CN101468721A - Superheated vapour secondary diffusion and division system for cold screen - Google Patents
Superheated vapour secondary diffusion and division system for cold screen Download PDFInfo
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- CN101468721A CN101468721A CNA2007103046435A CN200710304643A CN101468721A CN 101468721 A CN101468721 A CN 101468721A CN A2007103046435 A CNA2007103046435 A CN A2007103046435A CN 200710304643 A CN200710304643 A CN 200710304643A CN 101468721 A CN101468721 A CN 101468721A
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Abstract
The invention relates to an overheated steam secondary diffusion and distribution mechanism of a spatial cold shielding phrase-variable refrigeration system, which is particularly suitable for control the discharge of overheated steam of a spatial cold shielding system and is an indispensable mechanism for a phrase-variable refrigeration system in a high-vacuum microgravity environment. The mechanism is an airflow diffusion discharge mechanism having main function of using a micro diffusion theory to realize vibration-free, noise-free, uniform and symmetric discharge of the overheated steam in the air space without influencing the flight path of a space vehicle. The mechanism is suitable to be used to solve a spatial discharge problem of overheated steam and residual gases in the space vehicle. According to the technical characteristics of cold steam discharge in an open spatial phrase-variable refrigeration process, a secondary diffusion and distribution device can be used to solve the technical problem caused by the flow discharge of low-temperature fluid in a pressure-variable, temperature-variable and flow-variable spatial dynamic refrigeration process, improve spatial phrase-variable refrigeration efficiency, and realize relatively stable spatial refrigeration, thereby reducing the influences on the flight path of the space vehicle.
Description
Technical field
The present invention relates to the superheated steam secondary diffusion diversion mechanism in a kind of space cold shielding harness freezing by change of state system, belong to refrigerating field.
Background technology
Because aircraft has complicated aerodynamic heat transfer operating mode in starting and stabilized flight process, so cryogen is in fierce phase transformation and heterogeneous flow regime and is attended by pressure and the acute variation of temperature in the cold screen, constantly produce a large amount of saturated steam and superheated steam, contain moist steam and superheated steam in the pressure and temperature varying process not section outwards a discharging cause the spaceflight perturbed problem simultaneously, disturbance meeting change of flight device flight path.The present invention is primarily aimed at the perturbed problem that the space gaseous emission causes, analyze the disturbing influence of different discharging modes to aircraft movements, research reduces the emission control structure of disturbing influence, the problems such as position, direction, discharging bore and optimum discharge structure that comprise discharge of steam finally solve the through engineering approaches application problem of space with cold-shield system.The secondary diffusion dividing technology helps cold each branch line of steam uniform distribution after the throttling, guarantee exit flow evenly, stable, the vertical discharge, thereby do not influence ballistic trajectory; Secondary diffusion for the filling or starting process in excess refrigerant further gasification swell refrigeration, further little diffusion and keep integral structure stability, the reasonable distribution of overall pressure to have vital function equally.
Summary of the invention
The present invention is according to the technical characterstic of cold discharge of steam in the freezing by change of state process of open type space, design secondary diffusion part flow arrangement, be used for solving the technical barrier that the cry-fluid flow discharging of the dynamic process of refrigerastion in space of transformation, alternating temperature, unsteady flow amount is brought, improve space freezing by change of state efficient, it is relatively stable to freeze in the implementation space, thereby reduces the influence to the aircraft trajectory.
Technical solution of the present invention:
Space cold shielding harness system overheat secondary steam diffusion dividing technology solution under the microgravity high vacuum environment, it is characterized in that: the space cold shielding harness system is made of secondary diffusion part flow system and annex thereof etc., wherein the secondary diffusion part flow system is by secondary diffusion admission line (2), secondary diffusion device (6), capillary porous medium (10) in the diffuser, secondary diffusion air discharge grille 8, secondary diffusion bleeder line (5) is formed, the annex that is associated with it has capillary aerated materials (1), the internal refrigeration storage agent (13) that capillary aerated materials (1) absorbs, capillary materials support (4), cold screen outer (7), cold screen internal layer (3), a diffusion chamber (12) etc., capillary materials support (4) is made up of conical support body (15) and inner horizontal annular arrangement dividing plate (14) etc. thereof, has airflow square hole (16) on the conical suface.
