CN118066017A - Aviation power device using liquid ammonia as fuel - Google Patents
Aviation power device using liquid ammonia as fuel Download PDFInfo
- Publication number
- CN118066017A CN118066017A CN202410173210.4A CN202410173210A CN118066017A CN 118066017 A CN118066017 A CN 118066017A CN 202410173210 A CN202410173210 A CN 202410173210A CN 118066017 A CN118066017 A CN 118066017A
- Authority
- CN
- China
- Prior art keywords
- hydrogen
- nitrogen
- engine
- liquid ammonia
- power plant
- 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.)
- Pending
Links
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 title claims abstract description 91
- 239000000446 fuel Substances 0.000 title claims abstract description 33
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 199
- 239000001257 hydrogen Substances 0.000 claims abstract description 142
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 142
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 138
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 99
- 239000007789 gas Substances 0.000 claims abstract description 59
- 238000002485 combustion reaction Methods 0.000 claims abstract description 42
- 239000002828 fuel tank Substances 0.000 claims abstract description 16
- 230000009471 action Effects 0.000 claims abstract description 15
- 239000003054 catalyst Substances 0.000 claims abstract description 11
- 238000007664 blowing Methods 0.000 claims abstract description 10
- 239000002737 fuel gas Substances 0.000 claims description 7
- 239000007788 liquid Substances 0.000 claims description 7
- 150000002431 hydrogen Chemical class 0.000 claims description 5
- 238000007599 discharging Methods 0.000 claims description 2
- 229910021529 ammonia Inorganic materials 0.000 abstract description 15
- 238000001816 cooling Methods 0.000 abstract description 2
- 238000007865 diluting Methods 0.000 abstract 1
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 8
- 238000002679 ablation Methods 0.000 description 5
- 238000004880 explosion Methods 0.000 description 5
- 125000004435 hydrogen atom Chemical group [H]* 0.000 description 5
- 239000003350 kerosene Substances 0.000 description 5
- 238000005496 tempering Methods 0.000 description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 229910052799 carbon Inorganic materials 0.000 description 4
- 229910002092 carbon dioxide Inorganic materials 0.000 description 4
- 239000001569 carbon dioxide Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 229910001873 dinitrogen Inorganic materials 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005504 petroleum refining Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- LZDOYGMJVXUZGD-UHFFFAOYSA-J tetrasodium pyrene-1,3,6,8-tetrasulfonate hydrate Chemical compound O.[Na+].[Na+].[Na+].[Na+].[O-]S(=O)(=O)c1cc(c2ccc3c(cc(c4ccc1c2c34)S([O-])(=O)=O)S([O-])(=O)=O)S([O-])(=O)=O LZDOYGMJVXUZGD-UHFFFAOYSA-J 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The embodiment of the invention provides an aviation power device using liquid ammonia as fuel, which comprises a gas compressor, a combustion chamber, a turbine and an exhaust device, and further comprises: the device comprises a heat exchanger, a heater, a decomposing furnace, a catalyst, a PSA gas separator, a liquid ammonia fuel tank, a hydrogen system and a nitrogen system; the liquid ammonia is gasified into ammonia by utilizing the self heat of the engine during operation, the ammonia is decomposed into mixed gas of hydrogen and nitrogen under the action of a catalyst, the mixed gas is further separated into hydrogen and nitrogen by a PSA gas separator, the hydrogen and the nitrogen are respectively input into a hydrogen system and a nitrogen system, and the hydrogen entering the hydrogen system is used as fuel of a combustion chamber, so that the aeroengine has the capability of using ammonia fuel; the nitrogen of the nitrogen system can be used for cooling the turbine rotor and stator blades, realizing the increasing and pushing of the engine, replacing and blowing off the hydrogen in the hydrogen pipeline entering the combustion chamber, blowing the turbine of the engine and diluting the flow of the hydrogen entering the combustion chamber.
Description
Technical Field
The invention relates to the technical field of aircraft power devices, in particular to an aviation power device using liquid ammonia as fuel.
