CN109268169A - A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system - Google Patents
A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system Download PDFInfo
- Publication number
- CN109268169A CN109268169A CN201811390656.3A CN201811390656A CN109268169A CN 109268169 A CN109268169 A CN 109268169A CN 201811390656 A CN201811390656 A CN 201811390656A CN 109268169 A CN109268169 A CN 109268169A
- Authority
- CN
- China
- Prior art keywords
- water
- turbine
- pipe
- energy resource
- clean energy
- Prior art date
- 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.)
- Withdrawn
Links
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 121
- 230000005611 electricity Effects 0.000 title claims abstract description 17
- 238000007599 discharging Methods 0.000 title claims abstract description 16
- 238000002347 injection Methods 0.000 claims abstract description 10
- 239000007924 injection Substances 0.000 claims abstract description 10
- 238000000926 separation method Methods 0.000 claims abstract description 6
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 30
- 239000000446 fuel Substances 0.000 claims description 25
- 239000000945 filler Substances 0.000 claims description 19
- 239000007921 spray Substances 0.000 claims description 13
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 8
- 239000001301 oxygen Substances 0.000 claims description 8
- 229910052760 oxygen Inorganic materials 0.000 claims description 8
- 239000007788 liquid Substances 0.000 claims description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 abstract description 20
- 238000002485 combustion reaction Methods 0.000 abstract description 17
- 239000001569 carbon dioxide Substances 0.000 abstract description 10
- 229910002092 carbon dioxide Inorganic materials 0.000 abstract description 10
- 238000001816 cooling Methods 0.000 abstract description 8
- 239000000498 cooling water Substances 0.000 abstract description 4
- 230000009471 action Effects 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 35
- 239000007789 gas Substances 0.000 description 18
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 8
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 6
- 239000000567 combustion gas Substances 0.000 description 6
- 239000003949 liquefied natural gas Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 239000003345 natural gas Substances 0.000 description 4
- 239000010865 sewage Substances 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000011229 interlayer Substances 0.000 description 3
- 229910052757 nitrogen Inorganic materials 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 241000967522 Eruca pinnatifida Species 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
-
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
- F01K25/06—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using mixtures of different fluids
-
- 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
-
- 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 discloses a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation systems, including sequentially connected rocket chamber, turbine, motor, it further include condenser, separator, condenser is connected on turbine, separator connects condenser, and separator reconnects rocket chamber, turbine by water pipe.Beneficial effects of the present invention: the water and cooling water of rocket chamber's injection become superheated steam under high temperature action, superheated steam can do work to turbine section, turbine wheel shaft drives motor shaft, to convert electric energy for mechanical energy, and the low-temp low-pressure mixed gas exported by turbine, by condenser, separator, water and carbon dioxide separation are gone out, it can participate in burning by water pipe, combustion chamber is cooling, turbine cooling, carbon dioxide can collect, this water circulation system reuses water, improve the heat utilization efficiency of entire combustion chamber, it is a kind of power generator that clean energy resource is new, it is very environmentally friendly.
Description
Technical field
The present invention relates to a kind of power generator more particularly to a kind of clean energy resource water circulation zero-discharging rocket engines
Burner electricity generation system.
Background technique
The existing higher generating set of efficiency is mostly Gas Turbine Generating Units, and Gas Turbine Generating Units overall structure is multiple
Miscellaneous, gas turbine is made of compressor, combustion chamber and turbine, and turbine is main acting component, and compressor part is needed to sky
Gas carries out pressurization acting, can consume a large amount of turbine function, and efficiency is relatively low, and gas turbine application fuel oil or combustion gas etc. are carried out with air
Combustion reaction, due to containing a large amount of nitrogen in air, combustion process is also easy to produce the pollution gas such as nitrogen oxides.Common rocket
For engine since internal flame extreme temperatures, combustion chamber and nozzle structure are difficult to bear its high temperature, reliably working duration is shorter, and
Large quantity of exhaust gas is generated in combustion process, high-temperature gas is not also utilized effectively.