The position relation of secondary diffusion part flow system and annex outside in is followed successively by cold screen outer (7), secondary diffusion part flow system, capillary materials support (4), capillary aerated materials (1), cold screen internal layer (3), outer (7), the secondary diffusion part flow system (mainly comprising secondary diffusion admission line (2), secondary diffusion device (6), secondary diffusion bleeder line (5)) of wherein cold screen, capillary materials support (4), capillary materials fit tightly between (1), leave gas channel between capillary materials (1) and the cold screen internal layer.Secondary diffusion admission line (2)) is uniformly distributed on outer (7) inside face of cold screen and and closely pastes mutually with inside face, the entrance location of secondary diffusion admission line (2) is connected to bottom, a diffusion chamber (12) in the cold screen, and end links to each other with secondary diffusion device import (9).Secondary diffusion admission line (2) closely pastes mutually with capillary materials support (4) conical surface and bottom surface, closely paste mutually the bottom surface of secondary diffusion device (6) and capillary materials support (4), the bottom surface of secondary diffusion bleeder line (5) and capillary materials support (4) closely mutually subsides and with tangential relationship be connected with support (4) bottom surface rounded edge and along diffuser (6) radially equal circumference on average arrange.Capillary aerated materials (1) do annular cut apart the back layering be installed on the annular arrangement dividing plate (14) of capillary materials support (4).Diffuser center (8) is a round exit, is used for being connected of aircraft and propulsion system, is filled with the diffusion noise reduction in the diffuser with capillary porous medium (10).
Its mode of operation be the cold vapor stream after the throttling behind secondary diffusion admission line (2), continue to absorb cold screen surfaces (7) solar radiation heat so that evaporate overheated, by secondary diffusion admission line (2) cold screen outside face (7) solar heat is transmitted to the internal refrigeration storage agent (13) that capillary aerated materials (1) is absorbed simultaneously, the cold that internal refrigeration storage agent (13) heat absorption evaporation produces is again by capillary aerated materials (1), capillary materials stake body (4) and secondary diffusion admission line (2) thus outwards transmit that making conducts heat reaches balance, thereby it is constant that cold screen surfaces (7) temperature keeps.Stream-liquid two-phase flow after the throttling of refrigerant saturated steam produces superheated steam after the secondary diffusion admission line fully evaporates heat absorption, when superheated steam is flowed through capillary porous medium (10) in the diffuser (6) because capillary porous medium (10) thus stressedly cause that poroelasticity changes and cause superheated steam deceleration diffusion and noise reduction in diffuser (6), the diffusion rectification is after give vent to anger grid 9 and secondary diffusion bleeder line (5) evenly enter the space, thereby reduces the influence to the aircraft flight track.
The principle problem that scheme is related:
Cold steam behind throttling diffusion (diffusion is applicable to discharge process or the filling process when surpassing control presssure) or vapour-liquid two mutual reinforcements between through the secondary diffusion admission line further shunt, evaporation and overheated, the secondary diffusion admission line is equivalent to the evaporator after the throttling one time, can make full use of the cold after the throttling and cool off cold screen surfaces.Because cold screen surfaces is subjected to solar radiation, be superheated steam so diffusion induction tract and cold screen outside face direct contact more help directly absorbing the solar radiation thermal change in the cold steam of outlet low temperature.
The size of diffusion pipeline, quantity and arrangement mode are tentatively definite by the Heat transfer numerical simulation result, analog result must satisfy surface temperature distribution enough evenly and maximum temperature be that (size of saturated vapour pressure or superheated steam pressure is the critical size of the cold screen system of decision directly, so reduce the design pressure value that internal pressure can reduce cold screen system as much as possible for the over-heat inside vapor (steam) temperature twice that is no more than the pairing saturation temperature upper limit of saturated vapor pressure of corresponding refrigerant.)。According to the exit flow flow (by solar radiation intensity, environmental radiation intensity, the decision of parameters such as cold screen outside face absorptivity), the thickness of flow velocity and cold screen interlayer is (by the size of aircraft capacity of heat transmission in starting process and spaceflight process, the loading transitivity decision of refrigerant) three principal parameters are further determined the outlet pipeline size and the regularity of distribution, export pipeline size when utilization Field Flow Numerical Simulation result determines minimum cold vapor stream speed, pairing Peak Flow Rate is determined the size of export pipeline when being incompressible cold steam according to myopia promptly, quantity and distribution form.
Because air-flow exists vibration to reach problems such as aircraft trajectory disturbances in mobile or discharge process, so the mode of symmetry and multitube arranged side by side road (free area of each by path is as far as possible little) of pressing as much as possible during according to air-flow diffusion principle design pipeline designs, (size in cross section is gone back the size decision of fibrous root according to pipeline and internal pressure that diffuser bears, and the pressure that is born when the cross section increases can reduce as far as possible greatly by the exhaust side outlet in the design of bleeder line.) mode shunted behind the first diffusion carries out exhaust, and secondary diffusion bleeder line arrival end adopts fine and close grid to discharge mode, thereby reach the purpose of irrotationality uniform distribution and discharging.