Background
With the deep green aviation concept, on the basis of the traditional aviation gas turbine engine, the hydrogen adaptation of the combustion chamber component and the fuel control system is improved, and the hydrogen-burning engine is developed and developed. The hydrogen energy is an ideal clean energy source for domestic and foreign research because of no carbon element and high heat value per unit mass. However, because the hydrogen has low density and is easy to leak, the storage and transportation cost is high regardless of gas hydrogen or liquid hydrogen; so the hydrogen energy business is used in the aviation field and has a long way to travel.
The prior art mainly has the following defects: (1) Traditional aviation power is provided by a turbine engine combusting kerosene, the combustion of the fuel produces carbon dioxide, which is not a clean energy source, and aviation kerosene is derived from petroleum refining and is a non-renewable energy source. (2) Traditional aero-engines pursue high efficiency, which results in turbine component temperatures exceeding material temperature resistance limits, require compressor air to be drawn to cool the turbine component, and are disadvantageous in further improving engine performance. (3) At present, the research of aviation turbine engines based on hydrogen fuel is carried out by the front tightening gong of the major aviation countries in the world, and although a certain technology is accumulated, hydrogen tempering and thermal ablation still remain to be solved. (4) The hydrogen engine needs to be provided with a special nitrogen source, and the hydrogen in the hydrogen pipeline is replaced and blown off in the starting and stopping process of the engine so as to prevent explosion risks caused by hydrogen residues. (5) There is still no good solution to the problem of how to store and transport hydrogen energy on board an aircraft, which is a great obstacle to the engineering application of hydrogen-fueled aero-power plants.
Accordingly, overcoming the above-mentioned drawbacks of the prior art is a technical problem to be solved by those of ordinary skill in the art.
Disclosure of Invention
The invention provides an aviation power plant taking liquid ammonia as fuel.
The aim of the invention can be achieved by the following scheme:
The invention provides an aviation power device using liquid ammonia as fuel, which comprises a gas compressor, a combustion chamber, a turbine and an exhaust device, and further comprises: the device comprises a heat exchanger, a heater, a decomposing furnace, a catalyst, a PSA gas separator, a liquid ammonia fuel tank, a hydrogen system and a nitrogen system;
The heat exchanger is integrated with the casing of the compressor, the heater is integrated with the casing of the turbine, and the decomposing furnace is integrated with the casing of the exhaust device;
One path of liquid ammonia in the liquid ammonia fuel tank flows to the heater, and the other path flows to the heat exchanger and then flows into the heater;
Under the action of the high-temperature fuel gas of the turbine, the liquid ammonia flowing through the heater is heated and gasified into ammonia gas;
the heater is communicated with the decomposing furnace, and under the action of the catalyst, the ammonia gas is decomposed into a mixed gas of hydrogen and nitrogen;
The mixed gas is separated into hydrogen and nitrogen through the PSA gas separator, the hydrogen enters the hydrogen system, and the nitrogen enters the nitrogen system; the hydrogen of the hydrogen system is used as fuel for the combustion chamber.
Further, the hydrogen system includes: a high pressure hydrogen tank and a first control system; one path of the hydrogen separated from the PSA gas separator flows into the high-pressure hydrogen storage tank, and the other path of the hydrogen enters the combustion chamber to be used as fuel under the control of the first control system.
Further, the high-pressure hydrogen storage tank stores hydrogen, and when the engine of the aviation power device is just started, the stored hydrogen participates in the combustion of the combustion chamber in advance to ensure the starting and running of the engine.
Further, the nitrogen system includes: a high-pressure nitrogen storage tank, a second control system and a three-way valve;
nitrogen separated from the PSA gas separator enters the high pressure nitrogen tank through a first valve via a first line; through a second valve and through a second pipeline, entering the turbine under the control of the second control system; and the air is discharged into the exhaust device to realize boosting under the control of the second control system through a third valve passing through a third pipeline.
Further, nitrogen is stored in the high-pressure nitrogen storage tank, and when the engine of the aviation power device is started or stopped, the stored nitrogen is used for replacing and blowing off hydrogen in a hydrogen pipeline entering the combustion chamber;
when the engine of the aviation power device is started, the stored nitrogen is used for blowing the turbine to drive the engine rotor so as to realize engine starting.
Further, when the boost of the aviation power device is large, nitrogen in the high-pressure nitrogen storage tank is used for being discharged into the exhaust device to realize the boost.
