CN109357287A - Segmented rocket engine combustion chamber and power drive unit - Google Patents
Segmented rocket engine combustion chamber and power drive unit Download PDFInfo
- Publication number
- CN109357287A CN109357287A CN201811391210.2A CN201811391210A CN109357287A CN 109357287 A CN109357287 A CN 109357287A CN 201811391210 A CN201811391210 A CN 201811391210A CN 109357287 A CN109357287 A CN 109357287A
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- Prior art keywords
- pipe
- water
- liquid oxygen
- combustion chamber
- fuel
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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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
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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
- F02K9/52—Injectors
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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
- F02K9/56—Control
- F02K9/563—Control of propellant feed pumps
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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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The invention discloses a kind of segmented rocket engine combustion chambers, including sequentially connected ejector filler, burner inner liner, high speed jet pipe；The side of the ejector filler is equipped with fuel inlet pipe, water injection pipe, liquid oxygen inlet tube, and the other side is equipped with fuel nozzle, water spray pipe, liquid oxygen jet pipe in alignment burner inner liner；The burner inner liner includes at least two cylinders that divide for capableing of dismantling connection, and the high speed jet pipe includes at least two capableing of being in charge of for dismantling connection, and the present invention also provides the power drive units using the combustion chamber.Beneficial effects of the present invention: burner inner liner, high speed jet pipe are all made of segmented connection, are damaged, can targetedly be replaced if wherein dividing cylinder or being in charge of, whole rent equipment that no replacement is required reduces costs.
Description
Technical field
The present invention relates to a kind of power drive device and using the device more particularly to a kind of rocket of the driving equipment
Engine chamber and power drive unit.
Background technique
Since combustion chamber flame temperature is high, partial destruction will be replaced existing liquid-propellant rocket engine thrust device
Package unit, at high cost, the cooling of the cooling tube wall of liquid fuel is limited, and combustion chamber and nozzle structure are difficult to bear its high temperature, can
Shorter by operating time, reusable rate is low.
Such as, application No. is 201810005871.0 patents, disclose a kind of cooling structure of aeroengine combustor buring room,
It is characterised in that it includes barrel, the barrel offer multiple film cooling holes and it is multiple join mixed hole, the film cooling holes with
It is described to join mixed hole interval setting, in the circumferential direction of the barrel, the outer wall in the section of the inner wall of the barrel and the barrel
The section in face is wavy, and the film cooling holes and described join mix Kong Jun through the inner wall and the outside wall surface.It should
Application is mixed and burned indoor gas, realizes the purpose of cooling, but air-cooled effect using film cooling holes are introduced a gas into
Fruit is unsatisfactory, still can there is the case where partial destruction will replace package unit.
Furthermore the existing higher generating set of efficiency is mostly Gas Turbine Generating Units, and Gas Turbine Generating Units are whole
Structure is complicated, and gas turbine is made of compressor, combustion chamber and turbine, and turbine is main acting component, and compressor part needs
Pressurization acting is carried out to air, a large amount of turbine function can be consumed, efficiency is relatively low, gas turbine application fuel oil or combustion gas etc. and sky
Gas carries out combustion reaction, and due to containing a large amount of nitrogen in air, combustion process is also easy to produce the pollution gas such as nitrogen oxides.
Summary of the invention
Technical problem to be solved by the present invention lies in providing, a kind of to solve recycling rate of waterused in above-mentioned background technique low
Segmented rocket engine combustion chamber and using the combustion chamber power drive unit.
The present invention is to solve above-mentioned technical problem by the following technical programs: segmented rocket engine burning of the present invention
Room, including sequentially connected ejector filler, burner inner liner, high speed jet pipe；The side of the ejector filler is equipped with fuel inlet pipe, water filling
Pipe, liquid oxygen inlet tube, the other side are equipped with fuel nozzle, water spray pipe, liquid oxygen jet pipe in alignment burner inner liner；The burner inner liner includes
At least two are capable of the cylinder that divides of dismantling connection, and the first water inlet pipe is equipped on described point of cylinder, and the high speed jet pipe includes at least two
It is a to be capable of being in charge of for dismantling connection, it is described be in charge of be equipped with the second water inlet pipe.