When stream-liquid two-phase flow that the liquid flooding that causes owing to overheated boiling (open type refrigeration) in starting process produces or the stream-liquid two-phase flow that causes owing to subcooled boiling in the filling process of ground are flowed through secondary diffusion system 2, evaporation and overheated in pipeline (2), simultaneously the unnecessary liquid of vaporization flows into diffuser 7 and is absorbed continuing sweat cooling by capillary porous mediums (10) in the diffuser 7, thereby reaches effective utilization of cold.
Technical characterstic of the present invention:
The present invention is primarily aimed at the cold discharge of steam problem of space vehicle cold-shield system and the superheated steam secondary diffusion dividing technology that proposes, being characterized in satisfying gas-liquid two-phase behind the throttling diffusion has enough spaces to carry out sweat cooling and carries out interchange of heat with the external world, can make full use of the cold after the throttling and cool off cold screen surfaces, help exporting the cold vapor absorption solar radiation of low temperature and become superheated steam.The more important thing is that the secondary diffusion dividing technology can satisfy the purpose of uniform distribution behind the cold steam diffusion and discharging, reduce disturbing influence, reduce problems such as vibration that air-flow causes and noise space vehicle.
Description of drawings
Fig. 1 is the location diagram of superheated vapour secondary diffusion and division system and cold-shield system.
Fig. 2 is superheated vapour secondary diffusion and division system figure.
Fig. 3 is diffusion system and capillary materials stake body graph of a relation.
Fig. 4 is diffusion system and capillary materials graph of a relation.
Fig. 5 is that the outer inside face relation of diffusion system and cold screen is partly cutd open figure.
Fig. 6 is diffuser and bleeder line graph of a relation.
Fig. 7 is the diffuser cut-away view.
Fig. 8 imports and exports location diagram for diffuser.
Fig. 9 is the air discharge grille block diagram.
Comprise that 1-capillary materials, 2-secondary diffusion admission line, the cold screen internal layer of 3-, 4-capillary materials support, 5-secondary diffusion bleeder line, 6-diffuser and cold screen skin, 7-diffuser and cold screen skin (partly cuing open), 4-capillary materials support, 15-comprise ring, 11-diffuser air discharge grille, 9-diffuser admission port, the interior capillary materials of 10-diffuser, 9-diffuser intake, 12-exhausr port in conical support body, 14-horizontal circle annular dividing plate, 16-airflow square hole, the 8-diffuser.
The specific embodiment
As shown in Figure 1, it is secondary diffusion admission line (2) that a diffusion is shunted cold steam inflow evaporator pipeline, flow into secondary diffusion device (6) through abundant evaporation with overheated back, in secondary diffusion device (6), do little diffusion after air discharge grille exports (11), bleeder line (5) enters space environment.
As shown in Figure 3, capillary materials support (4) closely pastes mutually with secondary diffusion part flow system 2, through the fully evaporation and absorb solar power and heat is passed to capillary materials support (4) by pipeline after overheated in secondary diffusion admission line (2) of the cold steam after the throttling or vapour-liquid two-phase, capillary materials support (4) continues to pass to capillary materials (1) and the adsorbed liquid of capillary materials with the heat that transmits, thereby reaches effective transmission of heat.
As shown in Figure 4, secondary diffusion admission line (2) closely pastes mutually with capillary materials (1), can be directly passed to capillary materials (1) thereby the liquid refrigerant that is absorbed promotion sweat cooling effect by pipeline (2) absorbed heat.
As shown in Figure 5, secondary diffusion distribution pipeline (2) closely pastes mutually with the outer inside face of cold screen (7), cold steam in the pipeline (2) or gas-liquid two-phase can directly absorb solar radiation heat and then fully evaporation and overheated, cool off cold screen outside face (7) simultaneously, make outside face (7) temperature traverse more evenly rationally, thereby reach the further utilization of cold after the throttling.
As shown in Figure 6, (the vapour-liquid two-phase that produces owing to subcooled boiling in filling process can not fully be evaporated the liquid of following the vaporization of a large amount of ends or be formed high moisture-containing airflow, and the reduction owing to saturated vapor pressure in starting process makes liquid superheat and liquid flooding for cold steam or vapour-liquid two-phase.) enter and can continue to evaporate after the diffuser (6) and unlikelyly make liquid directly be discharged to the space and cause the loss of refrigerant cold, diffuser (6) to play to collect gasifying liquid not and then continue the effectiveness of evaporation.Aircraft steady state phase, superheated steam produce very big flow velocity when space drainage, by behind diffuser (6) diffusion cold steam evenly being discharged into the space by secondary diffusion distribution pipeline (5).
