CN102853987A - Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel - Google Patents
Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel Download PDFInfo
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- CN102853987A CN102853987A CN201210358709XA CN201210358709A CN102853987A CN 102853987 A CN102853987 A CN 102853987A CN 201210358709X A CN201210358709X A CN 201210358709XA CN 201210358709 A CN201210358709 A CN 201210358709A CN 102853987 A CN102853987 A CN 102853987A
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Abstract
The invention relates to a tester for researching ice accretion and ice prevention of an aero-engine cowling in an icing wind tunnel, belonging to the technical field of ice accretion and ice prevention of an aero-engine. The tester comprises an external component arranged outside an icing wind tunnel and an internal component arranged inside the icing wind tunnel, wherein the external component comprises an electromotor (1), a driving pulley (18) and a protective cover (19) arranged outside the driving pulley; the internal component comprises a substrate (2), a shaft sleeve (9) installed on the substrate by a support (8), and a revolving shaft (12) installed in the shaft sleeve by a left bearing (7) and a right bearing (10); one end of the revolving shaft is equipped with a conical axis connector (4) on which a cowling (3) is installed; the other end of the revolving shaft is equipped with a passive pulley (13); and the passive pulley is connected with the driving pulley (18) by a belt (14). The tester is designed reasonably, so that the structure size is reduced effectively, and block influences on the icing wind tunnel and disturbances of airflows in the icing wind tunnel are decreased.
Description
Technical field
The present invention is a kind of for belonging to aeromotor accumulated ice and anti-icing technical field in icing tunnel research.
Background technology
When aircraft flew under the subfreezing temperature in high-altitude, if pass through the cloud layer that contains super-cooling waterdrop (temperature is below the freezing point but still keeps liquid water), water droplet bumped on aircraft surfaces, will collision area and near the generation accumulated ice.Aircraft icing has not only increased component weight, and can change Flow Field, destruction aeroperformance, and maneuverability and stability are affected, and brings harm to flight safety.In recent years, because more and more higher to the requirement of security of operation, efficient and the performance of modern aeroengine, the freeze research of phenomenon of relevant engine is also more and more paid attention to.The critical piece of icing phenomenon normally appears (comprising rectification calotte, inlet casing and support plate thereof and compressor inlet guiding blade etc.) in motor head.Wherein the icing phenomenon of engine intake rectification calotte has significant impact to the pneumatic performance of engine, and is light then the amount of air entrainment of engine is descended, and propeller power reduces, in case heavy then ice cube comes off and may cause the damage of engine and parts thereof.So research rectification calotte is anti-icing/except ice problem significant.
The research of the icing phenomenon of relevant engine mainly adopts the modes such as numerical simulation, ground ice wind tunnel test, flight test to carry out.Make a general survey of countries in the world, the country of all capable independent research and development aircraft, great majority have research assessment aircraft and freeze and anti-icing experimental study platform---icing tunnel.Icing tunnel is subjected to the restriction of refrigerating capacity, and the size of test chamber is all little usually, and therefore a large amount of icing tests adopt scaled model to carry out.At present domestic and international accumulated ice experiment about the aeromotor imported equipments and parts launches for aerofoil profile support plate and rectification calotte mostly, but all is the experiment under the stationary state.Above-mentioned existing experimental system is not owing to comprise complicated drive system, therefore do not consider the design of problem such as vibration, gearing in the rotary course that drive system is brought impact and the testpieces rotation of kinematic train ice-formation condition in the congestion affects of icing tunnel, the icing tunnel and gearing for the disturbance in flow field etc., relevant engine rotation part patent icing and the anti-icing experiment device has not yet to see report.
Summary of the invention
For the icing phenomenon of research aeromotor rectification calotte in icing tunnel and explore its ice control, the present invention proposes a kind of research engine rectification calotte accumulated ice and anti-icing exerciser of being applicable in icing tunnel, this exerciser has effectively reduced its physical dimension, has reduced to the occlusive effects of wind-tunnel with to the disturbance of air-flow in the wind-tunnel through appropriate design.
This exerciser forms with the internal part that is positioned at icing tunnel by being positioned at the outer external component of icing tunnel; The said external parts comprise motor, driving pulley and are positioned at the outer protective cover of driving pulley; Above-mentioned internal part comprises: pedestal, be installed on axle sleeve on the pedestal, be installed on rotating shaft in the axle sleeve by pair of bearings by pillar; Rotating shaft one end is equipped with axis of cone web member, on the axis of cone web member radome fairing is installed; The rotating shaft other end is equipped with negative pulley wheel; This negative pulley wheel links by belt and above-mentioned driving pulley; Have on the pedestal and be convenient to the belt grooves that belt passes; Above-mentioned negative pulley wheel has the negative pulley wheel seal closure outward, and above-mentioned belt has the belt seal closure outward.
The present invention is based on following thinking and solves its technical matters and reach design object: this exerciser forms with the internal part that is positioned at icing tunnel by being positioned at the outer external component of icing tunnel, so just motor and driving pulley can be placed in the outside of icing tunnel, thereby significantly reduce the physical dimension of exerciser in wind-tunnel, reduce exerciser to the blockage ratio of wind-tunnel.Motor links to each other with rectification calotte testing table by belt and drives its work.Negative pulley wheel in the test chamber and belt are sealed in the seal closure, thereby prevent the generation of the icing phenomenon in the belt operational process, guarantee the stable of belt runnability.
According to above-mentioned analysis, the present invention separates drive system and rectification calotte testing table, to reach drive system is shifted out icing tunnel, reduces the purpose of rectification calotte testing table size in the icing tunnel, formed thus the separate type overall structures of aeromotor rectification calotte accumulated ice and anti-icing experiment device.
The invention has the beneficial effects as follows:
(1) drive system and rectification calotte testing table are separated, thereby drive system can be shifted out icing wind tunnel, thereby have reduced rectification calotte accumulated ice and the size of anti-icing experiment device in wind-tunnel, are conducive to reduce test unit to the blockage ratio of wind-tunnel.
(2) design of seal closure can prevent that belt from freezing, and guarantees that the belt runnability is stable.Can also prevent that air-flow from passing in and out from belt grooves, the circulation of the inside and outside air-flow of isolated wind-tunnel.Belt and belt pulley have been reduced simultaneously to the disturbance of wind-tunnel flow field.
(3) be connected in the axle sleeve of rectification calotte experiment table front-end of spindle by axis of cone web member, this structural design is so that testpieces is convenient to disassembling, assembling and replacing.
(4) if belt is corresponding with the pillar position of rectification calotte testing table, namely from the direction of air-flow incoming flow, belt is blocked fully by pillar, thereby has further reduced the blockage ratio of test unit to wind-tunnel.
Description of drawings
Fig. 1 is the two-dimentional cut-open view of aeromotor rectification calotte accumulated ice and anti-icing experiment device.
Fig. 2 is the three-dimensional modeling figure of aeromotor rectification calotte accumulated ice and anti-icing experiment device.
Fig. 3 is that aeromotor rectification calotte accumulated ice and the installation site of anti-icing experiment device in icing tunnel concern synoptic diagram.
Among the figure: 1. motor; 2. pedestal; 3. rectification calotte; 4. axis of cone web member; 5. thread bush; 6. bearing cap; 7. left bearing; 8. pillar; 9. axle sleeve; 10. right bearing; 11. nut; 12. rotating shaft; 13. negative pulley wheel; 14. belt; 15. negative pulley wheel seal closure; 16. belt seal closure; 17. belt grooves; 18. driving pulley; 19. protective cover; 20. test chamber.
Embodiment
The present invention is further illustrated below in conjunction with accompanying drawing.
Fig. 1 demonstrates total figure modelling of this anti-icing experiment device, and this exerciser forms with the internal part that is positioned at icing tunnel by being positioned at the outer external component of icing tunnel.External component comprises motor 1, driving pulley 18 and is positioned at driving pulley 18 protective cover 19 outward; Internal part comprises: pedestal 2, be installed on axle sleeve 9 on the pedestal 2, be installed on rotating shaft 12 in the axle sleeve 9 by pair of bearings 7,10 by pillar 8; Rotating shaft one end is equipped with axis of cone web member 4, and radome fairing 3 is installed on the axis of cone web member 4; The rotating shaft other end is equipped with negative pulley wheel 13; This negative pulley wheel 13 links by belt 14 and above-mentioned driving pulley 18; Pedestal 2 has is convenient to the belt grooves 17 that belt 14 passes; Have negative pulley wheel seal closure 16 outside the above-mentioned negative pulley wheel 13, have belt seal closure 16 outside the above-mentioned belt 14.
As shown in Figure 3, in order to reduce accumulated ice and anti-icing experiment device to the occlusive effects of icing wind tunnel, should reduce as far as possible its physical dimension, therefore motor 1 be shifted out icing tunnel, and only keep rectification calotte testing table in the icing tunnel.Rectification calotte testing table is fixed on the deep gouge of icing wind tunnel test section 20 inwalls by pedestal, makes pedestal upper surface concordant with the wall of icing wind tunnel.The belt seal closure 16 front and back in-line arrangements that cover while pillar 8 and belt 14 and outside thereof are seen that from icing tunnel air current flow direction belt seal closure 16 is blocked fully by pillar 8, thereby are further reduced exerciser to the obstruction of icing tunnel.
In order to prevent the generation of icing phenomenon in the belt operational process, guarantee that the belt runnability is stable, the belt 14 in the test chamber and negative pulley wheel 13 are sealed in belt seal closure 16 and the negative pulley wheel seal closure 15. Seal closure 15,16 is the circulation of the inside and outside air-flow of isolated wind-tunnel also, prevents that air-flow from passing in and out from belt grooves 17, and has reduced belt and belt pulley to the disturbance of wind-tunnel flow field.
Rectification calotte 3 is connected to the front end of rotating shaft 12 via axis of cone web member 4, and is fixed by thread bush 5, and design can be changed and dismounting rectification calotte testpieces easily like this.
This exerciser can carry out having again without the experiment of ice-phobic coating calotte the experiment of ice-phobic coating calotte.
Claims (2)
1. one kind is used for icing tunnel research airplane engine cowling accumulated ice and anti-icing exerciser, it is characterized in that:
Comprise the internal part that is positioned at the outer external component of icing tunnel and is positioned at icing tunnel;
Wherein external component comprises motor (1), driving pulley (18) and is positioned at the outer protective cover (19) of driving pulley;
Wherein internal part comprises: pedestal (2), be installed on axle sleeve (9) on the pedestal, be installed on rotating shaft (12) in the axle sleeve by left bearing (7) and right bearing (10) by pillar (8); Rotating shaft one end is equipped with axis of cone web member (4), and radome fairing (3) is installed on the axis of cone web member; The rotating shaft other end is equipped with negative pulley wheel (13); This negative pulley wheel links by belt (14) and above-mentioned driving pulley (18); Have the belt grooves (17) of being convenient to belt and passing on the pedestal (2); Have negative pulley wheel seal closure (15) outside the above-mentioned negative pulley wheel (13), have belt seal closure (16) outside the above-mentioned belt (14).
2. aeromotor rectification calotte accumulated ice according to claim 1 and anti-icing experiment device is characterized in that: see that from icing tunnel air current flow direction belt seal closure (16) is blocked fully by above-mentioned pillar (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210358709XA CN102853987A (en) | 2012-09-25 | 2012-09-25 | Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210358709XA CN102853987A (en) | 2012-09-25 | 2012-09-25 | Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel |
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| Publication Number | Publication Date |
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| CN102853987A true CN102853987A (en) | 2013-01-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210358709XA Pending CN102853987A (en) | 2012-09-25 | 2012-09-25 | Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103759915A (en) * | 2014-01-29 | 2014-04-30 | 中国商用飞机有限责任公司 | Test measurement method of local water collecting coefficient |
| CN106556509A (en) * | 2015-09-29 | 2017-04-05 | 中航商用航空发动机有限责任公司 | Ice comes off assay device, system and method |
| CN108106809A (en) * | 2017-12-14 | 2018-06-01 | 大连四达高技术发展有限公司 | Low blockage percentage support device |
| CN108104051A (en) * | 2017-12-27 | 2018-06-01 | 长春华普大通防冰工程技术有限公司 | A kind of air blowing component and the anti-icing equipment with air blowing component |
| CN113804394A (en) * | 2021-11-10 | 2021-12-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Air-jet anti-icing device, ice-shape online measurement system and method |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103759915A (en) * | 2014-01-29 | 2014-04-30 | 中国商用飞机有限责任公司 | Test measurement method of local water collecting coefficient |
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| CN106556509A (en) * | 2015-09-29 | 2017-04-05 | 中航商用航空发动机有限责任公司 | Ice comes off assay device, system and method |
| CN106556509B (en) * | 2015-09-29 | 2019-07-26 | 中国航发商用航空发动机有限责任公司 | Ice falls off experimental rig, system and method |
| CN108106809A (en) * | 2017-12-14 | 2018-06-01 | 大连四达高技术发展有限公司 | Low blockage percentage support device |
| CN108104051A (en) * | 2017-12-27 | 2018-06-01 | 长春华普大通防冰工程技术有限公司 | A kind of air blowing component and the anti-icing equipment with air blowing component |
| CN108104051B (en) * | 2017-12-27 | 2023-11-28 | 长春华普大通防冰工程技术有限公司 | Blowing assembly and anti-icing device with same |
| CN113804394A (en) * | 2021-11-10 | 2021-12-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Air-jet anti-icing device, ice-shape online measurement system and method |
| CN113804394B (en) * | 2021-11-10 | 2023-03-21 | 中国空气动力研究与发展中心低速空气动力研究所 | Air-jet anti-icing device, ice-shape online measurement system and method |
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Application publication date: 20130102 |