [alpha] is 15 ° ~ 75 °.
Further, the entrance section subtracting scroll described in is vertical with inlet air flow relative velocity direction.
Further, the outer surface subtracting the entrance of scroll described in is the closed surface be made up of curve.
Alternatively, the outer surface subtracting the entrance of scroll described in is the closure plane be made up of straight line.
Tubular type of the present invention subtract whirlpool device bleed air system from reduce air-flow enter subtract scroll produce local losses start with, be made up of circumferential component velocity, radial velocity component, axial component velocity owing to subtracting device ingress, whirlpool airspeed, and axial component velocity is much less than other direction component velocities, substantially can not consider, so air-flow is mainly the resultant velocity of relatively circumferential component velocity and radial velocity component formation under relative coordinate system, there is certain angle with radial direction.Subtract scroll to ensure that air-flow can enter comparatively smoothly, the form being designed to by the entrance subtracting scroll deflect to some extent to circumference, with just to airflow direction, effectively can reduce the pressure loss, ensure that aeroengine air system cooling supply gas pressure.
Accompanying drawing explanation
Embodiment by describing in detail below in conjunction with accompanying drawing is understood by further feature of the present invention and advantage better, in accompanying drawing, and the same or analogous parts of identical designated, wherein:
Fig. 1 is the perspective schematic view subtracting whirlpool device bleed air system structure according to the present invention for the tubular type of aeroengine;
Fig. 2 be illustrate after removing the left dish of gas compressor subtract the perspective schematic view that scroll arranges in compressor disc chamber;
Fig. 3 subtracts the sectional view of scroll mounting structure in axial-radial plane;
Fig. 4 is the sectional view along Fig. 3 center line A-A, shows the inlet air flow circumferential speed subtracting scroll and is less than the entrance structure subtracting scroll when subtracting scroll circumferential speed;
Fig. 5 is the schematic diagram subtracting the entrance structure of scroll according to another kind of preferred implementation in situation shown in Fig. 4;
Fig. 6 is the sectional view along Fig. 3 center line A-A, shows the inlet air flow circumferential speed subtracting scroll and is greater than the entrance structure subtracting scroll when subtracting scroll circumferential speed;
Fig. 7 is the schematic diagram subtracting the entrance structure of scroll according to another kind of preferred implementation in situation shown in Fig. 6.
Description of reference numerals
The left dish of 1 gas compressor right dish 2 gas compressor
3 drum barrel holes 4 subtract scroll
401 entrance 5 drum barrel axles
7 support ring 8 running shafts
101 tangent directions 102 subtract scroll radial direction
103 subtract scroll geometric center lines 104 subtracts spiral inlet cross section
Embodiment
Enforcement and the use of specific embodiments of the invention are described below in detail.But, should be appreciated that described specific embodiment only exemplarily illustrates and implement and use special type of the present invention, but not limit the scope of the invention.
First see Fig. 1 to 3, the whole whirlpool device bleed air system that subtracts is rotated around running shaft 8, and sense of rotation as shown by arrows.Shown in subtract whirlpool device bleed air system and comprise the support ring 7 forming the right dish of gas compressor 1 in compressor disc chamber, the left dish of gas compressor 2 and be connected and fixed with the right dish 1 of described gas compressor, multiple scroll 4 radial direction that subtracts to be arranged in compressor disc chamber and to be fixed on support ring 7 by snap ring, is connected and fixed shown in described support ring 7 such as Fig. 3 by bolt and the right dish 1 of described gas compressor.The air-flow of gas compressor mainstream channel is after stator, fraction enters compressor disc chamber by the long-round-shape drum barrel hole 3 on drum barrel axle 5, and with the radially axis direction flowing of the form of free vortex, gas is by subtracting scroll 4 subsequently, enter in chamber, axle center with the form of forced vortex, which achieves and subtract whirlpool device bleed.
In order to effectively reduce airflow pressure losses, the entrance 401 subtracting scroll 4 is circumferentially deflected an angle [alpha] with just to airflow direction by the present invention, the inlet air flow relative velocity direction that this angle [alpha] equals to subtract scroll 4 and the angle of radial direction at fixed position place subtracting scroll 4.
Specifically, air-flow enters compressor disc chamber, before entering and subtracting scroll 4, if air-flow circumferential speed be less than described in when subtracting the circumferential speed of scroll 4, see Fig. 4 and Fig. 5, subtract the entrance 401 of scroll 4 to engine rotor sense of rotation (illustrating with arrow) deflection angle α.Angle [alpha] is the tangent direction 101 subtracting scroll geometric center lines 103 and subtract spiral inlet cross section 104 point of intersection and the angle (i.e. the angle of inlet air flow relative velocity direction and radial direction 102) subtracted between scroll radial direction 102.
