CN105971768B - A kind of supercharging supply system certainly based on re-generatively cooled - Google Patents
A kind of supercharging supply system certainly based on re-generatively cooled Download PDFInfo
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- CN105971768B CN105971768B CN201610402329.XA CN201610402329A CN105971768B CN 105971768 B CN105971768 B CN 105971768B CN 201610402329 A CN201610402329 A CN 201610402329A CN 105971768 B CN105971768 B CN 105971768B
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- Prior art keywords
- tank
- propellant
- pressure
- cooling duct
- valve
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/50—Feeding propellants using pressurised fluid to pressurise the propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
Abstract
The invention belongs to Space Vehicle System technical field, the liquid propelling system or hybrid propulsion system using high saturated vapor pressure propellant are mainly used in.In order to solve from the problem of propellant temperature reduction, pressure decline serious in tank in the supercharging supply system course of work, the invention provides it is a kind of based on re-generatively cooled from Pressurization scheme, be made up of safety valve, tank, charging line, fill valve, check valve, cooling duct, liquid collecting cavity, main supply line, coolant line, incendiary agent pipeline, main valve, pressure piping etc..Propellant obtains heat while combustion chamber locular wall is cooled down, and the propellant after heat exchange gasification returns to tank and is pressurized to propellant.The present invention can keep tank pressure basicly stable in tank before liquid propellant emptying, so as to ensure that thrust is basicly stable.
Description
Technical field
It is more particularly to a kind of to be from supercharging supply based on re-generatively cooled the invention belongs to Space radiation technical field
System.
Background technology
The chemical rocket propulsion system used at present has：Liquid propelling system, solid propellant propulsion system, gas propulsive system and
Solid-liquid mixed propulsion system.In above-mentioned all kinds of propulsion systems, liquid propelling system, solid-liquid propulsion system and gas propulsive system
System is required for propellant booster transportation apparatus, and this kind of supercharging device is divided into pump pressure type and the major class of squash type two again.Pump pressure type system
Major advantage be that propellant tank need not bear high pressure, can use lighter weight tank, but due to using turbine pump increase
System complexity and cost, are generally only used for high thrust, long-life Large Launch Vehicle.For aircraft auxiliary propulsion system
The less system of propellant mass such as system and Upper Stage Attitude and orbit control system, generally uses squash type propellant feed system.Extruding
Formula supply system is simple in construction, reliable, and constant pressure type is divided into again and falls pressure type two schemes, and the former passes through decompression by gas cylinder
Valve constant output, is tank supercharging, but the part such as pressurization gas and gas cylinder and pressure-reducing valve considerably increases the matter of system
Amount；The latter relies on the pressure duty of tank air cushion, and the requirement to tank pressure-bearing is higher, and its pressure will be reduced gradually, and thrust is defeated
Go out non-constant.
It is that one kind falls pressure type scheme from supercharging, it is squeezed liquid using the energy of saturated liquid in sealing container from container
Go out.Its implementation is as follows：Propellant from tank flow out when, the pressure in tank will be reduced, when pressure is full less than propellant
During with vapour pressure, in tank remaining liquid propellant will partial gasification, the steam of generation maintains the pressure in tank basic
It is constant.This supercharging mode need not set gas cylinder and pressure-reducing valve, existing gas cylinder-tank type pressure-feed system in addition
Advantage simple in construction, has that turbopump-feed system tank quality is small, the premium properties that chamber pressure is high concurrently again.Lot of experiments
The feasibility of this supercharging mode is demonstrated, but is also indicated that simultaneously, in the supercharging supply system course of work certainly, because air cushion is done
The temperature of propellant will be reduced in work(and liquid gasification, tank, and pressure declines serious so that supply system can not be with constant mass
Measure flow supply propellant.To solve this problem, simpler method is to carry out thermal compensation to propellant tank.Generally use
Electric heating is simple in construction, heating power can adjust, but have the disadvantage that needs consumption plays electric energy valuable on arrow/satellite and provided
Source.