Further, under the action of the second control system, the nitrogen in the high-pressure nitrogen storage tank is used for being mixed into a hydrogen pipeline of the hydrogen entering the combustion chamber so as to dilute the flow of the hydrogen.
Further, the aerodynamic device further comprises: the first pump body, the second pump body and the third pump body;
The first pump body is communicated with the liquid outlet of the liquid ammonia fuel tank and is used for extracting the liquid ammonia to enter the heat exchanger and the heater respectively;
The second pump body is positioned between the decomposing furnace and the PSA gas separator and is used for inputting the mixed gas decomposed into hydrogen and nitrogen into the PSA gas separator;
The third pump body is arranged behind the PSA gas separator, and before the hydrogen system and the nitrogen system, the third pump body is used for pressurizing separated hydrogen and nitrogen and then respectively inputting the hydrogen system and the nitrogen system.
Further, the PSA gas separator is mounted as an accessory outside the engine case of the aero power plant.
Further, the liquid ammonia fuel tank is positioned on an aircraft where the aviation power device is positioned, and the hydrogen system and the nitrogen system are installed outside the engine casing.
Compared with the prior art, the application has the following beneficial effects:
According to the embodiment of the invention, the use of liquid ammonia is increased on the basis of the existing aeroengine or hydrogen fuel engine, the liquid ammonia is gasified into ammonia by utilizing the self heat of the engine during operation, the ammonia is decomposed into the mixed gas of hydrogen and nitrogen under the action of a catalyst, and further the PSA gas separator separates the mixed gas into hydrogen and nitrogen, the hydrogen is respectively input into a hydrogen system and a nitrogen system, and the hydrogen entering the hydrogen system is used as fuel of a combustion chamber, so that the aeroengine has the capability of using ammonia fuel. Compared with the traditional engine which uses kerosene as non-renewable energy, the engine can not produce carbon dioxide cleanly, and the aviation power device uses ammonia as renewable energy, so that zero carbon emission is realized. Compared with the complex and difficult problem of storage and transportation of liquid hydrogen on an airplane, the storage and transportation of liquid ammonia is more mature, safe and convenient.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 illustrates a schematic structural view of a conventional aircraft gas turbine engine;
FIG. 2 is a schematic structural diagram of an aviation power plant using liquid ammonia as fuel according to an embodiment of the present invention;
In the figure: 1-a heat exchanger; 2-a heater; 3-a decomposing furnace; a 4-PSA gas separator; 5-a high pressure hydrogen tank; 6-a high-pressure nitrogen storage tank; 7-liquid ammonia fuel tank.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The aviation power device taking liquid ammonia as fuel is based on the existing aero-engine or hydrogen-fuelled engine, and the aviation power device taking liquid ammonia as fuel is provided with the structures of an engine accessory transmission system, a gas compressor, a combustion chamber, a turbine, an exhaust device and the like of the traditional aero-engine.
The embodiment of the invention provides an aviation power device using liquid ammonia as fuel, which comprises a gas compressor, a combustion chamber, a turbine and an exhaust device, and further comprises: the device comprises a heat exchanger, a heater, a decomposing furnace, a catalyst, a PSA gas separator, a liquid ammonia fuel tank, a hydrogen system and a nitrogen system;
The heat exchanger is integrated with the casing of the compressor, the heater is integrated with the casing of the turbine, and the decomposing furnace is integrated with the casing of the exhaust device;
One path of liquid ammonia in the liquid ammonia fuel tank flows to the heater, and the other path flows to the heat exchanger and then flows into the heater;
Under the action of the high-temperature fuel gas of the turbine, the liquid ammonia flowing through the heater is heated and gasified into ammonia gas;
the heater is communicated with the decomposing furnace, and under the action of the catalyst, the ammonia gas is decomposed into a mixed gas of hydrogen and nitrogen;
The mixed gas is separated into hydrogen and nitrogen through the PSA gas separator, the hydrogen enters the hydrogen system, and the nitrogen enters the nitrogen system; the hydrogen of the hydrogen system is used as fuel for the combustion chamber.
