CN112177697B - Thermal protection coupling open Brayton power generation system based on thermal decomposition reaction - Google Patents
Thermal protection coupling open Brayton power generation system based on thermal decomposition reaction Download PDFInfo
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- CN112177697B CN112177697B CN202010933428.7A CN202010933428A CN112177697B CN 112177697 B CN112177697 B CN 112177697B CN 202010933428 A CN202010933428 A CN 202010933428A CN 112177697 B CN112177697 B CN 112177697B
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- 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
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
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- 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
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- 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
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
- F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
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- 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
- F01K25/08—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 special vapours
- F01K25/10—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 special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
- F01K25/103—Carbon dioxide
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- 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
- F01K25/08—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 special vapours
- F01K25/10—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 special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
- F01K25/106—Ammonia
Abstract
The invention discloses a thermal protection coupling open Brayton power generation system based on thermal decomposition reaction, which comprises a steam generator, a turbine generator and a spray pipe which are connected in series, and is used for solving the problems of insufficient thermal protection of a hypersonic aircraft and electric energy supply during high-Mach flight; the micro turbine generator realizes heat-power conversion through superheated gas discharged by the steam generator to generate electric power; the jet pipe system promotes the high-temperature exhaust gas of the micro turbine generator to be deeply expanded to generate thrust; the power generation system obviously enhances the thermal protection efficiency, the power generation capacity and the economy of the hypersonic vehicle.
Description
Technical Field
The invention relates to the technical field of power generation systems, in particular to a thermal protection coupling open Brayton power generation system based on thermal decomposition reaction.
Background
In a high-sound-speed flying state, a main structure of the hypersonic aircraft is usually in an extremely severe high-temperature environment due to the combined action of viscous friction, shock wave flow and pneumatic combustion. For example, when the flight mach number reaches 8Ma, the maximum temperature at the nose cone of a hypersonic aircraft can rise to 1800 ℃, and the temperature of the scramjet combustor can even reach 2800 ℃. For long-range rocket solid fuel engines, however, the high burn rate powder charge and long tail nozzles may be subjected to temperatures up to 3500 ℃ upon ignition.
The extreme thermal conditions (also known as "thermal barriers") of the primary structure of hypersonic aircraft pose serious challenges to thermal protection techniques. The existing passive thermal protection, namely the method of laying ablation materials to absorb heat and laying heat insulation materials to insulate heat, is difficult to ensure the strength, rigidity and safety reliability of a main structure when an aircraft runs, and occupies the weight of a carrying platform; the passive thermal protection basically cannot meet the development requirement of the hypersonic speed aircraft, and for a high-temperature solid rocket engine adopting the passive thermal protection, the failure of the long tail nozzle can account for 1/2 of the failure rate of the whole solid rocket engine, and the weight of the long tail nozzle especially accounts for 1/3 of the total weight of the solid rocket engine. Therefore, in order to realize the crossing development of the hypersonic aircraft, the thermal barrier must be broken through so as to realize the high-efficiency thermal protection of important parts of the hypersonic aircraft in a high-mach-number flight state and ensure the strength, rigidity and failure resistance of a main structure of the hypersonic aircraft in high-speed flight.
Meanwhile, in a high-mach-number flight state, the hypersonic aircraft has huge power consumption, and can generate strong induction torque during hypersonic flight, so that in order to improve stability in a wider flight airspace and overcome adverse effects caused by saturation of an actuator, the conventional hypersonic flight system not only uses an electric pneumatic control surface, but also integrates various advanced control means such as thrust vector, variable inertia, micro-nozzle control, intelligent material self-adaptive wings and the like. Under the combined action of the factors, the electric power requirement of the flight control system of the hypersonic flight vehicle is far beyond the requirement of a transonic fighter of the same era, and the electric power requirement can reach 50-100 kW. In addition, for an airborne radar system of the hypersonic aircraft, the peak power can reach 50-100kW, and the total energy consumption of the flight control system, the airborne radar, the computer module and other onboard electrical appliances is combined, so that the overall power consumption of the aircraft can be not lower than 0.3 MW. However, for a hypersonic aircraft, whether a scramjet engine or a solid rocket engine is used, all rotating parts in the engine are stopped in a high mach number flight condition, which means that the hypersonic aircraft cannot rely on the mechanical energy of the engine rotor to produce a sufficient amount of electrical energy.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a thermal protection coupling open Brayton power generation system based on thermal decomposition reaction, high-performance thermal protection is realized by combining strong heat absorption mechanisms such as ammonium bicarbonate thermal decomposition reaction, multi-component multiple phase change, vortex convection and the like, and electric energy supply in a high Mach number state is solved by carrying out heat-power-electricity conversion through a micro turbine generator.