Preferably, the ejector filler includes three fuel beds stacked together, water filling layer, liquid oxygen layer, fuel bed, water filling
Layer, liquid oxygen layer inside be cavity, the cavity side of fuel bed is arranged in fuel inlet pipe, and the other side is equipped with fuel nozzle,
The side of the cavity of water filling layer is arranged in water injection pipe, and the other side is equipped with water spray pipe, and the cavity of liquid oxygen layer is arranged in liquid oxygen inlet tube
Side, the other side be equipped with liquid oxygen jet pipe.
Preferably, the burner inner liner is straight pipe type structure, uses flanged joint between adjacent point of cylinder, each divides equal on cylinder
Equipped with the first water inlet pipe.
Preferably, described point of cylinder includes outer wall, inner wall, and water storage chamber is constituted between outer wall and inner wall, and the first water inlet pipe is set
On the outer wall, inner wall is equipped with air film hole, and outer wall is that two semicircular structures dock.
Preferably, the high speed jet pipe is variable diameters tubular structure, it is adjacent be in charge of between using flanged joint, each point
Pipe is equipped with the second water inlet pipe.
Preferably, described to be in charge of including outer layer, internal layer, water storage chamber is constituted between outer layer and internal layer, the second water inlet pipe is set
It sets on outer layer, internal layer is equipped with air film hole, and outer layer is docked by the structure of two mirror images.
Preferably, the diameter of the air film hole is less than or equal to 1mm.
It preferably, further include the turbine for being mounted on high speed jet pipe tail portion, turbine head is equipped with fiaring cone, and turbine tail portion is successively
Connect speed reducer, high-speed motor.
Preferably, further include heat exchanger, be connected to turbine tail portion, the fuel inlet pipe, water injection pipe, liquid oxygen inlet tube warp
Cross heat exchanger.
The present invention also provides a kind of power drive unit using the segmented rocket engine combustion chamber, power drives
Device includes shell, rocket chamber, controller, fuel transfer pump group assembly, liquid oxygen conveying pump group assembly, water conveying
Pump group assembly, the tail end of rocket chamber's setting inside housings, fuel transfer pump group assembly, liquid oxygen conveying pump group are total
It is arranged successively middle section inside housings at, water conveying pump group assembly, and passes through fuel inlet pipe, liquid oxygen inlet tube, water respectively
Inlet tube is connected with burner, and control cabinet is arranged in head end, and conveys pump group assembly, water with fuel transfer pump group assembly, liquid oxygen
It is automatically controlled connected to convey pump group assembly.
The present invention has the advantage that compared with prior art
(1) burner inner liner in the present invention, high speed jet pipe are all made of segmented connection, since flame direction temperature point is prolonged in inside
Cloth is different, and the tube wall that can will be burnt according to Temperature Distribution is divided into high-temperature region and secondary high-temperature region, and the high-temperature region outer tube wall service life is smaller, thus
The burner nozzle of this high-temperature region is only needed to change after the arrival service life, the replacement cost from maintenance maintenance angle combustion chamber is lower, repeats
Utilization rate is high；
(2) and on each section it is equipped with the pipe into cooling water, is conducive to being uniformly distributed for outer wall cooling water pressure, Neng Goufen
The temperature of the adjusting of the segmentation engine chamber, good cooling results；
(3) the cooling water of the water and tube wall of burning zone injection becomes superheated steam, steam and burning under high temperature action
It reacts the water generated and carbon dioxide collectively forms combustion gas, wherein vapor accounts for the overwhelming majority, the meeting after convergent-divergent nozzle
It is sprayed with supersonic speed, forms high speed, high temperature and high-pressure gas, can do work to turbine section, turbine wheel shaft drives motor shaft, thus will
Mechanical energy is converted into electric energy；
(4) natural gas and oxygen can be become gas from liquid using waste heat by exchanging air by the high-temperature tail gas that turbine comes out
State, water also become high-temperature water, improve the heat utilization efficiency of entire combustion chamber.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of segmented rocket engine of embodiment of the present invention combustion chamber；
Fig. 2 is the structural schematic diagram of ejector filler in the embodiment of the present invention；
Fig. 3 is the perspective view of the explosion of segmented rocket engine of embodiment of the present invention combustion chamber；
Fig. 4 is power drive unit structural schematic diagram.