According to the embodiment of the invention, the use of liquid ammonia is increased on the basis of the existing aeroengine or hydrogen fuel engine, the liquid ammonia is gasified into ammonia by utilizing the self heat of the engine during operation, the ammonia is decomposed into the mixed gas of hydrogen and nitrogen under the action of a catalyst, and further the PSA gas separator separates the mixed gas into hydrogen and nitrogen, the hydrogen is respectively input into a hydrogen system and a nitrogen system, and the hydrogen entering the hydrogen system is used as fuel of a combustion chamber, so that the aeroengine has the capability of using ammonia fuel.
Compared with the traditional engine which uses kerosene as non-renewable energy, the engine can not produce carbon dioxide cleanly, and the aviation power device uses ammonia as renewable energy, so that zero carbon emission is realized. Compared with the complex and difficult problem of storage and transportation of liquid hydrogen on an airplane, the storage and transportation of liquid ammonia is more mature, safe and convenient.
The aviation power device using liquid ammonia as fuel is based on the traditional aviation engine, a composition schematic diagram of the traditional aviation gas turbine engine is shown in fig. 1, and the traditional aviation gas turbine engine consists of a gas compressor, a combustion chamber, a turbine, an exhaust device and the like. The functions of each component are as follows: the air compressor increases the pressure of the air flow entering the engine and provides bleed air for air inlet anti-icing, ventilation and heat insulation of the bearing cavity, cooling of the hot end casing and the like; the combustion chamber has the function of combusting fuel oil in high-pressure air flow to form functional fuel gas; the turbine has the function of extracting energy in the fuel gas to form shaft power so as to drive the compressor to compress air flow; the exhaust device is used for guiding the gas after the turbine to be discharged out of the engine to generate thrust.
Referring to fig. 2, a structure and an operating principle of an aviation power plant using liquid ammonia as fuel according to an embodiment of the present invention will be described in detail.
In combination with the embodiment of the invention, the heat exchanger 1 and the casing of the air compressor are combined into a whole, the heater 2 and the casing of the turbine are combined into a whole, the decomposing furnace 3 and the casing of the exhaust device are combined into a whole, the PSA gas separator 4 is used as an accessory to be arranged outside the engine casing of the aviation power device, the liquid ammonia fuel tank 7 is positioned on the aircraft where the aviation power device is positioned, and the hydrogen system and the nitrogen system are arranged outside the engine casing. Preferably, the aeronautical device is an aircraft and the engine of the aeronautical power device is an aircraft engine.
In a preferred embodiment, the hydrogen system comprises a high pressure hydrogen tank 5 and a first control system; the nitrogen system comprises a high-pressure nitrogen storage tank 6, a second control system and a three-way valve.
In a preferred embodiment, the aero-power device further comprises a first pump body, a second pump body and a third pump body.
The liquid ammonia fuel tank 7 is respectively communicated with the heat exchanger 1 and the heater 2 through pipelines, and the first pump body is communicated with a liquid outlet of the liquid ammonia fuel tank 7. Under the pumping action of the first pump body, the liquid ammonia is divided into two paths, and one path of liquid ammonia flows to the heater 2; the other path of liquid ammonia enters the heat exchanger 1 according to the cold energy requirement of the compressor to cool the compressor, so that the engine can be lifted to performance parameters, and the liquid ammonia is converged with the former path of liquid ammonia after exiting from the heat exchanger 1 and flows into the heater 2.
Under the action of high-temperature fuel gas of the turbine, the liquid ammonia flowing through the heater 2 is heated and gasified into ammonia, and the gasified ammonia enters the decomposing furnace 3 under the control of a valve. The heater 2 is communicated with the decomposing furnace 3 through a pipeline, and a valve is arranged between the heater and the decomposing furnace. The decomposing furnace 3 heats and maintains the temperature of the ammonia gas through the high-temperature fuel gas flowing through the exhaust device, and the ammonia gas is chemically decomposed into the mixed gas of the hydrogen gas and the nitrogen gas under the action of the catalyst.
A second pump body is arranged between the decomposing furnace 3 and the PSA gas separator 4 and communicated with the decomposing furnace 3 through a pipeline, and the second pump body is used for inputting the mixed gas of the hydrogen and the nitrogen into the PSA gas separator 4.
