CN104974800A - Military airplane turbine engine fuel - Google Patents
Military airplane turbine engine fuel Download PDFInfo
- Publication number
- CN104974800A CN104974800A CN201510390950.4A CN201510390950A CN104974800A CN 104974800 A CN104974800 A CN 104974800A CN 201510390950 A CN201510390950 A CN 201510390950A CN 104974800 A CN104974800 A CN 104974800A
- Authority
- CN
- China
- Prior art keywords
- fuel
- turbine engine
- gunpowder
- aviation kerosene
- explosive
- 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
Landscapes
- Liquid Carbonaceous Fuels (AREA)
Abstract
The invention discloses a military airplane turbine engine fuel which is composed of the following components: (1) aviation kerosene; (2) a mixture of one or more of an explosive, gunpowder and a metal fuel. Compared with aviation kerosene, the military airplane turbine engine fuel enables the mass of the carried fuel to be greatly reduced, and greatly improves the performance of a warplane. A principle is simple, the preparation raw materials are cheap, the military airplane turbine engine fuel can generate greater pushing force compared with the general aviation kerosene with the same mass, a warplane engine using the military airplane turbine engine fuel has less carried fuel compared with a warplane engine using the aviation kerosene, the airplane overall weight is reduced, the speed is improved, and the cost can be saved.
Description
Technical field
The invention belongs to Material Field, particularly a kind of aircraft engine fuel.
Background technology
At present, along with the development of science and technology, the change of world situation, high-performance fighter aircraft of new generation is all being greatly developed in countries in the world, at air fighter design aspect, China also marches at the forefront of the world, but China can not provide suitable aircraft engine to the high-performance fighter aircraft designed, the engine complete dependence on import substantially of new-generation fighter, makes the development of Chinese fighter be limited by other country.High-performance enginer requires to have high thrust-weight ratio (engine produces the ratio of thrust and own wt), each state uses materials and structures to design two aspects to improve the performance of engine from engine in the world, the current state of the art of China does not also reach the requirement designing and manufacturing military aircraft engine advanced in the world, and west gap is probably in 20 years.
Summary of the invention
The object of this invention is to provide a kind of military aircraft turbine engine fuel, with the problem that the thrust-weight ratio solving current fuel existence is low.
For achieving the above object, the technical solution used in the present invention is:
A kind of military aircraft turbine engine fuel, it is composed of the following components:
(1) aviation kerosene; (2) one or more the mixture in explosive, gunpowder, metallic fuel.
Further, in above-mentioned military aircraft turbine engine fuel, according to weight percent, each component is: aviation kerosene is 0% ~ 99%, but does not comprise 0; One or more mixture in explosive, gunpowder, metallic fuel is 1% ~ 100% altogether, but does not comprise 100%.
Further, described component (2) be explosive, a kind of in gunpowder, metallic fuel or wherein at least two kinds with the mixtures of arbitrary proportion mixing.
Further, the common percentage of liveweight ratio of described explosive, gunpowder or metallic fuel is not less than 5%.
Further, the common percentage of liveweight ratio of described explosive, gunpowder or metallic fuel is not less than 10%.
Further, described metallic fuel is combustible micron order or nanoscale metal particles.
Further, described metallic fuel is one or more mixing of nano level aluminium powder, nano level lithium powder, nano level beryllium powder.
The preparation method of above-mentioned military aircraft turbine engine fuel is: proportionally, by each component Homogeneous phase mixing.
Principle of the present invention is: fuel of the present invention is by aviation kerosene, and explosive, gunpowder, one or more mixture composition in metallic fuel, wherein, aviation kerosene plays the effect of dilution explosive, gunpowder or metallic fuel, the energy that explosive, gunpowder or metallic fuel produce when burning is tens of hundreds of times of aviation kerosene, when with aviation kerosene equal in quality, the present invention can improve aeroengine thrust several times to decades of times, when requiring identical thrust.
The invention has the beneficial effects as follows:
The present invention compared with aviation kerosene, can reduce and carry quality of fuel greatly, improves the performance of air fighter greatly.
The principle of the invention is simple, making cost of material is cheap, and the present invention of equal in quality can produce more high thrust compared with general aviation kerosene, and it is less that fighter engine uses the present invention to carry fuel compared with use aviation kerosene, alleviate overall aircraft weight, improve speed and can cost be saved.
