CN109373351A - Straight pipe type rocket chamber and power drive unit - Google Patents
Straight pipe type rocket chamber and power drive unit Download PDFInfo
- Publication number
- CN109373351A CN109373351A CN201811391222.5A CN201811391222A CN109373351A CN 109373351 A CN109373351 A CN 109373351A CN 201811391222 A CN201811391222 A CN 201811391222A CN 109373351 A CN109373351 A CN 109373351A
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- Prior art keywords
- water
- liquid oxygen
- pipe
- fuel
- straight pipe
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Air Supply (AREA)
Abstract
The invention discloses a kind of straight pipe type rocket chambers, the burner inner liner including sequentially connected ejector filler, straight pipe type；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 include at least two be capable of dismantling connection divide cylinder, the present invention also provides the power drive units using the combustion chamber.Beneficial effects of the present invention: burner inner liner is all made of segmented connection, if wherein cylinder is divided to be damaged, can targetedly be replaced, 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
Straight pipe type rocket chamber and power drive unit.
The present invention is to solve above-mentioned technical problem by the following technical programs: the present invention discloses a kind of straight pipe type rocket hair
Motivation combustion chamber, the burner inner liner including sequentially connected ejector filler, straight pipe type；The side of the ejector filler is equipped with fuel inlet
Pipe, water injection 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 fire
Flame cylinder includes at least two cylinders that divide for capableing of dismantling connection, is equipped with the first water inlet pipe on described point of cylinder.
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, and flanged joint is used between adjacent point of cylinder, is all provided on described point of cylinder
There is the first water inlet pipe.
Preferably, described point of cylinder includes outer wall, inner wall, and water storage chamber, first water inlet are constituted between outer wall and inner wall
Pipe is arranged on the outer wall, and inner wall is equipped with air film hole.
Preferably, the outer wall is that two semicircular structures dock.
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 flame drum tail, turbine head is equipped with fiaring cone, and turbine tail portion successively connects
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.
Preferably, fuel inlet pipe, water injection pipe, liquid oxygen inlet tube, be equipped with working medium pump and pressure tune on the first water inlet pipe
Save valve.
The present invention also provides a kind of power drive unit using the straight pipe type rocket 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 is connected using segmented, can root since flame direction Temperature Distribution difference is prolonged in inside
Burning tube wall is divided into high-temperature region and secondary high-temperature region according to Temperature Distribution, the high-temperature region outer tube wall service life is smaller, thus after reaching the service life
The burner nozzle for only needing to change this high-temperature region, the replacement cost from maintenance maintenance angle combustion chamber is lower, high recycling rate；
(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 straight pipe type of embodiment of the present invention rocket 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 straight pipe type of embodiment of the present invention rocket chamber；
Fig. 4 is the structural schematic diagram of power drive unit.
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, air film hole 2121, turbine 3, fiaring cone
31, high-speed motor 32, heat exchanger 33,
Shell 4, controller 5, fuel transfer pump group assembly 6,62, first battery 63 of the pump of fuel tank 61, first, liquid oxygen are defeated
Send 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, the
Three batteries 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 straight pipe type rocket chamber includes sequentially connected in conjunction with shown in Fig. 2,3
The side of ejector filler 1, burner inner liner 2, the ejector filler 1 is equipped with fuel inlet pipe 111, water injection pipe 121, liquid oxygen inlet tube 131, separately
Side is 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 includes at least
Two be capable of dismantling connection divide cylinder 21.
Burner inner liner 2 in the present invention is connected using segmented, if needing to change, without discarded whole device, only needs to change damage
Bad divides cylinder 21, reduces 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, described point of cylinder are used between adjacent point of cylinder 21
On be equipped with the first water inlet pipe 2111, each divide cylinder 21 include outer wall 211, inner wall 212, water storage is constituted between outer wall and inner wall
Chamber, specifically, the first water inlet pipe 2111 is arranged on outer wall 211, the first water inlet pipe 2111 is equipped with pressure-regulating valve, can
The temperature of the adjusting of the segmented engine chamber, good cooling results, inner wall is equipped with air film hole 2121, wherein each dividing cylinder 21
Outer wall be that two semicircular structures dock.Herein, by taking two points of cylinders 21 as an example.