The PSA gas separator 4 separates the mixed gas into hydrogen and nitrogen, and the hydrogen and the nitrogen are respectively pressurized by the third pump body and then are conveyed into the hydrogen system and the nitrogen system. The PSA gas separator 4 is connected with the hydrogen system and the nitrogen system through pipelines respectively, a third pump body is arranged on the pipelines between the PSA gas separator 4 and the hydrogen system and the nitrogen system, and the third pump body is arranged behind the PSA gas separator 4 and in front of the hydrogen system and the nitrogen system.
In combination with the embodiment of the invention, the hydrogen entering the hydrogen system after being pressurized by the third pump body is divided into two paths by the valve control, one path of the high-pressure hydrogen flows into the high-pressure hydrogen storage tank 5 until the high-pressure hydrogen storage tank 5 is full, and the other path of the high-pressure hydrogen enters the combustion chamber of the aircraft engine as final fuel for combustion under the control of the first control system. The high-pressure hydrogen storage tank 5 stores hydrogen, and when the aircraft engine is just started, the stored hydrogen participates in the combustion of the combustion chamber in advance to ensure the starting and running of the engine until the aviation power plant taking liquid ammonia as fuel generates enough hydrogen.
In combination with the embodiment of the invention, nitrogen entering the nitrogen system after being pressurized by the third pump body is divided into three paths by the three-way valve, and enters the high-pressure nitrogen storage tank 6 through the first valve and the first pipeline; the turbine enters the turbine through a second valve through a second pipeline under the control of a second control system, and the stator blades of the turbine rotor are cooled; and the air is discharged into the exhaust device to realize boosting through a third valve passing through a third pipeline under the control of the second control system.
In a preferred embodiment, the high-pressure nitrogen tank 6 stores nitrogen, which is used to displace, blow off the hydrogen in the hydrogen line into the combustion chamber when the aircraft engine is started or stopped, in order to prevent explosion risks caused by hydrogen residues. During engine starting of an aircraft, the stored nitrogen is also used for blowing the turbine to drive the engine rotor to realize engine starting. When the boost of the aircraft engine is large, nitrogen in the high-pressure nitrogen tank 6 can be used for discharging into the exhaust device to realize the boost. Preferably, under the action of the second control system, the nitrogen in the high-pressure nitrogen tank 6 is also used for being mixed into the hydrogen pipeline of the hydrogen entering the combustion chamber so as to dilute the flow of the hydrogen and reduce the risks of hydrogen tempering and thermal ablation of the combustion chamber.
Compared with the prior art, the embodiment of the invention has the following advantages:
(1) Compared with the traditional kerosene which is a non-renewable energy source, the engine can not produce carbon dioxide cleanly, and the ammonia is a renewable energy source and burns zero carbon.
(2) Compared with the traditional aeroengine, the turbine component of the aeroengine needs to be cooled by introducing air of the compressor, and the engine is cooled by nitrogen which is a byproduct of ammonia, so that the engine can further improve performance parameters.
(3) Compared with the difficult problems of hydrogen tempering and thermal ablation faced by the current direct hydrogen engine, the engine can realize the flow of diluted hydrogen of nitrogen and reduce the risks of hydrogen tempering and thermal ablation of a combustion chamber.
(4) Compared with a hydrogen-burning engine which needs to be provided with a special nitrogen source, the invention can self-control nitrogen for replacing and blowing off the hydrogen in the hydrogen pipeline in the start-stop process of the engine so as to prevent explosion risk caused by hydrogen residue.
(5) Compared with the complex and difficult problem of storage and transportation of liquid hydrogen on an airplane, the storage and transportation of liquid ammonia is more mature, safe and convenient.
The working process of the aviation power plant using liquid ammonia as fuel provided by the embodiment of the invention is described next in combination with the embodiment of the invention. Next, an engine of an aircraft will be described as an example.
When the engine is started, nitrogen in the high-pressure nitrogen storage tank 6 is replaced and hydrogen in a hydrogen pipeline entering the combustion chamber is blown off, so that explosion risks caused by hydrogen residues are prevented; the stored nitrogen is also used for blowing the turbine to drive the engine rotor to realize engine starting.