Figure label: ejector filler 1, fuel bed 11, fuel inlet pipe 111, fuel nozzle 112, water filling layer 12, water injection pipe
121, water spray pipe 122, liquid oxygen layer 13, liquid oxygen inlet tube 131, liquid oxygen jet pipe 132, working medium pump 14,
Burner inner liner 2 divides cylinder 21, outer wall 211, inner wall 212, the first water inlet pipe 2111, and air film hole 2121, divides high speed jet pipe 3
Pipe 31, outer layer 311, internal layer 312, the second water inlet pipe 3111,
Turbine 4, fiaring cone 41, high-speed motor 42, heat exchanger 43.
Shell 5, controller 6, fuel transfer pump group assembly 6, fuel tank 61, first pump the 62, first battery 63, liquid oxygen conveying
Pump group assembly 7, liquid oxygen tank 71, second pump the 72, second battery 73, water conveying pump group assembly 8, water tank 81, third pump 82, third electricity
Pond 83.
Specific embodiment
It elaborates below to the embodiment of the present invention, the present embodiment carries out under the premise of the technical scheme of the present invention
Implement, the detailed implementation method and specific operation process are given, but protection scope of the present invention is not limited to following implementation
Example.
As shown in Figure 1, the present embodiment segmented rocket engine combustion chamber includes sequentially connected in conjunction with shown in Fig. 2,3
Ejector filler 1, burner inner liner 2, high speed jet pipe 3, the side of the ejector filler 1 are equipped with fuel inlet pipe 111, water injection pipe 121, liquid oxygen and enter
Mouth pipe 131, the other side are equipped with fuel nozzle 112, water spray pipe 122, liquid oxygen jet pipe 132 in alignment burner inner liner 2；The burner inner liner
2 include at least two be capable of dismantling connection divide cylinder 21, the high speed jet pipe 3 includes at least two capableing of being in charge of for dismantling connection
31。
Burner inner liner 2, high speed jet pipe 3 in the present invention are all made of segmented connection, if needing to change, without discarded entire dress
It sets, only needs to change dividing cylinder 21 or being in charge of 31 for damage, reduce costs.
As shown in Fig. 2, the ejector filler 1 includes three fuel beds 11 stacked together, fills the water layer 12, liquid oxygen layer 13,
Fuel bed 11, water filling layer 12, liquid oxygen layer 13 inside be cavity, the cavity one of fuel bed 11 is arranged in 111 pipe of fuel inlet
Side, the other side are equipped with fuel nozzle 112, and the side of the cavity of water filling layer 12 is arranged in water injection pipe 121, and the other side is equipped with water spray pipe
122, the side of the cavity of liquid oxygen layer 13 is arranged in liquid oxygen inlet tube 131, and the other side is equipped with liquid oxygen jet pipe 132.Specifically, as schemed
In by from left to right, first interlayer is spray liquefied natural gas (LNG), and second interlayer is spray water, and third interlayer is to spray
Fluid injection oxygen, each interlayer is the jet pipe of different bores, and every layer of water cavity can avoid other layers of jet pipe, all jet pipes pair
Inside quasi- burner inner liner 2.