Summary of the invention
Technical problem to be solved by the present invention lies in provide a kind of to solve in above-mentioned background technique that structure is complicated, efficiency
A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system that is low, being also easy to produce pollutant and use the burning
The power drive unit of room.
The present invention is solution above-mentioned technical problem by the following technical programs: the present invention discloses a kind of clean energy resource water and follows
Circulation layer discharges rocket engine burner electricity generation system, including sequentially connected rocket chamber, turbine, motor, also
Including condenser, separator, condenser is connected on turbine, and separator connects condenser, and separator reconnects fire by water pipe
Arrow engine chamber, turbine.
Preferably, rocket chamber includes sequentially connected ejector filler, burner inner liner；The side of the ejector filler is set
There are fuel inlet pipe, water injection pipe, liquid oxygen inlet tube, the other side is equipped with fuel nozzle, water spray pipe, liquid oxygen spray in alignment burner inner liner
Pipe, water injection pipe connect separator.
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 includes at least two cylinders that divide for capableing of dismantling connection, described point of cylinder be straight barrel type or
Gauge structure is straightened, uses flanged joint between adjacent point of cylinder, each, which divides on cylinder, is equipped with the first water inlet pipe, and the first water inlet pipe connects
Connect separator.
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.
It preferably, further include high speed jet pipe, the high speed jet pipe includes at least two capableing of being in charge of for dismantling connection, described
Be in charge of to straighten gauge 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, second into
Water pipe connects separator.
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.
It preferably, further include air separator, before being mounted on liquid oxygen inlet tube.
It preferably, further include fiaring cone, fiaring cone is mounted on turbine front end.
The present invention has the advantage that compared with prior art
(1) the cooling water of the water and burner inner liner that ejector filler injects in rocket chamber becomes under high temperature action
The water and carbon dioxide that superheated steam, steam and combustion reaction generate collectively form combustion gas, and wherein vapor accounts for the overwhelming majority, mistake
Hot steam can do work to turbine section, and turbine wheel shaft drives motor shaft, so that electric energy is converted by mechanical energy, and by turbine output
Low-temp low-pressure mixed gas goes out water and carbon dioxide separation by condenser, separator, and a part of water can pass through water pipe
Rocket chamber and turbine are connected, burning, combustion chamber cooling, turbine cooling can be participated in, carbon dioxide can be collected
Get up, this water circulation system reuses water, improves the heat utilization efficiency of entire combustion chamber；
(2) 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；
(3) the first water inlet pipe, the second water inlet pipe are set, is conducive to being uniformly distributed for outer wall cooling water pressure, can be segmented
The temperature of the adjusting of the formula engine chamber, good cooling results.
Detailed description of the invention
Fig. 1 is a kind of knot of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system of the embodiment of the present invention
Structure schematic diagram；
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 one rocket chamber of the embodiment of the present invention；
Fig. 4 is the perspective view of the explosion of two rocket chamber of the embodiment of the present invention.
Figure label: rocket chamber 1, ejector filler 11, fuel bed 111, fuel inlet pipe 1111, fuel nozzle
1112, layer 112, water injection pipe 1121, water spray pipe 122, liquid oxygen layer 113, liquid oxygen inlet tube 1131, liquid oxygen jet pipe 1132, fire are filled the water
Flame cylinder 12 divides cylinder 121, outer wall 1211, inner wall 1212, air film hole 12121, the first water inlet pipe 1213, high speed jet pipe 13, is in charge of
131, outer layer 1311, internal layer 1312, the second water inlet pipe 1313,
Turbine 2, motor 3, condenser 4, separator 5, air separator 6, fiaring cone 7.
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.
Embodiment one:
As shown in Figure 1, the present invention discloses a kind of clean energy resource water circulation zero-discharging rocket engine in conjunction with shown in Fig. 2,3
Burner electricity generation system, including sequentially connected rocket chamber 1, turbine 2, motor 3 further include condenser 4, separation
Device 5, condenser 4 are connected on turbine 2, and separator 5 connects condenser 4, and separator 5 reconnects rocket engine by water pipe and fires
Burn room 1, turbine 2.