Embodiment
Below in conjunction with specific embodiment, the present invention is further described.
Embodiment 1
According to weight percent, aviation kerosene is 99%, and the mixture of explosive, gunpowder, metallic fuel is 1% altogether.
Wherein, metallic fuel is nano level aluminium powder, and explosive adopts TNT, and gunpowder is black powder.
Proportionally, by each component Homogeneous phase mixing.
The aircraft engine thrust that the fuel of the present embodiment the produces institute that is aviation kerosene produces 1.05-2 times of thrust.
Embodiment 2
According to weight percent, aviation kerosene is 50%, and the mixture of explosive, gunpowder, metallic fuel is 50% altogether.
Wherein, metallic fuel is nano level lithium powder, and explosive adopts hexogen, and gunpowder is black powder.
Proportionally, by each component Homogeneous phase mixing.
The aircraft engine thrust that the fuel of the present embodiment the produces institute that is aviation kerosene produces 5-50 times of thrust.
Embodiment 3
According to weight percent, aviation kerosene is 95%, and the mixture of explosive, metallic fuel is 5% altogether.
Wherein, metallic fuel is nano level beryllium powder, and explosive adopts C4.
Proportionally, by each component Homogeneous phase mixing.
The aircraft engine thrust that the fuel of the present embodiment the produces institute that is aviation kerosene produces 1.3-6 times of thrust.
Embodiment 4
According to weight percent, aviation kerosene is 90%, and the mixture of gunpowder, metallic fuel is 10% altogether.
Wherein, metallic fuel is nano level aluminium powder, and gunpowder is black powder.
Proportionally, by each component Homogeneous phase mixing.
The aircraft engine thrust that the fuel of the present embodiment the produces institute that is aviation kerosene produces 1.5-11 times of thrust.
Embodiment 5
According to weight percent, aviation kerosene is 85%, and metallic fuel is 15%.
Wherein, metallic fuel is nano level lithium powder.
Proportionally, by each component Homogeneous phase mixing.
The aircraft engine thrust that the fuel of the present embodiment the produces institute that is aviation kerosene produces 2-15 times of thrust.
Embodiment 6
According to weight percent, aviation kerosene is 60%, and the mixture of explosive, gunpowder is 40% altogether.
Wherein, explosive adopts TNT, and gunpowder is black powder.
Proportionally, by each component Homogeneous phase mixing.
The aircraft engine thrust that the fuel of the present embodiment the produces institute that is aviation kerosene produces 3-40 times of thrust.
Embodiment 7
According to weight percent, aviation kerosene is 98%, and explosive is 2%.
Wherein, explosive adopts nitrocotton.
Proportionally, by each component Homogeneous phase mixing.
The aircraft engine thrust that the fuel of the present embodiment the produces institute that is aviation kerosene produces 1.1-3 times of thrust.
Embodiment 8
According to weight percent, aviation kerosene is 80%, and gunpowder is 20%.
Wherein, gunpowder is black powder.
Proportionally, by each component Homogeneous phase mixing.
The aircraft engine thrust that the fuel of the present embodiment the produces institute that is aviation kerosene produces 1.5-4 times of thrust.
The above is only the preferred embodiment of the present invention; be noted that for those skilled in the art; under the premise without departing from the principles of the invention, can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (7)
1. a military aircraft turbine engine fuel, is characterized in that: it is composed of the following components: (1) aviation kerosene; (2) one or more the mixture in explosive, gunpowder, metallic fuel.
2. military aircraft turbine engine fuel as claimed in claim 1, it is characterized in that: according to weight percent, each component is: aviation kerosene is 0% ~ 99%, but does not comprise 0; One or more mixture in explosive, gunpowder, metallic fuel is 1% ~ 100% altogether, but does not comprise 100%.
3. military aircraft turbine engine fuel as claimed in claim 1 or 2, is characterized in that: described component (2) is explosive, a kind of in gunpowder, metallic fuel or wherein at least two kinds with the mixtures of arbitrary proportion mixing.
4. military aircraft turbine engine fuel as claimed in claim 3, is characterized in that: described explosive, gunpowder or metallic fuel altogether percentage of liveweight ratio are not less than 5%.
5. military aircraft turbine engine fuel as claimed in claim 4, is characterized in that: described explosive, gunpowder or metallic fuel altogether percentage of liveweight ratio are not less than 10%.