The hydrogen in the high-pressure hydrogen storage tank 5 participates in the starting and running of the combustion guaranteeing engine in advance until the liquid ammonia in the liquid ammonia fuel tank 7 generates enough hydrogen and nitrogen through a heat exchanger, a heater, a decomposing furnace and a PSA gas separator, one path of generated hydrogen flows into the high-pressure hydrogen storage tank 5, and the other path of generated hydrogen is controlled by a first control system to enter a combustion chamber of the engine to be used as final fuel for combustion.
The generated nitrogen is divided into three paths by valve control, and enters a high-pressure nitrogen storage tank 6 through a first valve and a first pipeline; the turbine enters the turbine through a second valve through a second pipeline under the control of a second control system, and the stator blades of the turbine rotor are cooled; and the air is discharged into the exhaust device to realize boosting through a third valve passing through a third pipeline under the control of the second control system. If the aircraft needs a larger engine boosting, nitrogen in the high-pressure nitrogen storage tank 6 can also be discharged into the exhaust device to realize short-time large boosting. Wherein, the nitrogen in the high-pressure nitrogen storage tank 6 can be mixed into the hydrogen pipeline of the hydrogen entering the combustion chamber by the second control system according to the requirement, so as to dilute the flow of the hydrogen and reduce the risks of hydrogen tempering and thermal ablation of the combustion chamber.
After the engine is stopped, the nitrogen in the high-pressure nitrogen storage tank 6 is used for replacing and blowing off the hydrogen in the hydrogen pipeline entering the combustion chamber, so as to prevent explosion risks caused by hydrogen residues.
Although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. The utility model provides an use aviation power device of liquid ammonia as fuel, includes compressor, combustion chamber, turbine and exhaust apparatus, its characterized in that still includes: the device comprises a heat exchanger (1), a heater (2), a decomposing furnace (3), a catalyst, a PSA gas separator (4), a liquid ammonia fuel tank (7), a hydrogen system and a nitrogen system;
The heat exchanger (1) is integrated with the casing of the compressor, the heater (2) is integrated with the casing of the turbine, and the decomposing furnace (3) is integrated with the casing of the exhaust device;
One path of liquid ammonia in the liquid ammonia fuel tank (7) flows to the heater (2), and the other path flows to the heat exchanger (1) and then flows into the heater (2);
Under the action of the high-temperature fuel gas of the turbine, the liquid ammonia flowing through the heater (2) is heated and gasified into ammonia gas;
the heater (2) is communicated with the decomposing furnace (3), and under the action of the catalyst, the ammonia gas is decomposed into a mixed gas of hydrogen and nitrogen;
The mixed gas is separated into hydrogen and nitrogen through the PSA gas separator (4), the hydrogen enters the hydrogen system, and the nitrogen enters the nitrogen system; the hydrogen of the hydrogen system is used as fuel for the combustion chamber.
2. The aero power plant of claim 1, wherein the hydrogen system comprises: a high pressure hydrogen tank (5) and a first control system; one path of the hydrogen separated from the PSA gas separator (4) flows into the high-pressure hydrogen storage tank (5), and the other path enters the combustion chamber to be used as fuel under the control of the first control system.
3. Aero power plant according to claim 2, wherein said high pressure hydrogen tank (5) stores hydrogen, which stored hydrogen is pre-engaged in the combustion of said combustion chamber to ensure the starting and running of the engine upon the engine start of said aero power plant.
4. The aero-power plant of claim 1, wherein the nitrogen system comprises: a high-pressure nitrogen storage tank (6), a second control system and a three-way valve;
Nitrogen separated from the PSA gas separator (4) enters the high pressure nitrogen tank (6) through a first valve via a first line; through a second valve and through a second pipeline, entering the turbine under the control of the second control system; and the air is discharged into the exhaust device to realize boosting under the control of the second control system through a third valve passing through a third pipeline.
5. Aero power plant according to claim 4, wherein the high pressure nitrogen tank (6) stores nitrogen for displacing, blowing off hydrogen in the hydrogen line into the combustion chamber when the aero power plant engine is started or stopped;
when the engine of the aviation power device is started, the stored nitrogen is used for blowing the turbine to drive the engine rotor so as to realize engine starting.
6. Aero power plant according to claim 4, wherein the nitrogen in the high pressure nitrogen tank (6) is used for discharging into the exhaust device for increasing the thrust when the increase of the aero power plant is large.