The invention is realized by the following technical scheme:
a thermal protection coupling open Brayton power generation system based on thermal decomposition reaction comprises a steam generator, a turbine generator and a spray pipe;
the steam generator is arranged at a preset position of the aircraft and comprises a shell and pyrolysis working media filled in the shell, the pyrolysis working media exchanges heat with the aircraft and is decomposed to generate pyrolysis products, an output port of the pyrolysis products is formed in the shell and is connected with an input end of the turbine generator, and an exhaust port of the turbine generator is connected with the spray pipe.
Preferably, the pyrolysis working medium is ammonium bicarbonate, dry ice, ammonium chloride or ammonium perchlorate, or a mixture of the above working media.
Preferably, the pyrolysis working medium is ammonium bicarbonate, and the ammonium bicarbonate is in a granular or blocky porous structure.
Preferably, the ammonium bicarbonate is mixed with a desensitizing agent.
Preferably, a thermal expansion framework is further arranged in the shell and comprises a framework and branches arranged on the framework, the framework is connected with the shell, and the branches extend into the pyrolysis working medium in a root hair shape.
Preferably, the material of the thermal expansion framework is high expansion ceramic.
Preferably, the steam generator is arranged in a sandwich of high temperature walls of the aircraft, or in a high temperature chamber of the aircraft.
Preferably, the turbine generator is a micro turbine generator.
Compared with the prior art, the invention has the following technical effects:
the invention provides a thermal protection coupling open Brayton power generation system based on thermal decomposition reaction, which comprises a steam generator, a turbine generator and a spray pipe which are connected in series, wherein a pyrolysis working medium is filled in the steam generator and is arranged in a high-temperature area of an aircraft, when the aircraft is in a high-Mach number flight state, a shell of the steam generator exchanges heat with the aircraft to realize the purpose of cooling the aircraft, meanwhile, the pyrolysis working medium in the steam generator is decomposed to produce a pyrolysis product, the pyrolysis product is heated and pressurized in a limited space of the shell and flows towards a low-pressure area, secondary heat exchange is realized in the flowing process, and an overheated gaseous mixed working medium is formed. The gaseous mixed working medium enters a turbine generator to generate power, and exhaust gas after acting is discharged through a spray pipe to provide auxiliary thrust for the aircraft. In the aspect of thermal protection, the overall heat capacity and the surface heat exchange coefficient of the system are higher than those of regenerative cooling by more than one order of magnitude; in the aspect of power supply performance, the miniature high-speed turbine generator can output high-power electric energy.
Drawings
FIG. 1 is a block diagram of a power generation system of the present invention;
FIG. 2 is a schematic diagram of the thermal-power conversion process of the pyrolysis mixed working medium of the present invention.
In the figure: 1. an interlayer; 2. pyrolyzing the working medium; 3. a turbine generator; 4. a nozzle; 5. a steam generator.
Detailed Description
The present invention will now be described in further detail with reference to the attached drawings, which are illustrative, but not limiting, of the present invention.
Referring to fig. 1 and 2, a thermal protection coupled open brayton power generation system based on thermal decomposition reaction includes a steam generator 5, a turbine generator 3 and a nozzle 4.
The steam generator 5 is arranged at a preset position of the aircraft and comprises a shell and pyrolysis working medium 2 filled in the shell, wherein an output port of a pyrolysis product is arranged on the shell, the output port is connected with an input end of the turbine generator 3, and the turbine generator 3 is connected with the exhaust port and the spray pipe 4.
Inside aircraft top layer high temperature conducted steam generator 5 through the casing, made the pyrolysis material decompose, and then played the effect of cooling to the aircraft, generated electricity in the leading-in turbine generator 3 of pyrolysis product after the heat transfer simultaneously, and the exhaust after the electricity generation passes through the spray tube and discharges, provides power for the aircraft.