The content of the invention
The purpose of the present invention is：Decline in tradition from pressure in the supercharging supply system course of work serious, it is impossible to maintain storage
In the case that case pressure is constant, propose that a kind of propellant is pressurized supply system certainly.The method that the system uses similar re-generatively cooled,
In combustion chamber, locular wall arranges cooling duct, allows propellant to be exchanged heat as coolant flow through cooling duct, in cooling combustion chamber
While wall, propellant obtains heat to be gasified, and vaporized propellant is sent back to tank, gives tank supercharging, reaches
The purpose for making tank pressure basicly stable.
The present invention " a kind of supercharging supply system certainly based on re-generatively cooled " is realized by following proposal：
The system include safety valve 1, tank 2, charging line 3, fill valve 4, check valve 5, cooling duct 6, liquid collecting cavity 7,
Main supply line 8, coolant line 8a, incendiary agent pipeline 8b, main valve 9, pressure piping 10, combustion chamber 11, propellant 12.
Safety valve 1 is arranged on tank 2, positioned at tank air cushion end.Charging line 3 is connected with tank 2, during filling, liquid
Propellant 12 enters tank through fill valve 4 by charging line 3.Main supply line 8 is connected with tank 2, is set on main supply line 8
Main valve 9.In the downstream of main valve 9, main 8 points of supply line is two branch roads of coolant line 8a and incendiary agent pipeline 8b, wherein cooling down
Agent pipeline 8a is connected with liquid collecting cavity 7, and check valve 5 is also provided with the branch road, and incendiary agent pipeline 8b is directly connected with combustion chamber 11.
Groove ribbed cooling duct 6 is arranged between the inside and outside wall of combustion chamber 11, and the arrival end of cooling duct 6 is connected with liquid collecting cavity 7, outlet
End is connected with the arrival end of pressure piping 10.Pressure piping 10 connects cooling duct 6 and tank 2, and its port of export is located at tank gas
Pad end.The air cushion end refers to that one end of gas is arranged at tank top.
It must be liquid as the propellant 12 of cooling agent, and require that it has higher saturated vapor pressure (high under normal temperature
In 1MPa, for example, N2Saturated vapor pressures of the O in 287.15K is 4.58MPa, and the saturated vapor pressure in 298.15K is about
5.38MPa), it is not easily decomposed under heating condition, there is preferable compatibility with cooling duct chamber wall materials.
The operation principle of cooling duct 6 is identical with common re-generatively cooled mode, by internal groove ribbed structure (inwall)
Constituted with external supporting structure (outer wall), inwall mills out rectangle using the higher Cu alloy material of thermal conductivity by machining
Conduit and fin flow for cooling agent；Outer wall uses stainless steel or high temperature alloy to bear the high temperature and high pressure in combustion chamber 11.
Sealed between external and internal compositionses using welding manner.
Before start-up operation, fill valve 4 is opened, liquid propellant is filled into tank 2 by charging line 3.Filling
After the completion of, the air cushion that certain volume is left in fill valve 4, tank 2 is closed, is reached after balance, air-cushion pressure is the full of propellant
And vapour pressure.
When engine is started working, open the liquid propellant in main valve 9, tank 2 and supplied under air cushion pressure effect from main
Pipeline 8 is answered to flow out, the pressure in tank 2 will be reduced, according to phase equilibrium relationship, a part of liquid will gasify in tank, to make up
Liquid propellant discharges vacated gaseous phase volume.With the continuation of work, air cushion volume increases, pressure and temperature in tank 2
Degree all will reduction.
The liquid propellant 12 flowed out by tank 2, is flowed through after main valve 9, and a part is directly entered combustion through incendiary agent pipeline 8b
Room 11 is burnt, combustion reaction is carried out and produces high-temperature fuel gas, so as to produce thrust.Another fraction flows through list through coolant line 8a
To valve 5, into liquid collecting cavity 7, it is assigned to by liquid collecting cavity 7 in the groove ribbed cooling duct 6 of the outer arrangement in combustion chamber 11.It is used as cooling
The partially liq propellant of agent absorbs the heat that combustion gas is transmitted by the inwall of combustion chamber 11, temperature rise in cooling duct 6
And gasify, while cooling combustion chamber locular wall.Propellant after gasification by cooling duct 6 flow out after through pressure piping 10 return to storage
In case 2, pressure compensation to tank 2 and thermal compensation are realized, so that the pressure of tank 2 substantially constant in the course of the work is maintained,
Until all emptyings, system stalls of the liquid propellant in tank 2.