6. military aircraft turbine engine fuel as claimed in claim 1, is characterized in that: described metallic fuel is combustible micron order or nanoscale metal particles.
7. military aircraft turbine engine fuel as claimed in claim 1, is characterized in that: described metallic fuel is one or more mixing of nano level aluminium powder, nano level lithium powder, nano level beryllium powder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510390950.4A CN104974800A (en) | 2015-07-06 | 2015-07-06 | Military airplane turbine engine fuel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510390950.4A CN104974800A (en) | 2015-07-06 | 2015-07-06 | Military airplane turbine engine fuel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104974800A true CN104974800A (en) | 2015-10-14 |
Family
ID=54271771
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510390950.4A Pending CN104974800A (en) | 2015-07-06 | 2015-07-06 | Military airplane turbine engine fuel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104974800A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101333467A (en) * | 2007-06-28 | 2008-12-31 | 詹姆士·肯尼思·桑德斯 | Nano-sized metal and metal oxide particles for more complete fuel combustion |
| CN101358150A (en) * | 2007-08-04 | 2009-02-04 | 左天德 | Engine fuel using explosive and powder as principal raw material |
| US20100084313A1 (en) * | 2008-10-06 | 2010-04-08 | Helton Terry E | Process to improve jet fuels |
| CN103265983A (en) * | 2013-06-08 | 2013-08-28 | 江苏大学 | High-efficiency nanometer fuel oil |
-
2015
- 2015-07-06 CN CN201510390950.4A patent/CN104974800A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101333467A (en) * | 2007-06-28 | 2008-12-31 | 詹姆士·肯尼思·桑德斯 | Nano-sized metal and metal oxide particles for more complete fuel combustion |
| CN101358150A (en) * | 2007-08-04 | 2009-02-04 | 左天德 | Engine fuel using explosive and powder as principal raw material |
| US20100084313A1 (en) * | 2008-10-06 | 2010-04-08 | Helton Terry E | Process to improve jet fuels |
| CN103265983A (en) * | 2013-06-08 | 2013-08-28 | 江苏大学 | High-efficiency nanometer fuel oil |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109305869B (en) | Carborane propellant and preparation method thereof | |
| CN109384636B (en) | Hydrocarbon fuel-rich propellant and preparation method thereof | |
| CN103638628A (en) | Application of compound type D-class dry powder extinguishing agent in fire disaster of lithium metal and derivative thereof | |
| CN104030866B (en) | Seismic charge prepared by waste hydroxyl-terminated polyb (HTPB) solid propellant slurry and application thereof | |
| CN104557351B (en) | A kind of composite smoke fire type high-energy combustion agent | |
| CN104974800A (en) | Military airplane turbine engine fuel | |
| CN110981665B (en) | Boron-containing fuel-rich propellant for platform combustion | |
| CN102826942B (en) | Smokeless firework propellant | |
| CN111013078A (en) | Semi-solid fire extinguishing agent for forest blasting fire extinguishing bomb and preparation method thereof | |
| CN111892466A (en) | High-density high-energy metal fuel | |
| CN103333036B (en) | A kind of low critical pressure double base propellant | |
| CN201974110U (en) | Cruise target missile | |
| CN105565266B (en) | A kind of hypersonic aircraft carries hydrogen fuel with heat absorbing type | |
| CN102864403A (en) | Granular feeds with nano composite structures and preparation method thereof | |
| CN109467492B (en) | Negative pressure intensity index propellant | |
| Zhou et al. | Aerodynamics design of two-stage vane-less counter-rotating turbinec | |
| CN110218133A (en) | A kind of explosive and its preparation method and application | |
| CN111892966B (en) | High-energy metal fuel for boron-containing propellant | |
| Trevethan | " Brigadization" of the PLA Air Force | |
| RU2663037C2 (en) | Composition of the simplest explosive and the method of its implementation | |
| CN103305295A (en) | Diesel oil emulsifier | |
| Yuan et al. | Effect of Nano Combustion Modifier on Combustion Properties of DB and CMDB-propellant | |
| CN103626614B (en) | Low explosion velocity explosive for explosive welding | |
| CN103467923A (en) | Epoxy resin material compatible with liquid oxygen and preparation method of epoxy resin material | |
| CN108976096A (en) | A kind of ignition powder for no cutting knife |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20151014 |