As shown in figure 3, the burner inner liner 2 is straight pipe type structure, flanged joint is used between adjacent point of cylinder 21, each point
Cylinder 21 includes outer wall 211, inner wall 212, and water storage chamber is constituted between outer wall 211 and inner wall 212, and the is equipped on described point of cylinder 21
One water inlet pipe 2111, specifically, the first water inlet pipe 2111 is arranged on outer wall 211, the first water inlet pipe 2111 is equipped with pressure tune
Valve is saved, water inlet can be adjusted according to chamber temperature.Inner wall is equipped with air film hole 2121, wherein each dividing the outer of cylinder 21
Wall is that two semicircular structures dock.Herein, by taking two points of cylinders 21 as an example.
As shown in figure 3, the high speed jet pipe 3 is variable diameters tubular structure, it is adjacent to be in charge of between 31 using flanged joint, often
One be in charge of 31 include outer layer 311, internal layer 312, between outer layer and internal layer constitute water storage chamber, it is described be in charge of be equipped with second
Water inlet pipe 3111, specifically, the second water inlet pipe 3111 is arranged on outer layer, the second water inlet pipe 3111 is equipped with pressure-regulating valve,
Water inlet can be adjusted according to chamber temperature, internal layer 312 is equipped with air film hole 2121, wherein being each in charge of 31 outer layer
It is that the structures of two mirror images is docked, because of the relationship that high speed jet pipe 3 is variable diameters, the form that each is in charge of 31 is different,
But structure composition is identical.High speed jet pipe 3 can be Laval nozzle herein, propelling nozzle etc., it can be achieved that High Mach number, combustion gas by
Subsonics state enters Supersonic, corresponding, and the supersonic turbines such as impact wheel can be used.Only display is connected with burner inner liner 2 in figure
One connect is in charge of 31.
The temperature of burner inner liner 2 and high speed jet pipe 3 using the adjusting of the segmented engine chamber, good cooling results.
It is equipped with igniter 22 inside the burner inner liner 2, is used for gas ignition.
The diameter of the air film hole 2121 is less than or equal to 1mm, and water or vapor can be by air film holes 2121 from inside and outside
The water storage chamber flowing in combustion chamber that wall or ectonexine are formed.
Fuel inlet pipe 111, water injection pipe 121, liquid oxygen inlet tube 131 are equipped with working medium pump 14 and pressure-regulating valve, can lead to
Excess pressure controls to adjust every section of water, the specific gravity of water and fuel can be adjusted according to exhaust gas component, so that sulphur and nitrogen in tail gas
The discharge amount of oxide is controlled within critical field.
As shown in Figure 1, further including the turbine 4 for being mounted on 3 tail portion of high speed jet pipe, 4 tail portion of turbine is sequentially connected speed reducer (figure
In be not shown), high-speed motor 42, speed reducer just uses in the prior art.4 head of turbine is also equipped with fiaring cone 41.Also wrap
Heat exchanger 43 is included, is connected to 4 tail portion of turbine, the fuel inlet pipe 111, water injection pipe 121, liquid oxygen inlet tube 131 are by heat exchange
Device 43, natural gas and water and liquid oxygen are entered by fuel inlet pipe 111, water injection pipe 121, liquid oxygen inlet tube 131, by heat exchanger 43,
Natural gas and liquid oxygen become gaseous state from liquid, and water becomes high-temperature water.
The course of work of the invention:
Temperature increases after liquefied natural gas, liquid oxygen and water pass through heat exchanger 43, and turbine tail gas becomes low temperature exhaust gas, natural gas
And oxygen becomes gaseous state from liquid, natural gas, oxygen and water are anti-by burn in the meeting of ejector filler 1 together spray to burner inner liner 2
It answers, another part water injects the burner inner liner 2 of segmented by the first water inlet pipe 2111 or/and the second water inlet pipe 3111 and high speed is sprayed
Pipe 3, every section of water are controlled by tube wall temperature by adjusting pressure-regulating valve.What burner inner liner 2 and high speed jet pipe 3 injected
Water and the water for dividing cylinder 21 and being in charge of on 31 for cooling become superheated steam under high temperature action, what steam and combustion reaction generated
Water and carbon dioxide collectively form combustion gas, and wherein vapor accounts for the overwhelming majority, can be sprayed after convergent-divergent nozzle with supersonic speed
Out, high speed, high temperature and high-pressure gas are formed, can be done work to 4 sections of turbine, 4 axis of turbine drives the motor shaft of high-speed motor 42, from
And electric energy is converted by mechanical energy.The high-temperature tail gas that turbine 4 comes out can be utilized waste heat by heat exchanger 43.