The temperature of the adjusting of 2 segmented of the burner inner liner 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 3 for being mounted on 2 tail portion of burner inner liner, 3 tail portion of turbine is sequentially connected speed reducer, high speed
Motor 32, speed reducer just use in the prior art.3 head of turbine may be provided with 31 (not shown) of fiaring cone.Also
Including heat exchanger 33, it is connected to 3 tail portion of turbine, the fuel inlet pipe 111, water injection pipe 121, liquid oxygen inlet tube 131 are by changing
Hot device 33, 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
33, natural gas and liquid oxygen become gaseous state from liquid, and water becomes high-temperature water.
The engine chamber of straight pipe type can be matched with subsonic turbine and transonic turbine, more efficient.
In addition, other purposes of this rocket engine other than power generation can be achieved in the use of non-straight tube, thrust is such as generated, is used
In ground and offshore platform, serve many purposes.
The course of work of the invention:
Temperature increases after liquefied natural gas, liquid oxygen and water pass through heat exchanger 33, 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, and every section of water is passed through by tube wall temperature
Pressure-regulating valve is adjusted to be controlled.The water and the water on cylinder 21 for cooling is divided to become under high temperature action that burner inner liner 2 injects
The water and carbon dioxide that superheated steam, steam and combustion reaction generate collectively form combustion gas, can do work to 3 sections of turbine, turbine 3
Axis drives the motor shaft of high-speed motor 32, to convert electric energy for mechanical energy.The high-temperature tail gas that turbine 3 comes out can pass through
Heat exchanger 33, waste heat is utilized.
It joined high-speed motor 32, the provinces and regions compressor compared with gas turbine, and access heat exchanger 33, 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 the temperature of 2 wall of burner inner liner and turbine 3, mention
The high service life of high-temperature component, combustion gas tail gas are mainly vapor and a small amount of carbon dioxide, the pollutions such as nitrogenfree oxide
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 further improves its maintainability.
In addition, water that burner inner liner 2 injects and dividing on cylinder 21 and can be pure water for cooling water, it can also be dirty
Water has the function that handle complex component sewage, sewage is participated in combustion process, the high temperature generated using burning will be dirty
Aqueous vapor turns to superheated steam, and discharges into the atmosphere, so that sewage participates in natural water cycle process, and in sewage
Various Complex group branch participates in burning or in the form of molecule in discharge cause atmosphere, and is deposited to earth's surface.
Furthermore turbine can also be installed in high speed jet pipe tail portion, turbine head is equipped with fiaring cone, and turbine tail portion is sequentially connected
Speed reducer, high-speed motor are used as generator and use.
As shown in figure 4, the present invention also provides a kind of using the rocket engine burner for being capable of handling complex component and dynamic
Force driving device, power drive unit include shell 4, burner, controller 5, fuel transfer pump group assembly 6, liquid oxygen delivery pump
Group assembly 7, water convey pump group assembly 8, and the tail end inside shell 4 is arranged in combustion chamber, and fuel transfer pump group assembly 6, liquid oxygen are defeated
Send pump group assembly 7, water conveying pump group assembly 8 to be arranged successively middle section inside housings, and respectively by fuel inlet pipe 111,
Liquid oxygen inlet tube 121, water inlet pipe 131 are connected with burner, controller 5 be arranged in head end, and with fuel transfer pump group assembly
6, liquid oxygen conveying pump group assembly 7, water conveying pump group assembly 8 are automatically controlled connected, which is product, such as PLC in the prior art
Controller, it is intended to control the working condition of fuel transfer pump group assembly 6, liquid oxygen conveying pump group assembly 7, water conveying pump group assembly 8.
Fuel transfer pump group assembly 6 includes fuel tank 61, first be arranged on fuel inlet pipe 111 pump 62 and drives
First battery 63 of dynamic first pump, 62 operating；Liquid oxygen conveys pump group assembly 7 and includes liquid oxygen tank 71, is arranged in liquid oxygen inlet tube 121
On second pump 72 and driving second pump 72 operating the second batteries 73；Water conveys pump group assembly 8 and exists including water tank 81, setting
The third battery 83 of 82 operating of third pump 82 and driving third pump on water inlet pipe 131.
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. straight pipe type rocket chamber, which is characterized in that the burner inner liner including sequentially connected ejector filler, straight pipe type；
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 include at least two be capable of dismantling connection divide cylinder.
2. straight pipe type rocket 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. straight pipe type rocket 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, is equipped with the first water inlet pipe on described point of cylinder.
4. straight pipe type rocket 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, on the outer wall, inner wall is equipped with air film hole for the first water inlet pipe setting.
5. straight pipe type rocket chamber according to claim 4, which is characterized in that the outer wall is two and half
Circular configuration docks.
6. straight pipe type rocket chamber according to claim 4, which is characterized in that the diameter of the air film hole is small
In equal to 1mm.
7. straight pipe type rocket chamber according to claim 1, which is characterized in that further include being mounted on burner inner liner
The turbine of tail portion, turbine head are equipped with fiaring cone, and turbine tail portion is sequentially connected speed reducer, high-speed motor.
8. straight pipe type rocket chamber according to claim 7, which is characterized in that it further include heat exchanger, connection
In turbine tail portion, the fuel inlet pipe, water injection pipe, liquid oxygen inlet tube pass through heat exchanger.
9. straight pipe type rocket chamber according to claim 1, which is characterized in that fuel inlet pipe, water injection pipe,
Working medium pump and pressure-regulating valve are equipped on liquid oxygen inlet tube, the first water inlet pipe.
10. a kind of power drive unit using any straight pipe type rocket 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 |
|---|---|---|---|
| CN201811391222.5A CN109373351A (en) | 2018-11-21 | 2018-11-21 | Straight pipe type rocket chamber and power drive unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811391222.5A CN109373351A (en) | 2018-11-21 | 2018-11-21 | Straight pipe type rocket chamber and power drive unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109373351A true CN109373351A (en) | 2019-02-22 |
Family
ID=65377038
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811391222.5A Withdrawn CN109373351A (en) | 2018-11-21 | 2018-11-21 | Straight pipe type rocket chamber and power drive unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109373351A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1322896A (en) * | 2000-05-07 | 2001-11-21 | 郭跃生 | Internally cooling method to increase efficiency of heat machine |
| CN200982739Y (en) * | 2006-12-14 | 2007-11-28 | 中国航天科技集团公司第六研究院第十一研究所 | Large flow high room pressure quick starting air heater |
| CN101713546A (en) * | 2008-10-08 | 2010-05-26 | 中国航空工业第一集团公司沈阳发动机设计研究所 | Low-pollution combustor for various fuels |
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
| CN209229786U (en) * | 2018-11-21 | 2019-08-09 | 贵州智慧能源科技有限公司 | Straight pipe type rocket chamber and power drive unit |
-
2018
- 2018-11-21 CN CN201811391222.5A patent/CN109373351A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1322896A (en) * | 2000-05-07 | 2001-11-21 | 郭跃生 | Internally cooling method to increase efficiency of heat machine |
| CN200982739Y (en) * | 2006-12-14 | 2007-11-28 | 中国航天科技集团公司第六研究院第十一研究所 | Large flow high room pressure quick starting air heater |
| CN101713546A (en) * | 2008-10-08 | 2010-05-26 | 中国航空工业第一集团公司沈阳发动机设计研究所 | Low-pollution combustor for various fuels |
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
| CN209229786U (en) * | 2018-11-21 | 2019-08-09 | 贵州智慧能源科技有限公司 | Straight pipe type rocket chamber and power drive unit |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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| WW01 | Invention patent application withdrawn after publication | ||
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Application publication date: 20190222 |