Wherein safety valve 1 is opened when the pressure of tank 2 is higher than secure threshold, and discharge part gas is to ensure tank pressure
Will not be too high；When the pressure of tank 2 is less than secure threshold, safety valve 1 is remained turned-off.
Wherein check valve 5 prevents propellant reverse flow, it is ensured that the gas in cooling duct 6 is entered by pressure piping 10 to be store
Case 2.
The cooling duct 6, can be arranged in preceding combustion room, powder charge section, afterburner or the spray of solid-liquid hybrid rocket engine
One section in pipe or several sections, with arranged in series or can be arranged in parallel, and its arrangement side is specifically determined according to the demand of cooling and supercharging
Formula.The cooling duct 6 can be arranged in liquid propellant rocket also available for liquid prpellant rocket from being pressurized
One or more snippets in the combustion chamber of engine；With arranged in series or it can be arranged in parallel.
Certainly supercharging supply system of the present invention based on re-generatively cooled is mainly used in liquid propelling system or solid-liquid mixing is pushed away
Enter system, the advantage is that：
(1) pressurized gas cylinder and turbine pump is not needed just to be produced to propellant from supercharging supply system based on re-generatively cooled
Higher boost pressure, reduces the quality and complexity of supply system while certain boost performance is ensured；
(2) costs such as pressurized gas cylinder, pressure-reducing valve and turbine pump are not needed to hold high from supercharging supply system based on re-generatively cooled
Expensive part, reduces the cost of supply system；
(3) cooling to combustion chamber wall surface can be realized while supercharging from supercharging supply system based on re-generatively cooled,
Suitable for liquid propelling system；For solid-liquid mixed propulsion system, the heat-insulated of the costliness such as high silica need not be set in cooling section
Liner, it is cost-saved, it is ensured that safety.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the accompanying drawing used required in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, without having to pay creative labor, may be used also
To obtain other accompanying drawings according to these accompanying drawings.
From the schematic diagram of pressure charging system in Fig. 1 present invention；
The 3 dimensional drawing of Fig. 2 bracket groove ribbed of embodiment of the present invention cooling duct；
The curve map that tank pressure changes with the working time in Fig. 3 embodiment of the present invention.
Marginal data：
1- safety valves；2- tanks；3- charging lines；4- fill valves；5- check valves；6- cooling ducts；7- liquid collecting cavities；8- master
Supply line；8a- coolant lines；8b- incendiary agent pipelines；9- main valves；10- pressure pipings；11- combustion chambers；12- liquid is promoted
Agent；61- internal face of combustion chamber, 62- outer wall of combustion chamber face, 63- groove rib structures.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
The present invention " a kind of supercharging supply system certainly based on re-generatively cooled " includes：Safety valve 1, tank 2, charging line 3,
Fill valve 4, check valve 5, cooling duct 6, liquid collecting cavity 7, main supply line 8, coolant line 8a, incendiary agent pipeline 8b, main valve
9th, pressure piping 10, combustion chamber 11, propellant 12.
In the present embodiment, using nitrous oxide N2O is used as liquid propellant.
Before start-up operation, fill valve 4 is opened, liquid propellant is filled into tank 2 by charging line 3.Filling
After the completion of, the air cushion that certain volume is left in fill valve 4, tank 2 is closed, is reached after balance, air-cushion pressure is the full of propellant
And vapour pressure.When environment temperature is 287K, the pressure in tank is about 4.58MPa.
When engine is started working, open the liquid propellant in main valve 9, tank 2 and supplied under air cushion pressure effect from main
Pipeline 8 is answered to flow out, while a part of liquid in tank 2 will gasify, air cushion volume increase, pressure and temperature all decreases.
The liquid propellant 12 flowed out by tank 2, is flowed through after main valve 9, and a part enters combustion chamber through incendiary agent pipeline 8b
11, carry out combustion reaction and produce high-temperature fuel gas, so as to produce thrust.Another part flows through check valve 5 through coolant line 8a,
Into in liquid collecting cavity 7, it is assigned to by liquid collecting cavity 7 in the groove ribbed cooling duct 6 of the outer arrangement in combustion chamber 11.Its bracket groove ribbed is cooled down
The structure of passage 6 is as shown in Fig. 2 internal face uses zirconium copper product, and outside wall surface uses 30CrMnSi materials.