7. Aero power plant according to claim 4, wherein under the action of said second control system, nitrogen in said high pressure nitrogen tank (6) is used to blend into the hydrogen line of said hydrogen into said combustion chamber to dilute the flow of said hydrogen.
8. The aero-power plant of claim 1, further comprising: the first pump body, the second pump body and the third pump body;
the first pump body is communicated with a liquid outlet of the liquid ammonia fuel tank (7) and is used for extracting the liquid ammonia to enter the heat exchanger (1) and the heater (2) respectively;
the second pump body is positioned between the decomposing furnace (3) and the PSA gas separator (4) and is used for inputting the mixed gas decomposed into hydrogen and nitrogen into the PSA gas separator (4);
the third pump body is arranged behind the PSA gas separator (4), and before the hydrogen system and the nitrogen system, the third pump body is used for pressurizing separated hydrogen and nitrogen and then respectively inputting the hydrogen system and the nitrogen system.
9. Aero power plant according to claim 1, wherein said PSA gas separator (4) is mounted as an accessory outside the engine casing of said aero power plant.
10. Aero power plant according to claim 1, wherein said liquid ammonia fuel tank (7) is located on the aircraft in which said aero power plant is located, said hydrogen system and said nitrogen system being mounted outside the engine casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410173210.4A CN118066017A (en) | 2024-02-07 | 2024-02-07 | Aviation power device using liquid ammonia as fuel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410173210.4A CN118066017A (en) | 2024-02-07 | 2024-02-07 | Aviation power device using liquid ammonia as fuel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118066017A true CN118066017A (en) | 2024-05-24 |
Family
ID=91110669
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410173210.4A Pending CN118066017A (en) | 2024-02-07 | 2024-02-07 | Aviation power device using liquid ammonia as fuel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118066017A (en) |
-
2024
- 2024-02-07 CN CN202410173210.4A patent/CN118066017A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11041439B2 (en) | Hybrid expander cycle with turbo-generator and cooled power electronics | |
| US20200088098A1 (en) | Hybrid expander cycle with pre-compression cooling and turbo-generator | |
| US20200200086A1 (en) | High speed propulsion system with inlet cooling | |
| US11828200B2 (en) | Hydrogen-oxygen fueled powerplant with water and heat recovery | |
| CN106014637A (en) | Air precooling compression aircraft engine and hypersonic velocity aircraft | |
| CN104595032B (en) | A kind of multi-fan super large bypass ratio turbine push system | |
| US12037127B2 (en) | Hydrogen-fuelled aircraft power system | |
| US11920526B1 (en) | Inter-cooled preheat of steam injected turbine engine | |
| US20240010352A1 (en) | Hybrid electric power for turbine engines having hydrogen fuel systems | |
| EP4227512A1 (en) | Hydrogen-oxygen fueled powerplant with water and heat recovery | |
| CN118066017A (en) | Aviation power device using liquid ammonia as fuel | |
| WO2023216278A1 (en) | Electric energy turbine engine | |
| RU2376483C1 (en) | Nuclear gas turbine engine with afterburning | |
| EP4407161A1 (en) | Inter-turbine burner in recuperation cycle engine | |
| CN116677498B (en) | Novel hypersonic combined engine based on hydrogen energy | |
| US20240133340A1 (en) | Combined gas turbine engine and fuel cell | |
| US20240133343A1 (en) | Gas turbine engine fuel system | |
| US20240254898A1 (en) | Power electronics waste heat recovery in recuperation cycle | |
| US20240141831A1 (en) | Hydrogen steam injected turbine engine with cooled cooling air | |
| US20240141837A1 (en) | Reverse flow hydrogen steam injected turbine engine | |
| RU2392461C1 (en) | Power plant of nuclear gas turbine locomotive | |
| US20240254920A1 (en) | Hydrogen Steam Injected Turbine Engine with Turboexpander Heat Recovery | |
| CN118148779A (en) | Aircraft hydrogen-burning power system and aircraft | |
| CN118309562A (en) | Comprehensive thermal management system for turbine punching combined engine | |
| CN116498437A (en) | Implementation method of general internal circulation turbine engine for air, water and land |
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 |