It joined high-speed motor 42, compressor eliminated compared with gas turbine, and access heat exchanger 43, increase backheat side
Formula makes full use of the thermal energy of high-temperature tail gas, improves system effectiveness.
Fuel is liquefied natural gas and liquid oxygen, and the blending burning with water improves flame holding, noise reduced, with pipe
The combination of wall sectional type water cooled mode further reduced flame temperature, to reduce by 2 wall of burner inner liner, high speed jet pipe 3 and turbine 4
Temperature, improve the service life of high-temperature component, combustion gas tail gas is mainly vapor and a small amount of carbon dioxide, nitrogenfree oxide
Equal pollution gas, energy conservation and environmental protection.
It is whole to use cell cube design method, there is very high maintainability, and be suitable for a variety of different operating condition occasions, fire
The water cooling sectional design of flame cylinder 2 and high speed jet pipe 3 further improves its maintainability.
In addition, water that burner inner liner 2 and high speed jet pipe 3 inject and divide cylinder 21 and be in charge of on 31 can be for cooling water it is pure
Net water, can also be sewage, have the function that handling complex component sewage participates in sewage in combustion process, utilizes burning
Sewage is gasified as superheated steam, and discharged into the atmosphere by the high temperature of generation, is circulated throughout so that water participates in natural water
Journey, and the Various Complex group branch in sewage participates in burning or in the form of molecule in discharge cause atmosphere, and is deposited to
Earth's surface.
The present invention also provides it is a kind of using be capable of handling complex component rocket engine burner power drive unit,
Power drive unit includes that shell 5, burner, controller 6, fuel transfer pump group assembly 7, liquid oxygen conveying pump group assembly 8, water are defeated
Send pump group assembly 9, combustion chamber is arranged in the tail end inside shell 5, fuel transfer pump group assembly 7, liquid oxygen conveying pump group assembly 8,
Water conveying pump group assembly 9 is arranged successively middle section inside housings, and passes through fuel inlet pipe 111, liquid oxygen inlet tube respectively
121, water inlet pipe 131 is connected with burner, and controller 6 is arranged in head end, and conveys with fuel transfer pump group assembly 7, liquid oxygen
Pump group assembly 8, water conveying pump group assembly 9 are automatically controlled connected, which is product, such as PLC controller in the prior art, it is intended to
Control the working condition of fuel transfer pump group assembly 7, liquid oxygen conveying pump group assembly 8, water conveying pump group assembly 9.
Fuel transfer pump group assembly 7 includes fuel tank 71, first be arranged on fuel inlet pipe 111 pump 72 and driving
First battery 73 of 72 operating of the first pump；Liquid oxygen conveys pump group assembly 8 and includes liquid oxygen tank 81, is arranged on liquid oxygen inlet tube 121
Second pump 82 and driving second pump 82 operating the second batteries 83；Water conveys pump group assembly 9 and includes water tank 91, is arranged in water
The third battery 93 of 92 operating of third pump 92 and driving third pump on inlet tube 131.
The power drive unit is mainly used for the power drive of power generation, ground offshore platform, naval vessel etc..
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (10)
1. segmented rocket engine combustion chamber, which is characterized in that including sequentially connected ejector filler, burner inner liner, high speed jet pipe；
The side of the ejector filler is equipped with fuel inlet pipe, water injection pipe, liquid oxygen inlet tube, and the other side is equipped with the fuel in alignment burner inner liner
Jet pipe, water spray pipe, liquid oxygen jet pipe；The burner inner liner includes at least two cylinders that divide for capableing of dismantling connection, the high speed jet pipe packet
It includes at least two and is capable of being in charge of for dismantling connection.