As shown in Figure 7, capillary porous medium (10) is housed in the diffuser (6), high velocity air enters diffuser (6) after enter bleeder line (5) through air discharge grille 9 again after the diffusion action of capillary porous medium (10), thus reach evenly, do not have make an uproar, do not have shake, no disturbance discharges.
Claims (1)
1, space cold shielding harness system overheat secondary steam diffusion dividing technology scheme, the secondary diffusion part flow system comprises that capillary porous medium 10 in the secondary diffusion admission line 2, secondary diffusion device 6, diffuser, secondary diffusion air discharge grille 8, secondary diffusion bleeder line 5 form, and the annex that is associated with it has internal refrigeration storage agent 13 that capillary aerated materials 1, capillary aerated materials 1 absorb, capillary materials support 4, cold screen skin 7, cold screen internal layer 3, a diffusion chamber 12; Capillary materials support 4 is made up of conical support body 15 and inner horizontal annular arrangement dividing plate 14 thereof, has airflow square hole 16 on the conical suface; It is characterized in that pass, secondary diffusion part flow system position is: outside in be followed successively by cold screen skin 7, secondary diffusion part flow system, capillary materials support 4, capillary aerated materials 1, cold screen internal layer 3, fit tightly between wherein cold screen skin 7, secondary diffusion admission line 2, secondary diffusion device 6, secondary diffusion bleeder line 5 and capillary materials support 4, the capillary materials 1, leave gas channel between capillary materials 1 and the cold screen internal layer; Secondary diffusion admission line 2 is uniformly distributed on outer 7 inside faces of cold screen and with inside face and closely pastes mutually, and the entrance location of secondary diffusion admission line 2 is connected to 12 bottoms, a diffusion chamber in the cold screen, and end links to each other with secondary diffusion device import 9; Secondary diffusion admission line 2 closely pastes mutually with capillary materials support 4 conical surfaces and bottom surface, closely paste mutually the bottom surface of secondary diffusion device 6 and capillary materials support 4, the bottom surface of secondary diffusion bleeder line 5 and capillary materials support 4 closely mutually subsides and with tangential relationship be connected with capillary materials support 4 bottom surface rounded edge and along diffuser 6 radially equal circumference on average arrange.Capillary aerated materials 1 do annular cut apart the back layering be installed on the annular arrangement dividing plate 14 of capillary materials support 4; Diffuser center 8 is a round exit, is used for being connected of aircraft and propulsion system, is filled with the diffusion noise reduction in the diffuser with capillary porous medium 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710304643 CN101468721B (en) | 2007-12-28 | 2007-12-28 | Superheated vapour secondary diffusion and division system for cold screen |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710304643 CN101468721B (en) | 2007-12-28 | 2007-12-28 | Superheated vapour secondary diffusion and division system for cold screen |
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| CN101468721A true CN101468721A (en) | 2009-07-01 |
| CN101468721B CN101468721B (en) | 2010-10-13 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101792025A (en) * | 2010-04-07 | 2010-08-04 | 北京交通大学 | Driving device suitable for space environment |
| CN101712382B (en) * | 2010-01-20 | 2014-07-30 | 张周卫 | Self-pressurization type space low-infrared radiation cold-shield system device |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1014022A1 (en) * | 1998-12-24 | 2000-06-28 | ABB Alstom Power (Schweiz) AG | Surface condenser |
| US6899861B2 (en) * | 2002-07-25 | 2005-05-31 | General Motors Corporation | Heat exchanger mechanization to transfer reformate energy to steam and air |
| CN201195595Y (en) * | 2007-12-28 | 2009-02-18 | 中国航天科技集团公司第五研究院第五一〇研究所 | Secondary expansion-press split stream mechanism of cold screen superheated steam |
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2007
- 2007-12-28 CN CN 200710304643 patent/CN101468721B/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101712382B (en) * | 2010-01-20 | 2014-07-30 | 张周卫 | Self-pressurization type space low-infrared radiation cold-shield system device |
| CN101792025A (en) * | 2010-04-07 | 2010-08-04 | 北京交通大学 | Driving device suitable for space environment |
| CN101792025B (en) * | 2010-04-07 | 2012-08-08 | 北京交通大学 | Driving device suitable for space environment |
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| CN101468721B (en) | 2010-10-13 |
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