According to another kind of mode of execution, when air-flow is before entering and subtracting scroll 4, if when air-flow circumferential speed is greater than the circumferential speed subtracting scroll 4, see Fig. 6 and Fig. 7, subtract the entrance 401 of scroll 4 in contrast to engine rotor sense of rotation (illustrating with arrow) deflection angle α.
The span of above-mentioned angle [alpha] can be selected as required, such as, take from 5 ° ~ 85 °, and be preferably 10 ° ~ 80 °, the best is 15 ° ~ 75 °.
In addition, as shown in the figure, in order to ensure air-flow enter subtract scroll 4 time effective admission area maximum, the entrance section 104 subtracting scroll 4 is preferably vertical with tangent direction 101.
Should be understood that, although the scroll that subtracts according to the present invention is in entrance place circumferential deflection, described in subtract scroll and remain and be made up of the curved surface of continual curvature.Such as, the outer surface subtracting the entrance 401 of scroll 4 for the closed surface be made up of curve as shown in Figure 4 and Figure 5, can also can be the closure plane be made up of straight line as shown in Figure 6 and Figure 7.In any case, need the entrance 401 ensureing to subtract scroll 4 to subtracting the intermediate section of scroll 4 until subtract the outlet section curvature of curved surface continuous transition of scroll 4.
Below technology contents of the present invention and technical characterstic is disclosed by specific embodiment; but be appreciated that; under creative ideas of the present invention; those skilled in the art can not make various changes in the combination of this feature clearly illustrated and improve above-mentioned disclosed various characteristic sum, and these changes and improvements all belong to protection scope of the present invention.
Claims (9)
1. the tubular type for aeroengine subtracts whirlpool device bleed air system, comprise the right dish of gas compressor (1) forming compressor disc chamber, the left dish of gas compressor (2) and the support ring (7) be connected and fixed with the right dish of described gas compressor (1), multiple scroll (4) radial direction that subtracts to be arranged in compressor disc chamber and to be fixed on described support ring (7), it is characterized in that, described entrance (401) the circumferentially deflection angle α subtracting scroll (4), the inlet air flow relative velocity direction that described angle [alpha] equals to subtract scroll (4) and the angle of radial direction at fixed position place subtracting scroll (4).
2. tubular type according to claim 1 subtracts whirlpool device bleed air system, it is characterized in that, when subtracting the circumferential speed of scroll (4) described in air-flow circumferential speed is less than, subtract the described entrance (401) of scroll (4) to engine rotor sense of rotation deflection angle α.
3. tubular type according to claim 1 subtracts whirlpool device bleed air system, it is characterized in that, when subtracting the circumferential speed of scroll (4) described in air-flow circumferential speed is greater than, the described entrance (401) subtracting scroll (4) is in contrast to engine rotor sense of rotation deflection angle α.
4. the tubular type according to Claims 2 or 3 subtracts whirlpool device bleed air system, it is characterized in that, described angle [alpha] is 5 ° ~ 85 °.
5. tubular type according to claim 4 subtracts whirlpool device bleed air system, it is characterized in that, described angle [alpha] is 10 ° ~ 80 °.
6. tubular type according to claim 5 subtracts whirlpool device bleed air system, it is characterized in that, described angle [alpha] is 15 ° ~ 75 °.
7. tubular type according to claim 6 subtracts whirlpool device bleed air system, it is characterized in that, described in subtract the entrance section of scroll (4) vertical with inlet air flow relative velocity direction.
8. tubular type according to claim 7 subtracts whirlpool device bleed air system, it is characterized in that, described in subtract the entrance (401) of scroll (4) outer surface be the closed surface be made up of curve.