As shown in figure 3, transverse axis represents the time, the longitudinal axis represents tank pressure, and solid line is represented when the re-generatively cooled for having 4.1% goes out
Mouthful flow be used as from pressurization gas when, the curve that pressure is changed over time in tank；When dotted line indicates no re-generatively cooled system, storage
The curve that pressure is changed over time in case.It can be seen that, the pressure in tank in the present invention was in 0~about 3500 second period, base
This holding is stable.Its principle is：Liquid propellant absorbs the heat of combustion gas transmission in cooling duct 6, and temperature is raised and gasified,
Combustion chamber locular wall is cooled down simultaneously.After propellant after gasification is flowed out by cooling duct 6, returned to through pressure piping 10 in tank 2, it is real
The now pressure compensation to tank 2 and thermal compensation, so as to maintain the pressure in tank 2 constant in the course of the work, is always held at
4.5MPa or so, until the liquid propellant emptying in tank 2, system stalls.And during without re-generatively cooled system, in tank
Pressure drastically declines, substantially without stable section.
If in the course of work, the pressure of tank 2 is higher than secure threshold, and safety valve 1 will be opened, and discharge part gas is with true
Protecting tank pressure will not be too high；When the pressure of tank 2 is less than safety value, safety valve 1 is remained turned-off.The wherein anti-thrust of check valve 5
Enter agent reverse flow, it is ensured that the gas in cooling duct 6 enters tank 2 by pressure piping 10
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the protection domain of claims as
It is accurate.
Claims (5)
1. a kind of supercharging supply system certainly based on re-generatively cooled, it is characterized in that：It includes safety valve (1), tank (2), added
Note pipeline (3), fill valve (4), check valve (5), cooling duct (6), liquid collecting cavity (7), main supply line (8), coolant line
(8a), incendiary agent pipeline (8b), main valve (9), pressure piping (10), combustion chamber (11), propellant (12)；
The safety valve (1) is arranged on the air cushion end of tank (2), and charging line (3) is connected with tank (2), and fill valve (4) is installed
On charging line (3)；Main supply line (8) connects with tank (2)；Main valve (9) is set on main supply line (8)；In main valve
(9) downstream, main supply line (8) is divided into two branch roads of coolant line (8a) and incendiary agent pipeline (8b), wherein coolant hose
Road (8a) is connected with liquid collecting cavity (7), and check valve (5) is also provided with the coolant line (8a)；Incendiary agent pipeline (8b) is straight
Connect and connected with combustion chamber (11)；The cooling duct (6) is groove rib structure, and it is inside and outside that cooling duct (6) are arranged on combustion chamber (11)
Between wall, the arrival end of cooling duct (6) is connected with liquid collecting cavity (7), and the port of export is connected with the arrival end of pressure piping (10)；Increase
Pressure pipe road (10) connects cooling duct (6) and tank (2), and its port of export is located at the air cushion end of tank (2).
2. the supercharging supply system according to claim 1 certainly based on re-generatively cooled, it is characterized in that：The propellant (12)
It is higher than 1MPa liquid propellant using saturated vapor pressure under normal temperature.
3. the supercharging supply system according to claim 1 certainly based on re-generatively cooled, it is characterized in that：The cooling duct
(6) it is made up of inner and outer wall, the side of inwall towards outer wall is milled with rectangular duct and fin；Inwall is higher using thermal conductivity
Cu alloy material, outer wall uses stainless steel or high temperature alloy；Sealed between inside and outside wall using welding manner.
4. the supercharging supply system according to claim 1 certainly based on re-generatively cooled, it is characterized in that：The cooling duct
(6) one or more snippets in the preceding combustion room of solid-liquid hybrid rocket engine, afterburner, powder charge section or jet pipe can be arranged in；Can
With arranged in series or it is arranged in parallel.