The pyrolysis working medium 2 is dry ice, ammonium chloride, ammonium perchlorate or ammonium bicarbonate or a mixture of the above components.
The pyrolysis working medium 2 is preferably ammonium bicarbonate, and the ammonium bicarbonate is in a granular or blocky porous medium structure.
The ammonium bicarbonate releases cold energy through thermal decomposition reaction, and decomposes generated multiphase and multicomponent mixed working medium which is in a gas-liquid-supercritical state, absorbs heat through multiple phase changes and strong vortex convection of the multicomponent multiphase fluid and is used as a medium for efficient thermal protection. The ammonium bicarbonate is subjected to thermal decomposition chemical reaction, phase change of pyrolysis products and forced convection process, and a large amount of aerodynamic heat and combustion heat are absorbed; the pyrolysis product generates a heat absorption expansion process under the condition of limited volume under the action of the high-temperature environment and geometric constraint of the steam generator, and the working medium pressure is greatly improved.
In order to prevent the ammonium bicarbonate solid from flash explosion due to the excessively fast pyrolysis rate in a high-temperature environment, a desensitizer is doped in the ammonium bicarbonate, and the thermal decomposition reaction rate of the ammonium bicarbonate solid is inhibited from the chemical kinetics mechanism.
The steam generator 5 adopts a light and small efficient heat exchange structure and is arranged in the interlayer 1 of the high-temperature wall surface of the hypersonic aircraft or in a high-temperature cavity of the hypersonic aircraft.
In steam generator 5's casing, still be provided with the thermal expansion skeleton, the thermal expansion skeleton is pre-buried in pyrolysis working medium 2, and the thermal expansion skeleton is heated the expansion and is made the pyrolysis working medium fully with high temperature housing contact, improves heat exchange efficiency, prevents to take place to transmit heat and worsen.
The thermal expansion framework wraps the framework and branches are arranged on the framework and extend into the ammonium bicarbonate in a crotch shape, and two ends of the framework are fixedly connected with two sides of the shell.
In order to realize the basic function of the thermal expansion framework, the thermal expansion framework is in a tree root shape, the branch structure of the framework extends into the ammonium bicarbonate, and two ends of the framework are connected with the shell through fixing points on the metal shell, so that the temperature change of the metal shell is induced through heat conduction and heat radiation. When the pyrolysis working medium is separated from the metal shell, the temperature of the metal shell rises, the thermal expansion framework expands under heating, and the pyrolysis working medium is squeezed, so that the pyrolysis working medium and the metal shell are restored to be in contact.
The thermal expansion framework is made of high expansion ceramics in order to keep the ammonium bicarbonate in contact with the shell.
The turbine generator 3 is a high-speed micro turbine generator, adopts a TA configuration of a centripetal turbine coupled with a high-speed motor, and is used as a main airborne power supply of the hypersonic aircraft. The micro turbine generator adopts multi-component superheated mixed gas discharged by a steam generator as a medium for conversion of heat energy, mechanical work and electric energy of a centripetal turbine stage.
The jet pipe 4 and the attitude track control system of the hypersonic vehicle are mutually related through a gas transmission pipeline, the gas flow discharged from the jet pipe when the system operates is ejected at a high speed through the gas transmission pipeline to generate extra attitude track control force, and the high-temperature exhaust gas discharged from the micro turbine generator is sucked into the jet pipe 4 to be used as a working medium for deep expansion.
The working principle of the thermal protection coupled open brayton power generation system based on thermal decomposition reaction of the present invention is explained in detail below.
The working process mainly comprises three stages, namely steam generation, steam expansion work application and exhaust propulsion.
A steam generation stage: the ammonium bicarbonate stored in the steam generator 5 absorbs the aerodynamic heat generated by the aircraft shell and the combustion heat generated by the engine, and undergoes a rapid thermal decomposition reaction, first generating carbon dioxide (CO)2) Ammonia (NH)3) And water (H)2O), and at the same time, the mixed product generated by pyrolysis expands in volume and is rapidly pressurized due to heat absorption in the confined space, and flows toward a low-pressure region. In the flowing process, the pyrolysis product continuously absorbs heat and undergoes multiple boiling heat transfer and multiphase fluid vortex flowing processes, and finally is heated into superheated gaseous mixed working medium.
A steam expansion stage: the superheated gaseous mixed working medium enters a micro turbine generator to push a micro turbine and a generating rotor to rotate at a high speed, so that the conversion of heat energy, mechanical work and electric energy is realized, the electric energy is transmitted to an aircraft and is used as a main airborne power supply of the aircraft.
In the exhaust propulsion stage, exhaust of the turbine generator enters a jet pipe group, residual heat energy and pressure energy are further converted into kinetic energy, and the kinetic energy is discharged out of the system through the jet pipe, so that thrust is generated, and auxiliary power is provided for the aircraft.
The thermal protection coupling open Brayton power generation system based on the thermal decomposition reaction realizes high-performance thermal protection by combining strong heat absorption mechanisms such as ammonium bicarbonate thermal decomposition reaction, multi-component multiple phase change, vortex convection and the like, and solves the electric energy supply in a high Mach number state by carrying out heat-power-electricity conversion through the micro turbine generator.
The thermal protection coupling open Brayton power generation system based on the thermal decomposition reaction has the following advantages:
firstly, the thermal protection capability of the hypersonic aircraft is improved: the composite high-efficiency thermal protection of the hypersonic aircraft is realized by utilizing strong heat absorption mechanisms of ammonium bicarbonate such as pyrolysis, solid-liquid and liquid-vapor phase change, strong vortex convection and the like, and conditions are created for improving the upper limit of the combustion temperature.
Secondly, the power performance is improved, and the high-speed micro turbine generator can realize high-specific power thermoelectric conversion. Compared with a chemical battery, the transient performance such as peak output power, instantaneous starting speed and the like is remarkably improved. Compared with a chemical battery, the system also has the advantages of high reliability and storage resistance, and the overall reliability of the power supply system can be improved.
In addition, additional thrust is provided, the maneuvering performance of the hypersonic aircraft is improved, and the exhaust of the spray pipe is utilized through the micro-spray pipe flight control system, so that the hypersonic aircraft can be a new power source.
Finally, the power generation system adopts open circulation, does not need a cold source, utilizes pyrolysis gasification expansion to boost pressure, does not need a compressor, improves the heat efficiency and the overall reliability of unit operation, reduces the additional weight of the unit, and adapts to the working environment lacking the cold source.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (6)
1. A thermal protection coupling open Brayton power generation system based on thermal decomposition reaction is characterized by comprising a steam generator (5), a turbine generator (3) and a spray pipe (4);
the steam generator (5) is arranged at a preset position of the aircraft and comprises a shell and pyrolysis working media (2) filled in the shell, wherein the pyrolysis working media are ammonium bicarbonate, dry ice, ammonium chloride or ammonium perchlorate or a mixture of the ammonium bicarbonate, the dry ice, the ammonium chloride or the ammonium perchlorate;
still be provided with the thermal expansion skeleton in the casing, the thermal expansion skeleton includes the skeleton to and set up branch on the skeleton, the both ends of skeleton are connected with the casing through the fixed point on the casing, casing temperature risees, the thermal expansion skeleton is heated the inflation, form the squeezing action to pyrolysis working medium, make it resume the contact with the casing, the branch is the root hair form and stretches into to the pyrolysis working medium, pyrolysis working medium and aircraft heat transfer and decomposition produce pyrolysis product, be provided with the delivery outlet of pyrolysis product on the casing, the delivery outlet is connected with the input of turbo generator (3), the gas vent and spray tube (4) of turbo generator (3) are connected.
2. The thermal protection coupled open brayton power generation system based on thermal decomposition reaction according to claim 1, characterized in that the pyrolysis working medium (2) is ammonium bicarbonate, which is in a granular or block-shaped porous structure.
3. The thermally protected coupled open brayton power generation system in accordance with claim 2, wherein said ammonium bicarbonate is mixed with a phlegmatizer.
4. The thermal protection coupled open brayton power generation system of claim 1, wherein the thermal expansion framework is made of a high expansion ceramic.
5. A thermal protection coupled open brayton power generation system based on thermolysis reaction according to claim 1, characterized in that the steam generator (5) is arranged in the sandwich (1) of the high temperature wall of the aircraft or in the high temperature chamber of the aircraft.
6. A thermal protection coupled open brayton power generation system based on thermal decomposition reaction according to claim 1, characterized in that said turbine generator (3) is a micro turbine generator.
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