9. tubular type according to claim 7 subtracts whirlpool device bleed air system, it is characterized in that, described in subtract the entrance (401) of scroll (4) outer surface be the closure plane be made up of straight line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210552768.0A CN103867235B (en) | 2012-12-18 | 2012-12-18 | A kind of tubular type subtracts whirlpool device bleed air system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210552768.0A CN103867235B (en) | 2012-12-18 | 2012-12-18 | A kind of tubular type subtracts whirlpool device bleed air system |
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| Publication Number | Publication Date |
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| CN103867235A CN103867235A (en) | 2014-06-18 |
| CN103867235B true CN103867235B (en) | 2015-12-23 |
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| CN201210552768.0A Active CN103867235B (en) | 2012-12-18 | 2012-12-18 | A kind of tubular type subtracts whirlpool device bleed air system |
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Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105201909B (en) * | 2014-06-25 | 2018-04-13 | 中国航发商用航空发动机有限责任公司 | A kind of compressor and its centripetal bleed subtract whirlpool device |
| CN105402028B (en) * | 2015-04-30 | 2017-05-03 | 中国科学院工程热物理研究所 | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine |
| PL415045A1 (en) | 2015-12-03 | 2017-06-05 | General Electric Company | Turbine disk and methods for manufacturing them |
| CN105888849B (en) * | 2016-04-06 | 2017-08-04 | 中国南方航空工业(集团)有限公司 | Bleed cooling structure and the aero-engine with the bleed cooling structure |
| CN107218083A (en) * | 2017-06-21 | 2017-09-29 | 南京航空航天大学 | A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air |
| CN111775177B (en) * | 2020-06-30 | 2022-07-08 | 大连海事大学 | Integrated valve-controlled modular double-acting hydraulic artificial muscle joint |
| CN112377307A (en) * | 2020-10-28 | 2021-02-19 | 北京航空航天大学 | Curved tube type vortex reducing system with high-radius outlet |
| CN112412628A (en) * | 2020-11-27 | 2021-02-26 | 北京化工大学 | Closed type repeated cooling fluid network and closed loop terminal structure for gas turbine |
| CN112283156B (en) * | 2020-12-29 | 2021-03-19 | 中国航发上海商用航空发动机制造有限责任公司 | Gas compressor bleed structure and aeroengine |
| CN114718910A (en) * | 2021-01-06 | 2022-07-08 | 中国航发商用航空发动机有限责任公司 | Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor |
| CN114961893B (en) * | 2021-02-24 | 2023-08-04 | 中国航发商用航空发动机有限责任公司 | Air entraining device of vortex breaker of aero-engine and aero-engine |
| CN113266599B (en) * | 2021-05-21 | 2022-08-09 | 西安交通大学 | Spindle-shaped air-entraining structure for secondary air system of gas turbine |
| CN114838006B (en) * | 2022-04-29 | 2023-04-07 | 北京航空航天大学 | Baffle type vortex-reducing air-entraining system for compressor |
| CN115013549B (en) * | 2022-06-15 | 2023-03-28 | 北京航空航天大学 | Radial bleed air flow regulating system of compressor |
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| US4236869A (en) * | 1977-12-27 | 1980-12-02 | United Technologies Corporation | Gas turbine engine having bleed apparatus with dynamic pressure recovery |
| FR2614654A1 (en) * | 1987-04-29 | 1988-11-04 | Snecma | Turbine engine axial compressor disc with centripetal air take-off |
| US6398487B1 (en) * | 2000-07-14 | 2002-06-04 | General Electric Company | Methods and apparatus for supplying cooling airflow in turbine engines |
| EP1978209A2 (en) * | 2007-03-26 | 2008-10-08 | Honeywell International Inc. | Vortex spoiler for delivery of cooling airflow in a turbine engine |
| RU2451840C2 (en) * | 2010-06-21 | 2012-05-27 | Открытое акционерное общество "Авиадвигатель" | Compressor rotor of gas-turbine engine |
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| DE10159670A1 (en) * | 2001-12-05 | 2003-06-18 | Rolls Royce Deutschland | Vortex rectifier in the high pressure compressor of a gas turbine |
| DE10310815A1 (en) * | 2003-03-12 | 2004-09-23 | Rolls-Royce Deutschland Ltd & Co Kg | Vortex rectifier in tubular design with retaining ring |
| DE102004006775A1 (en) * | 2004-02-11 | 2006-10-19 | Rolls-Royce Deutschland Ltd & Co Kg | Vortex rectifier in tubular construction |
| DE102008024146A1 (en) * | 2008-05-19 | 2009-11-26 | Rolls-Royce Deutschland Ltd & Co Kg | Combined vortex rectifier |
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| US4236869A (en) * | 1977-12-27 | 1980-12-02 | United Technologies Corporation | Gas turbine engine having bleed apparatus with dynamic pressure recovery |
| FR2614654A1 (en) * | 1987-04-29 | 1988-11-04 | Snecma | Turbine engine axial compressor disc with centripetal air take-off |
| US6398487B1 (en) * | 2000-07-14 | 2002-06-04 | General Electric Company | Methods and apparatus for supplying cooling airflow in turbine engines |
| EP1978209A2 (en) * | 2007-03-26 | 2008-10-08 | Honeywell International Inc. | Vortex spoiler for delivery of cooling airflow in a turbine engine |
| RU2451840C2 (en) * | 2010-06-21 | 2012-05-27 | Открытое акционерное общество "Авиадвигатель" | Compressor rotor of gas-turbine engine |
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| Publication number | Publication date |
|---|---|
| CN103867235A (en) | 2014-06-18 |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |