CN103184935B - Hot-air anti-icer for engine inlet - Google Patents
Hot-air anti-icer for engine inlet Download PDFInfo
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- CN103184935B CN103184935B CN201110447988.2A CN201110447988A CN103184935B CN 103184935 B CN103184935 B CN 103184935B CN 201110447988 A CN201110447988 A CN 201110447988A CN 103184935 B CN103184935 B CN 103184935B
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- air
- icer
- circulating line
- engine inlet
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Abstract
The invention relates to a hot-air anti-icer for an engine inlet, belonging to the technical field of anti-icing for aero-engine inlets. The invention aims to provide the hot-air anti-icer which is capable of effectively controlling the flow direction of hot-air so as to improve heat exchange efficiency. The hot-air anti-icer apparatus comprises an air introducing pipeline introducing hot air out from a compressor, an annular pipeline communicated with the air introducing pipeline, a plurality of supports supporting the annular pipeline to the front wall surface of an inlet nacelle, a plurality of diversion blade cascades installed on a lip part formed on an air spraying throat of the annular pipeline and used for guiding air-flow and an exhaust pipeline used for discharging air having undergone heat exchange in a heat exchange passage. According to the invention, sprayed hot-air is allowed to flow, as closely as possible, along an anti-icing surface in the heat exchange passage at the front of the inlet and to spirally flow forward in the heat exchange passage, so heat exchange efficiency is improved to the greatest extent.
Description
Technical field
The present invention relates to the anti-icing technology of aeroengine intake duct, relate more specifically to aeroengine intake duct hot gas anti-icing system.
Background technique
It is situation the most dangerous during aircraft freezes that aeroengine intake duct freezes, it not only directly causes the destruction of the pneumatic external form of intake duct, reduce motor power, increase flight load, and in intake duct, ice sheet is once come off, ice cube will enter engine interior with air-flow, not only can injure and there is the blade of very large rotating speed, cause the mechanical deterioration of gas compressor, even whole motor is damaged, directly cause flying accident.Therefore, in order to ensure flight safety, Engine Anti-Ice is very important.At present, the hot air that thermal source many employings engine compressor of Engine Anti-Ice is drawn, after hot air enters the anti-icer of intake duct leading edge, along in the flow process of passage, heat is passed to covering, the temperature on the anti-icing surface of intake duct leading edge is reached and guarantees surperficial non-icing numerical value.
Common hot air anti-icing device, by bleed air, flows through and controls after valve, allows hot air free-flow in intake duct leading edge heat exchanger channels, finally discharges from outlet; Or adopt simple and easy ring jet pipeline, be fixed on before nacelle on ballasting wall by support, the aperture of hot air by ring jet pipeline is opened, is ejected to anti-icing surface in certain direction by hot gas, plays anti-icing effect.But, no matter which kind of anti-icer above-mentioned all do not realize to thermal air current to effective control, heat exchange efficiency is difficult to ensure.
Summary of the invention
Therefore, provide a kind of can effectively control thermal air current to thus to improve the hot-air anti-icer for engine inlet of heat exchange efficiency will be favourable.
For this reason, according to an aspect of the present invention, a kind of hot-air anti-icer for engine inlet is provided, this device comprises: bleed pipeline, circulating line, exhaust duct, multiple support frame and multiple guide-ring, wherein, bleed pipeline extends for receiving the hot air from engine compressor along described intake duct; Circulating line have be connected with described bleed pipeline air flow inlet, to be connected with intake duct leading edge heat exchanger channels and to be close to the ring jet throat on anti-icing surface in it, to be extended by described ring jet throat side and with the lip of a described anti-icing spaced intended distance and be formed at the fracture that described circulating line is arranged with described air flow inlet radial symmetric; One end of exhaust duct is communicated with described heat exchanger channels via the described fracture of described circulating line, and the other end is communicated with external environment or described intake duct and is used for hot air complete for heat exchange to discharge in heat exchanger channels; Multiple support installing is on the nacelle front face of described intake duct and be used for supporting described circulating line; Make hot air along the anti-icing surface flowing of intake duct leading edge and advance in the shape of a spiral in heat exchanger channels on the described lip that multiple guide-ring is installed on described circulating line and between described lip and described anti-icing surface.
At this on the one hand, due to the structure of circulating line itself and the setting of guide-ring, thus this deicer can control the emission direction of hot air, make the anti-icing surface flowing that hot air is fitted in intake duct leading edge heat exchanger channels as much as possible, and advance in the shape of a spiral in heat exchanger channels, improve heat exchange efficiency to greatest extent, and then reduce the amount of air entrainment from high-pressure compressor.
Preferably, multiple guide-ring becomes 10 ° ~ 80 ° to be obliquely installed relative to the radial direction of described intake duct.Like this, the hot air sprayed by circulating line throat is via after the shunting of guide-ring guiding, and flowing in anti-icing surface of fitting at a certain angle, and advances at heat exchanger channels internal spiral, then discharged by exhaust duct.
Preferably, described multiple guide-ring is uniformly distributed circumferentially on the circulating line between described air flow inlet and described fracture, and symmetrical about face in described air flow inlet and described fracture.Thus the hot air sprayed by circulating line is also finally discharged heat exchanger channels along anti-icing surface distributed and flowing equably.
Further preferably, described circulating line is provided with slide block towards the side of described support, and described support is formed with chute, described slide block in described chute circumference slidably, to adapt to the thermal expansion effects of circulating line.
By reference to mode of execution described below, these and other aspects of the present invention face will clearly be set forth.
Accompanying drawing explanation
Structure of the present invention and mode of operation and further object and advantage are better understood by the description below in conjunction with accompanying drawing, and wherein, identical reference mark identifies identical element:
Fig. 1 is the perspective view of motor, that schematically shows the external structure of motor;
Fig. 2 is the sectional view of the longitudinal axis along motor shown in Fig. 1, and it schematically shows the internal structure of motor, and for clarity sake eliminates the hanging of motor;
Fig. 3 is the perspective schematic view of the nacelle inlet of motor shown in Fig. 1, it illustrates the bleed pipeline according to the hot-air anti-icer for engine inlet of a preferred implementation of the present invention and exhaust duct;
Fig. 4 is the schematic diagram of the hot-air anti-icer for engine inlet according to above-mentioned preferred implementation of the present invention, which basically illustrates circulating line and support;
Fig. 5 shows the arrangement of circulating line in the anti-icing heat exchanger channels of engine nacelle intake duct leading edge of the hot air anti-icing device in Fig. 4;
Fig. 6 is the longitudinal sectional view of the engine nacelle intake duct of the hot air anti-icing device be provided with in Fig. 4, shows the air flow direction of hot air anti-icing device;
Fig. 7 is the close-up schematic view at the guide-ring place, hot air anti-icing device section in Fig. 4, shows the air-flow in the flowing of motor heat exchanger channels internal spiral;
Fig. 8 is the close-up schematic view of the air flow outlet of hot air anti-icing device in Fig. 4;
Fig. 9 is the slide block schematic diagram for connecting circulating line and support of hot air anti-icing device in Fig. 4;
Figure 10 is the perspective schematic view of the support for supporting circulating line of hot air anti-icing device in Fig. 4.
Embodiment
As requested, the specific embodiment of the present invention will be disclosed here.But should be understood that, mode of execution disclosed is here only exemplary of the present invention, and its cocoa is presented as various forms.Therefore, here the detail disclosed is not considered to restrictive, and be only as the basis of claim and as instructing those skilled in the art differently to apply representational basis of the present invention in appropriate mode any in reality, the various features comprising employing disclosed here also combine the feature that may clearly not disclose here.
As shown in Figure 1, and composition graphs 2, Fig. 1 shows a motor 100, and under it is connected to the wing of aircraft by hanging 110, certainly, it also can be connected to other regions of aircraft.This motor 100 has nacelle 120, and the longitudinal axis X of motor 100 as shown in Figure 2.
Again as shown in Figure 1, engine nacelle 120 has inner tubal wall, which defines the pipeline of motor head intake duct 150 (i.e. nacelle inlet).The leading edge of intake duct 150 roughly forms a ring bodies, and it extends along a plane substantially vertical with longitudinal axis X, as shown in Figure 2.Certainly, intake duct described herein also can consider other form.
As shown in figs. 3-10, bleed pipeline 10, circulating line 20, exhaust duct 30, multiple support 40 and multiple guide-ring 50 is comprised according to the hot-air anti-icer for engine inlet of the present invention one preferred implementation.As shown in Fig. 2, Fig. 3 and Fig. 6, bleed pipeline 10 is extended to circulating line 20 along described intake duct 150 by engine compressor 160, for the hot air from gas compressor 160 is guided in circulating line 20, preferably, between bleed pipeline 10 and gas compressor 160, be also provided with bleed control valve 60, to control the amount of the hot air of drawing from gas compressor 160 by controlling valve 60.Should be understood that, the surface of bleed pipeline 10 is preferably coated with insulation material layer 11, in case due to overheated and burn out sound lining 180 (see Fig. 2), and avoid the unnecessary heat leakage of the hot air flowed through.
As shown in Figure 3, the hot air of coming from gas compressor 160 is introduced the circulating line 20 in intake duct 150 leading edge calotte 190 by bleed pipeline 10.As shown in Figure 4, and with reference to figure 5-9, circulating line 20 have be connected with described bleed pipeline 10 air flow inlet 21 (i.e. circulating line herein opening be connected with bleed pipeline), to be connected with the leading edge heat exchanger channels 151 of intake duct 150 and to be close to the ring jet throat 22 of anti-icing surperficial 152 in heat exchanger channels 151, to be extended by described ring jet throat 22 side and with the lip 23 of described anti-icing surperficial 152 spaced apart intended distance S1 and be formed at the fracture 24 that described circulating line 20 is arranged with described air flow inlet 21 radial symmetric.Two the fracture ends being positioned at described fracture 24 place that it should be noted that circulating line 20 are cecums, such as, by forming cecum at fracture end welding cecum baffle plate 26.Should be understood that, arranging of above-mentioned fracture 24 can adapt to expanding with heat and contract with cold of circulating line 20.
As shown in Figure 3 and composition graphs 9, one end of exhaust duct 30 is communicated with described heat exchanger channels 151 in described fracture 24 position of described circulating line 20, the other end and external environment connect are used for hot air complete for heat exchange to discharge in heat exchanger channels, certainly, the above-mentioned the other end of exhaust duct 30 also can be communicated to intake duct 150, thus is drained in intake duct by the air of discharging after heat exchange again.
As shown in Fig. 4-5,6-8, the shape of above-mentioned guide-ring 50 for flat board or can have certain pneumatic external form, and titanium alloy or other refractory alloys can be adopted to make.Circumferential distance between two adjacent guide-rings 50 can be 1mm ~ 10mm, they are installed on the described lip 23 of described circulating line 20, and between described lip 23 and described anti-icing surperficial 152, thus make throat 22 hot air out via circulating line 20 flow along anti-icing surperficial 152 of intake duct 150 leading edge and advance in the shape of a spiral in heat exchanger channels, as shown in fig. 6-7.These guide-rings 50 are arranged relative to the inclined of described intake duct 150, preferably become 10 ° ~ 80 ° to be obliquely installed relative to the radial direction of intake duct.Like this, after the hot air sprayed by circulating line throat 22 is shunted via guide-ring guiding, anti-icing surperficial 152 flowings of fitting ideally, and advance at heat exchanger channels 151 internal spiral, then discharged by exhaust duct 30.
Should be understood that, the lip 23 of circulating line 20 and anti-icing surperficial 152 want isolated intended distance ideally between 2mm and 40mm, guide-ring 50 is installed on lip 23 in this interval, such as, be fixed on lip 23 by welding or the mode such as bonding.These guide-rings 50 are preferably uniformly distributed circumferentially on the circulating line 20 between air flow inlet 21 and described fracture 24, and ideally, guide-ring is symmetrical about face in described air flow inlet 21 and described fracture 24, that is: guide-ring crosses the semi-section symmetry of the line of centres of air flow inlet 21 and described fracture 24 about nacelle inlet 150, as shown in Figure 4.Like this, spray via guide-ring 50 and naturally understand and carry out thermal cycle at the advance hot air flow that finally enters exhaust duct 30 of heat exchanger channels 151 internal spiral along respective flow path, strengthen and know clearly and the anti-icing heat exchange of surperficial 152, thus heat exchange efficiency is higher.
For another example, shown in Fig. 4, Fig. 5 and Figure 10, the nacelle front face 153 that multiple support 40 is installed on described intake duct 150 is used for supporting described circulating line 20, thus circulating line 20 is arranged on nacelle front face 153 (as shown in Figure 5).As Fig. 4 shows best, in order to better circulating line 20 is supported and fixed on the nacelle front face 153 of intake duct 150, near the air flow inlet 21 of circulating line 20 and near fracture 24, spacing between two adjacent supports 40 is smaller, namely, preferably in these two positions, support 40 is arranged more intensive, to make circulating line 20 be supported securely; And in other positions, the spacing of adjacent stent can be relatively larger.Such as, in the present embodiment, the circumferential spacing of adjacent two supports near air flow inlet 21 and near fracture 24 can be 20 °, and between other adjacent stents, circumferential spacing can be 40 °.Certainly, this spacing can change to some extent according to actual conditions and adjust.
Figure 10 schematically shows the structure of single support 40.Described support comprises the bearing 41 that is fixed on described nacelle front face 153 and is supported by described bearing 41 and be formed with the water conservancy diversion support plate 43 of described chute 42.As shown in Figure 6 and Figure 7, described water conservancy diversion support plate 43 is preferably arranged relative to the inclined of described intake duct 151,10 ° ~ 80 ° are become to be in tilted layout relative to the radial direction of intake duct ideally, and its true dip direction is along the flow direction of air-flow in heat exchanger channels 151, thus more effectively ensure the air current flow in heat exchanger channels.
As seen in figs. 8-10, coordinating preferably by means of the slide block 25 (Fig. 9) on circulating line and the chute 42 on support is connected and fixed between circulating line 20 with support 40.As shown in Figure 8, slide block 25 can be integrally formed with circulating line 20, also in the welding of the below of circulating line 20 or can be bonded with this slide block 25.Chute 42 is formed on the water conservancy diversion support plate 43 of support 40, sees Figure 10.When circulating line 20 support is fixed on nacelle front face 153 by support 40, be distributed in the slide block 25 below circulating line 20 and chute 42 slip joint on support 40, the chute 42 of slide block 25 on support is allowed to do circumferential small slip, to adapt to the thermal expansion effects of annular air entraining pipe 20.Should be understood that, slide block 25 is also preferred about air flow inlet 21 and symmetrical as face in the fracture 24 of flow outlet.
Specifically describe the working procedure of hot-air anti-icer for engine inlet in above-mentioned mode of execution below.Hot air in gas compressor 160 controls valve 60 by bleed and enters bleed pipeline 10 (see Fig. 2), and imports in circulating line 20 (see Fig. 6) via bleed pipeline 10.Air-flow is while the flowing of circulating line 20 inner circumferential, throat 22 via circulating line 20 sprays, then, under the effect of guide-ring 50, fit at a certain angle anti-icing surperficial 152 flowing, meanwhile, because water conservancy diversion support plate 43 has certain angle of inclination along air flow direction, thus water conservancy diversion support plate 43 also has certain guide functions to air-flow, thus air-flow forms large swirling flow in the heat exchanger channels 151 be made up of anti-icing surperficial 152 and nacelle front face 153.From the front of deicer, swirling flow is advanced, until be expelled in external environment condition or intake duct 150 by means of exhaust duct 30 via fracture 24 at heat exchanger channels 151 internal spiral.When hot air flows in heat exchanger channels 151, heat is passed to covering 170 by it, the anti-icing temperature of surperficial 151 of intake duct leading edge is reached and guarantees surperficial non-icing numerical value.
Technology contents of the present invention and technical characterstic have disclosed as above; but be appreciated that; under creative ideas of the present invention; those skilled in the art can make various changes said structure and material and improve; comprise the combination of disclosure or claimed technical characteristics separately here, comprise other combination of these features significantly.These distortion and/or combination all fall in technical field involved in the present invention, and fall into the protection domain of the claims in the present invention.It should be noted that by convention, in claim, use discrete component to be intended to comprise one or more such element.In addition, any reference mark in claims should be configured to limit the scope of the invention.
Claims (16)
1. hot-air anti-icer for engine inlet, comprising:
Bleed pipeline, it extends for receiving the hot air from engine compressor along described intake duct;
Circulating line, it has the air flow inlet be connected with described bleed pipeline;
Exhaust duct, its one end is communicated with external environment or described intake duct and is used for hot air complete for heat exchange to discharge in heat exchanger channels;
It is characterized in that, described circulating line also has and to be connected with intake duct leading edge heat exchanger channels and to be close to the ring jet throat on anti-icing surface in it, to be extended by described ring jet throat side and with the lip of a described anti-icing spaced intended distance and be formed at the fracture that described circulating line is arranged with described air flow inlet radial symmetric;
The other end of described exhaust duct is communicated with described heat exchanger channels via the described fracture of described circulating line;
Multiple support, its nacelle front face being installed on described intake duct is used for supporting described circulating line;
Multiple guide-ring, on its described lip being installed on described circulating line and between described lip and described anti-icing surface.
2. hot-air anti-icer for engine inlet according to claim 1, is characterized in that, described multiple guide-ring is arranged relative to the inclined of described intake duct.
3. hot-air anti-icer for engine inlet according to claim 2, is characterized in that, described multiple guide-ring becomes 10 ° ~ 80 ° to be obliquely installed relative to the radial direction of described intake duct.
4. hot-air anti-icer for engine inlet according to claim 3, is characterized in that, the circumferential distance between two adjacent described guide-rings is 1mm ~ 10mm.
5. hot-air anti-icer for engine inlet according to claim 4, is characterized in that, described lip and described anti-icing spaced described intended distance are 2mm to 40mm.
6. hot-air anti-icer for engine inlet according to claim 5, is characterized in that, described multiple guide-ring is uniformly distributed circumferentially on the circulating line between described air flow inlet and described fracture.
7. hot-air anti-icer for engine inlet according to claim 6, is characterized in that, described multiple guide-ring is symmetrical about face in described air flow inlet and described fracture.
8. hot-air anti-icer for engine inlet according to claim 7, is characterized in that, two the fracture ends being positioned at described incision position of described circulating line are cecums.
9. according to the arbitrary described hot-air anti-icer for engine inlet of claim 1 to 8, it is characterized in that, described circulating line is provided with slide block towards the side of described support, and described support is formed with chute, described slide block in described chute circumference slidably.
10. hot-air anti-icer for engine inlet according to claim 9, is characterized in that, described slide block is symmetrical about face in described air flow inlet and described fracture.
11. hot-air anti-icer for engine inlet according to claim 10, is characterized in that, little relative to the spacing of two of other positions adjacent described supports in the spacing of described air flow inlet described support adjacent with two near described fracture.
12. hot-air anti-icer for engine inlet according to claim 11, is characterized in that, described support comprises and is fixed to bearing on described nacelle front face and is formed with the water conservancy diversion support plate of described chute by described seat supports.
13. hot-air anti-icer for engine inlet according to claim 12, is characterized in that, described water conservancy diversion support plate is arranged relative to the inclined of described intake duct, and its true dip direction is along the flow direction of air-flow in described heat exchanger channels.
14. hot-air anti-icer for engine inlet according to claim 13, is characterized in that, described water conservancy diversion support plate becomes 10 ° ~ 80 ° to be obliquely installed relative to the radial direction of described intake duct.
15. hot-air anti-icer for engine inlet according to claim 14, is characterized in that, described bleed pipeline Surface coating has insulation material layer.
16. hot-air anti-icer for engine inlet according to claim 15, it is characterized in that, be provided with hot gas away from one end of described circulating line in described bleed pipeline and control valve so that control the hot gas amount of valve control from engine compressor by described hot gas.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201110447988.2A CN103184935B (en) | 2011-12-28 | 2011-12-28 | Hot-air anti-icer for engine inlet |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110447988.2A CN103184935B (en) | 2011-12-28 | 2011-12-28 | Hot-air anti-icer for engine inlet |
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| CN103184935A CN103184935A (en) | 2013-07-03 |
| CN103184935B true CN103184935B (en) | 2015-06-10 |
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| CN104929778B (en) * | 2014-03-18 | 2017-08-25 | 中国航发商用航空发动机有限责任公司 | Engine inlets anti-icing system |
| CN105508054B (en) * | 2014-09-23 | 2018-12-07 | 中国航发商用航空发动机有限责任公司 | A kind of engine inlets anti-icing system and aero-engine |
| US10167085B2 (en) | 2016-01-27 | 2019-01-01 | General Electric Company | Nozzle and vane system for nacelle anti-icing |
| CN105699044B (en) * | 2016-04-20 | 2019-03-26 | 上海交通大学 | The icing mnncl tcst device of aero-engine air intake duct supporting plate |
| CN106650081B (en) * | 2016-12-19 | 2019-08-27 | 北京航空航天大学 | Impact-hot gas film combined type ice prevention structure design method |
| CN109131902B (en) * | 2018-09-21 | 2022-05-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft intake duct lip structure |
| CN113027611A (en) * | 2019-12-24 | 2021-06-25 | 中国航发商用航空发动机有限责任公司 | Split ring anti-icing system and aeroengine |
| CN112455693A (en) * | 2020-12-02 | 2021-03-09 | 唐建平 | Air interchanger for aerospace |
| CN113123874B (en) * | 2021-04-09 | 2022-02-15 | 滁州市翼腾精密制造有限公司 | Small-sized aviation starter air inlet shell and machining process thereof |
| CN113530888B (en) * | 2021-08-24 | 2022-08-09 | 中国航发湖南动力机械研究所 | Multi-cavity integrated guide vane casing structure with anti-icing function |
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| CN103184935A (en) | 2013-07-03 |
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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. |
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