5. the supercharging supply system according to claim 1 certainly based on re-generatively cooled, it is characterized in that：The cooling duct
(6) one or more snippets in the combustion chamber of liquid prpellant rocket can be arranged in；Can be with arranged in series or cloth in parallel
Put.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610402329.XA CN105971768B (en) | 2016-06-10 | 2016-06-10 | A kind of supercharging supply system certainly based on re-generatively cooled |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610402329.XA CN105971768B (en) | 2016-06-10 | 2016-06-10 | A kind of supercharging supply system certainly based on re-generatively cooled |
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| CN105971768A CN105971768A (en) | 2016-09-28 |
| CN105971768B true CN105971768B (en) | 2017-09-15 |
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| CN106567791B (en) * | 2016-11-08 | 2018-04-06 | 上海宇航系统工程研究所 | A kind of forced circulation chilldown system |
| CN108019296B (en) * | 2017-12-07 | 2020-03-24 | 上海新力动力设备研究所 | Nitrous oxide decomposes from turbocharging system |
| CN108119260B (en) * | 2018-01-23 | 2023-12-05 | 陕西蓝箭航天技术有限公司 | Liquid engine and carrier |
| CN108590888A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system |
| CN108590887A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system based on steam cooling screen |
| CN108826018B (en) * | 2018-07-19 | 2024-03-26 | 北京航天动力研究所 | Microminiature pressurization system and pressurization method based on liquefied gas |
| CN109779787A (en) * | 2018-12-28 | 2019-05-21 | 中国运载火箭技术研究院 | Reuse aircraft liquid methane circulating precooling system |
| CN109737829B (en) * | 2019-01-31 | 2024-03-26 | 蓝箭航天空间科技股份有限公司 | Rocket liquid storage tank propellant conveying system and carrier rocket |
| CN109826725A (en) * | 2019-02-19 | 2019-05-31 | 北京星际荣耀空间科技有限公司 | Power mechanism, propulsion system and the liquid rocket system of propulsion system |
| CN110030115A (en) * | 2019-03-27 | 2019-07-19 | 上海宇航系统工程研究所 | A kind of propellant tank combination pressure charging system |
| CN110131073B (en) * | 2019-05-06 | 2022-02-18 | 上海空间推进研究所 | Space propulsion system suitable for filling of large-capacity storage tank |
| CN110700966A (en) * | 2019-09-18 | 2020-01-17 | 北京星际荣耀空间科技有限公司 | Rocket engine heat exchanger and aerospace vehicle |
| CN111042950A (en) * | 2019-12-31 | 2020-04-21 | 西北工业大学 | Motor pump auxiliary speed regulation type turbine pump supply system |
| CN112160848A (en) * | 2020-09-29 | 2021-01-01 | 西北工业大学 | Self-supercharging solid-liquid mixed engine |
| CN112196695A (en) * | 2020-10-19 | 2021-01-08 | 北京天兵科技有限公司 | Self-generated pressurization system and pressurization method for liquid rocket engine |
| CN113386981B (en) * | 2021-06-07 | 2022-09-27 | 上海空间推进研究所 | Corrugated conical column diaphragm storage tank |
| CN113565652B (en) * | 2021-07-27 | 2022-08-19 | 中国人民解放军国防科技大学 | Multilayer fixed high-temperature fluid channel |
| CN114320667B (en) * | 2021-09-16 | 2023-06-20 | 西北工业大学 | Extrusion type oxidant supply solid-liquid mixed engine |
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| JPS58217605A (en) * | 1982-06-08 | 1983-12-17 | Natl Aerospace Lab | Manufacture of combustor for rocket |
| FR2877403B1 (en) * | 2004-11-02 | 2009-10-16 | Eads Space Transportation Sa | DEVICE FOR SUPPLYING A FUEL ENGINE WITH FUEL AND FUEL |
| US7784269B1 (en) * | 2006-08-25 | 2010-08-31 | Xcor Aerospace | System and method for cooling rocket engines |
| WO2010068636A2 (en) * | 2008-12-08 | 2010-06-17 | Firestar Engineering, Llc | Regeneratively cooled porous media jacket |
| WO2013033437A2 (en) * | 2011-08-30 | 2013-03-07 | Firestar Engineering, Llc | Thermal phase separation |
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