2. segmented rocket engine combustion chamber according to claim 1, which is characterized in that the ejector filler includes three
Fuel bed stacked together, water filling layer, liquid oxygen layer, fuel bed, water filling layer, liquid oxygen layer inside be cavity, fuel inlet
The cavity side of fuel bed is arranged in pipe, and the other side is equipped with fuel nozzle, and the side of the cavity of water filling layer is arranged in water injection pipe, separately
Side is equipped with water spray pipe, and the side of the cavity of liquid oxygen layer is arranged in liquid oxygen inlet tube, and the other side is equipped with liquid oxygen jet pipe.
3. segmented rocket engine combustion chamber according to claim 1, which is characterized in that the burner inner liner is straight pipe type
Structure uses flanged joint between adjacent point of cylinder, each, which divides on cylinder, is equipped with the first water inlet pipe.
4. segmented rocket engine combustion chamber according to claim 3, which is characterized in that described point of cylinder include outer wall,
Inner wall constitutes water storage chamber between outer wall and inner wall, the first water inlet pipe is located on the outer wall, and inner wall is equipped with air film hole, and outer wall is
Two semicircular structures dock.
5. segmented rocket engine combustion chamber according to claim 1, which is characterized in that the high speed jet pipe is to straighten
Diameter tubular structure, it is adjacent be in charge of between using flanged joint, each, which is in charge of, is equipped with the second water inlet pipe.
6. segmented rocket engine combustion chamber according to claim 5, which is characterized in that it is described be in charge of including outer layer,
Internal layer, between outer layer and internal layer constitute water storage chamber, the second water inlet pipe be arranged on outer layer, internal layer be equipped with air film hole, outer layer by
The structure of two mirror images is docked.
7. the segmented rocket engine combustion chamber according to claim 4 or 6, which is characterized in that the air film hole it is straight
Diameter is less than or equal to 1mm.
8. segmented rocket engine combustion chamber according to claim 1, which is characterized in that further include being mounted on high speed to spray
The turbine of pipe tail portion, turbine head are equipped with fiaring cone, and turbine tail portion is sequentially connected speed reducer, high-speed motor.
9. segmented rocket engine combustion chamber according to claim 8, further includes heat exchanger, it is connected to turbine tail portion,
The fuel inlet pipe, water injection pipe, liquid oxygen inlet tube pass through heat exchanger.
10. a kind of power drive unit using any segmented rocket engine combustion chamber the claims 1-9,
It is characterized in that, power drive unit includes that shell, rocket chamber, controller, fuel transfer pump group assembly, liquid oxygen are defeated
Pump group assembly, water conveying pump group assembly are sent, tail end inside housings is arranged in rocket chamber, and fuel transfer pump group is total
It is arranged successively middle section inside housings, and passes through fuel inlet respectively at, liquid oxygen conveying pump group assembly, water conveying pump group assembly
Pipe, liquid oxygen inlet tube, water inlet pipe are connected with burner, control cabinet be arranged in head end, and with fuel transfer pump group assembly, liquid oxygen
It is automatically controlled connected to convey pump group assembly, water conveying pump group assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811391210.2A CN109357287A (en) | 2018-11-21 | 2018-11-21 | Segmented rocket engine combustion chamber and power drive unit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811391210.2A CN109357287A (en) | 2018-11-21 | 2018-11-21 | Segmented rocket engine combustion chamber and power drive unit |
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| CN109357287A true CN109357287A (en) | 2019-02-19 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111271733A (en) * | 2020-03-02 | 2020-06-12 | 北京航空航天大学 | Combustion heater |
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| CN111271733B (en) * | 2020-03-02 | 2020-12-01 | 北京航空航天大学 | Combustion heater |
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