As shown in Figure 2,3, rocket chamber 1 includes sequentially connected ejector filler 11, burner inner liner 12, high speed jet pipe
13, the side of the ejector filler 11 is equipped with fuel inlet, 1111, water injection pipe 1121, liquid oxygen inlet tube 1131, and the other side is equipped with pair
Fuel nozzle 1112, water spray pipe 1122, liquid oxygen jet pipe 1132 in quasi- burner inner liner 12, water injection pipe 1121 connect separator 5, specifically
, the ejector filler 11 includes three fuel beds 111 stacked together, water filling layer 112, liquid oxygen layer 113, fuel bed 111, note
Water layer 112, liquid oxygen layer 113 inside be cavity, the cavity side of fuel bed 111 is arranged in 1111 pipe of fuel inlet, another
Side is equipped with fuel nozzle 1112, and the side of the cavity of water filling layer 112 is arranged in water injection pipe 1121, and the other side is equipped with water spray pipe
1122, the side of the cavity of liquid oxygen layer 113 is arranged in liquid oxygen inlet tube 1131, and the other side is equipped with liquid oxygen jet pipe 1132.Specifically,
By from left to right, first interlayer is spray liquefied natural gas (LNG) in such as figure, second interlayer is spray sewage, third folder
Layer is spray liquid oxygen, and each interlayer is the jet pipe of different bores, and every layer of water cavity can avoid other layers of jet pipe, all
Jet pipe is aligned inside burner inner liner 12.
The burner inner liner 12 include at least two be capable of dismantling connection divide cylinder 121, described point of cylinder 121 is variable diameters knot
Structure uses flanged joint between adjacent point of cylinder 121, each, which divides on cylinder 121, is equipped with the first water inlet pipe 1213, the first water inlet pipe
Divide cylinder 121 to include outer wall 1211, inner wall 1212 described in 1213 connection separators 5, storage is constituted between outer wall 1211 and inner wall 1212
Water chamber, the first water inlet pipe 1213 are located on the outer wall, and inner wall 1212 is equipped with air film hole, and outer wall 1211 is two semicircular structures
It docks.First water inlet pipe 2113 is equipped with pressure-regulating valve, and sewage inlet can be adjusted according to chamber temperature.
The outer wall for being wherein each divided to cylinder 121 is that two semicircular structures dock.Herein, by taking two points of cylinders 21 as an example.The fire
It is equipped with igniter inside flame cylinder 12, is used for gas ignition.
The high speed jet pipe 13 include at least two be capable of dismantling connection be in charge of 131, it is described to be in charge of 131 for variable diameters knot
Structure, adjacent to be in charge of between 131 using flanged joint, each, which is in charge of on 131, is equipped with the second water inlet pipe 1313, the second water inlet pipe
1313 connection separators 5.It is described be in charge of 131 include outer layer 1311, internal layer 1312, between outer layer 1311 and internal layer 1312 constitute storage
Water chamber, the second water inlet pipe 1313 are arranged on outer layer 1311, and pressure-regulating valve is equipped on the second water inlet pipe 1313, can be with
Be adjusted sewage inlet according to chamber temperature, internal layer 1312 is equipped with air film hole, outer layer 1311 by two mirror images structure
It docks, because of the relationship that high speed jet pipe 13 is variable diameters, the form that each is in charge of 131 is different, but structure composition is identical.This
Place's high speed jet pipe 13 can be Laval nozzle, and propelling nozzle etc. is, it can be achieved that High Mach number, combustion gas are entered super by subsonics state
Sound, it is corresponding, the supersonic turbines such as impact wheel can be used.Only show that one be connected with burner inner liner 12 is in charge of in figure
131。
Burner inner liner 12, high speed jet pipe 13 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 121 or being in charge of 31 for damage, reduce costs, and be capable of the adjusting of the segmented engine combustion
The temperature of room, good cooling results.
Wherein, the diameter of air film hole is less than or equal to 1mm, and water or vapor can be by air film holes from inside and outside wall or inside and outside
The water storage chamber flowing in combustion chamber that layer is formed.
Further include air separator 6 in the present embodiment, before being mounted on liquid oxygen inlet tube 1131, air can be divided
From.
It further include fiaring cone 7 in the present embodiment, fiaring cone 7 is mounted on 2 front end of turbine.
The course of work of the embodiment of the present invention one:
Air isolates oxygen and nitrogen by air separator 6, and natural gas, oxygen and water can together by ejector filler 11
Combustion reaction is carried out in spray to burner inner liner 12, temperature increases after liquefied natural gas, liquid oxygen and water pass through heat exchanger 43, by whirlpool
Wheel tail gas, which becomes low temperature exhaust gas, natural gas and oxygen, becomes gaseous state from liquid, another part water by the first water inlet pipe 1213 or/and
Second water inlet pipe 1313 injects the burner inner liner 12 and high speed jet pipe 13 of segmented, and every section of water passes through adjusting by tube wall temperature
Pressure-regulating valve is controlled, and the water that is injected by ejector filler 11 and is divided cylinder 121 and is in charge of on 131 and make for cooling water in high temperature
Become superheated steam under, the water and carbon dioxide that steam and combustion reaction generate collectively form combustion gas, and wherein vapor accounts for absolutely
It is most of, it can be sprayed after convergent-divergent nozzle with supersonic speed, form high speed, high temperature and high-pressure gas, it can be 2 sections to turbine
Acting, 2 axis of turbine drives the motor shaft of high-speed motor 3, to convert electric energy for mechanical energy.The high-temperature tail gas that turbine 2 comes out
It can be cooled down by condenser 4, using separator 5, water and carbon dioxide separation are come out, the water isolated connects through piping
Connect ejector filler 11, burner inner liner 12, high speed jet pipe 13 and turbine 2.
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 12 wall of burner inner liner, high speed jet pipe 13 and whirlpool
The temperature of wheel 2, improves the service life of high-temperature component, combustion gas tail gas is mainly vapor and a small amount of carbon dioxide, nitrogen-free oxygen
The pollution gas such as compound, 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 12 and high speed jet pipe 13 further improves its maintainability.
Embodiment two:
Embodiment two and the difference of embodiment one are: burner inner liner is straight pipe type.
As shown in figure 4, rocket chamber 1 includes sequentially connected ejector filler 11, burner inner liner 12；The burner inner liner
12 include at least two be capable of dismantling connection divide cylinder 121, described point of cylinder 121 is to straighten gauge structure, is adopted between adjacent point of cylinder 121
With flanged joint, each, which divides on cylinder 121, is equipped with the first water inlet pipe 1213, and the first water inlet pipe 1213 connects described in separator 5
Dividing cylinder 121 includes outer wall 1211, inner wall 1212, and water storage chamber, the first water inlet pipe are constituted between outer wall 1211 and inner wall 1212
1213 are located on the outer wall, and inner wall 1212 is equipped with air film hole, and outer wall 1211 is that two semicircular structures dock.First water inlet
Pipe 2113 is equipped with pressure-regulating valve, and sewage inlet can be adjusted according to chamber temperature.Wherein each divide cylinder 121
Outer wall is that two semicircular structures dock.Herein, by taking two points of cylinders 21 as an example.Igniting is equipped with inside the burner inner liner 12
Device is used for gas ignition.
The rocket chamber 1 of straight pipe type can be matched with subsonic turbine and transonic turbine, more efficient.
The course of work of the embodiment of the present invention two:
Air isolates oxygen and nitrogen by air separator 6, and natural gas, oxygen and water can together by ejector filler 11
Combustion reaction is carried out in spray to burner inner liner 12, temperature increases after liquefied natural gas, liquid oxygen and water pass through heat exchanger 43, by whirlpool
Wheel tail gas, which becomes low temperature exhaust gas, natural gas and oxygen, becomes gaseous state from liquid, and another part water is injected by the first water inlet pipe 1213
The burner inner liner 12 of segmented, every section of water are controlled, by 11 note of ejector filler by tube wall temperature by adjusting pressure-regulating valve
The water entered and the water for dividing cylinder 121 and being in charge of on 131 for cooling become superheated steam, steam and combustion reaction under high temperature action
The water and carbon dioxide of generation collectively form combustion gas, and wherein vapor accounts for the overwhelming majority, and superheated steam can do 2 sections of turbine
Function, 2 axis of turbine drive the motor shaft of high-speed motor 3, to convert electric energy for mechanical energy, the high-temperature tail gas that turbine 2 comes out can
To be cooled down by condenser 4, using separator 5, water and carbon dioxide separation are come out, the water isolated is connected through piping
Ejector filler 11, burner inner liner 12 and turbine 2.
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 (9)
1. a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system, which is characterized in that including successively connecting
The rocket chamber that connects, turbine, motor, further include condenser, separator, condenser is connected on turbine, separator
Condenser is connected, separator reconnects rocket chamber, turbine by water pipe.
2. a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system according to claim 1,
It is characterized in that, rocket chamber includes sequentially connected ejector filler, burner inner liner, and the side of the ejector filler is equipped with fuel
Inlet tube, 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, note
Water pipe connects separator.
3. a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system according to claim 2,
It is characterized in that, the ejector filler includes three fuel beds stacked together, water filling layer, liquid oxygen layer, fuel bed, water filling layer, liquid
The inside of oxygen layer is cavity, and the cavity side of fuel bed is arranged in fuel inlet pipe, and the other side is equipped with fuel nozzle, water injection pipe
The side of the cavity of water filling layer is set, the other side is equipped with water spray pipe, and the side of the cavity of liquid oxygen layer is arranged in liquid oxygen inlet tube,
The other side is equipped with liquid oxygen jet pipe.
4. a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system according to claim 2,
It is characterized in that, the burner inner liner includes at least two cylinders that divide for capableing of dismantling connection, and described point of cylinder is straight barrel type or variable diameters
Structure uses flanged joint between adjacent point of cylinder, each, which divides on cylinder, is equipped with the first water inlet pipe, the connection separation of the first water inlet pipe
Device.
5. a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system according to claim 4,
It is characterized in that, 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 located at outside
On wall, inner wall is equipped with air film hole, and outer wall is that two semicircular structures dock.
6. a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system according to claim 2,
Be characterized in that, further include high speed jet pipe, the high speed jet pipe includes at least two capableing of being in charge of for dismantling connection, it is described be in charge of for
Straighten gauge 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, and the second water inlet pipe connects
Connect separator.
7. a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system according to claim 6,
It is characterized in that, it is 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 arranged outside
On layer, internal layer is equipped with air film hole, and outer layer is docked by the structure of two mirror images.
8. a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system according to claim 2,
It is characterized in that, further includes air separator, before being mounted on liquid oxygen inlet tube.
9. a kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system according to claim 1,
It is characterized in that, further includes fiaring cone, fiaring cone is mounted on turbine front end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811390656.3A CN109268169A (en) | 2018-11-21 | 2018-11-21 | A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811390656.3A CN109268169A (en) | 2018-11-21 | 2018-11-21 | A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109268169A true CN109268169A (en) | 2019-01-25 |
Family
ID=65191184
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811390656.3A Withdrawn CN109268169A (en) | 2018-11-21 | 2018-11-21 | A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109268169A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112780411A (en) * | 2019-11-06 | 2021-05-11 | 中国航发商用航空发动机有限责任公司 | Gas turbine water vapor hybrid power system, water vapor generation assembly, aircraft and power supply method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5014508A (en) * | 1989-03-18 | 1991-05-14 | Messerschmitt-Boelkow-Blohm Gmbh | Combination propulsion system for a flying craft |
| 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 |
| CN101371026A (en) * | 2005-12-13 | 2009-02-18 | 理查德·A·哈瑟 | Water combustion technology-the haase cycle |
| CN101539066A (en) * | 2009-04-22 | 2009-09-23 | 王鑫弘 | Jet-steam compound engine with spray liquid evaporating on hot wall |
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
| US20170254296A1 (en) * | 2016-03-03 | 2017-09-07 | Daniel Patrick Weldon | Rocket Engine Bipropellant Supply System |
| CN108131975A (en) * | 2017-12-21 | 2018-06-08 | 中国航发南方工业有限公司 | Heat exchange type jet pipe and high temperature combustion exhaust waste heat recycle method |
| CN209228489U (en) * | 2018-11-21 | 2019-08-09 | 贵州智慧能源科技有限公司 | A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system |
-
2018
- 2018-11-21 CN CN201811390656.3A patent/CN109268169A/en not_active Withdrawn
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5014508A (en) * | 1989-03-18 | 1991-05-14 | Messerschmitt-Boelkow-Blohm Gmbh | Combination propulsion system for a flying craft |
| CN1322896A (en) * | 2000-05-07 | 2001-11-21 | 郭跃生 | Internally cooling method to increase efficiency of heat machine |
| CN101371026A (en) * | 2005-12-13 | 2009-02-18 | 理查德·A·哈瑟 | Water combustion technology-the haase cycle |
| 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 |
| CN101539066A (en) * | 2009-04-22 | 2009-09-23 | 王鑫弘 | Jet-steam compound engine with spray liquid evaporating on hot wall |
| US20170254296A1 (en) * | 2016-03-03 | 2017-09-07 | Daniel Patrick Weldon | Rocket Engine Bipropellant Supply System |
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
| CN108131975A (en) * | 2017-12-21 | 2018-06-08 | 中国航发南方工业有限公司 | Heat exchange type jet pipe and high temperature combustion exhaust waste heat recycle method |
| CN209228489U (en) * | 2018-11-21 | 2019-08-09 | 贵州智慧能源科技有限公司 | A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112780411A (en) * | 2019-11-06 | 2021-05-11 | 中国航发商用航空发动机有限责任公司 | Gas turbine water vapor hybrid power system, water vapor generation assembly, aircraft and power supply method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106014637B (en) | Air precooling compresses aero-engine and Hypersonic Aircraft | |
| CN111577459B (en) | Gas turbine power generation device utilizing viscous force of pulse detonation gas to do work | |
| CN108603441B (en) | Combustion chamber apparatus and system including the same | |
| CN106051821A (en) | Shunting type multi-pipe pulse detonation combustion chamber | |
| CN108757182A (en) | Air-breathing rocket engine and Hypersonic Aircraft | |
| CN102619645A (en) | Charge engine injected with low-entropy mixed-combustion liquefied gas | |
| CN101117915A (en) | Subsequent technology of combined dynamoelectric engine | |
| CN209228489U (en) | A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system | |
| CN109268169A (en) | A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system | |
| CN209229786U (en) | Straight pipe type rocket chamber and power drive unit | |
| CN108826356B (en) | Combustion chamber for fuel cell turbine composite simulation test | |
| CN115046227B (en) | High-pressure rotary detonation gas turbine using ammonia as fuel | |
| CN209229787U (en) | Segmented rocket engine combustion chamber and power drive unit | |
| CN113882968B (en) | Wide-speed-range multi-working-medium efficiency matching combined power system | |
| CN109357287A (en) | Segmented rocket engine combustion chamber and power drive unit | |
| CN108757221A (en) | A kind of liquid Asia burning ramjet | |
| RU2594828C1 (en) | Propulsion engine of supersonic aircraft | |
| CN103939944A (en) | Double-flap swirl-type dual-fuel nozzle used for chemical regenerative cycle | |
| CN203685414U (en) | Ramjet engine | |
| CN207729590U (en) | Turbocharging type combustor | |
| RU2292471C1 (en) | Method of and system for fuel delivery into gas-turbine engine (versions) | |
| CN101737104B (en) | Fuel gas-steam turbine engine | |
| RU2591361C1 (en) | Engine of hypersonic aircraft | |
| CN109373351A (en) | Straight pipe type rocket chamber and power drive unit | |
| CN202228175U (en) | Low-temperature air inlet engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190125 |