RU2541526C1 - Fuel for hypersonic athodyd - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention describes the fuel for hypersonic athodyd based on T-10 hydrocarbon fuel. Note here that fuel containing 1.7-dimethyl dicarbo-closo-octocarboran at the following ratio of components, wt %: 1.7-dimethyl dicarbo-closo-octocarboran - 70, T-10 fuel - 30.

EFFECT: invariable physical-chemical properties in the wide temperature range.

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Description

The present invention relates to fuels for ramjet engines, in particular to compositions based on organoboron compounds with high specific heat of combustion.

It is known that liquefied hydrogen and methane [2, 3], as well as hydrocarbon fuels of the JP-7, JP-10 grades [2, 3, 4] were proposed as fuel for the scramjet engine. Liquid boron-containing fuels are known, which are mixtures of isopropylmethacarborane with hydrocarbons: toluene, cyclin, quadran, naphthyl, alkyl benzene derivatives, as well as T-6, RJ-5 fuels and some others [5].

The closest analogue of the claimed technical solution is “Composition for solid fuel” (“Composition for solid fuel”) [6]. The specified technical solution has significant advantages over previous analogues, contains in its composition carboran (C ₂ B ₁₀ H ₁₂ ) and its derivatives in the amount of 4-15% of the mass. The disadvantages of solid fuels for ramjet engines are their low energy characteristics in comparison with ramjet engines on liquid fuel and atmospheric air, as well as increased sensitivity to mechanical and temperature influences. In addition, at hypersonic flight speeds, it is necessary to cool the engine structural elements, including due to the circulation of liquid fuel in the cooling jacket.

An object of the present invention is to provide fuel for a hypersonic ramjet engine with increased energy intensity, retaining its physicochemical properties in a wide temperature range due to the combination of energy-intensive low-freezing and highly heat-stable fuel 1,7-dimethyldicarb-closo-octocarborane and hydrocarbon fuel T -10, in the ratio, wt.%:

1,7-dimethyldicarb-closo-octocarborane 70 fuel T-10 thirty

A comparative analysis of the technical solution with the known one shows that the claimed technical solution is characterized in that it is proposed to use a mixture of T-10 fuel and 1,7-dimethyldicarb-closo-octocarborane as a fuel for a hypersonic ramjet engine.

With an increase in the flight speed of an aircraft equipped with ramjet engine, the relative heating of the air in the engine θ decreases, equal to the ratio of the temperature in the combustion chamber to the braking temperature of cold air at the inlet of the air intake, due to an increase in the braking temperature of cold air. With a sufficient increase in flight speed, a "thermal death" of the jet engine occurs, since relative heating approaches unity [2].

1,7-dimethyldicarb-closo-octocarborane has a high specific heat of combustion ≈ 50,000 kJ / kg, high thermal stability, and also a fairly low melting point (-60 ° C) compared with other representatives of this class of compounds. The mixture of 1,7-dimethyldicarb-closo-octocarborane with T-10 is carried out in order to give the fuel optimal operating properties.

The efficiency of using fuel in a hypersonic ramjet engine will become apparent when calculating the relative heating θ for two standard hydrocarbon fuels T-6, T-10 and fuel consisting of 1,7-dimethyldicarb-closo-octocarborane (70 wt.%) And T -10 (30 wt.%) (For ideal ramjet). The obtained calculated data are presented in table 1.

This fuel composition is supposed to be used in hypersonic ramjet engines of aviation and space rocket technology.

The presented fuel composition solves the problem of insufficient heat production of fuels proposed for use in the scramjet engine for flight speeds of 6-10M, as well as insufficient physical and chemical stability during operation in a wide temperature range.

Information sources

1. R. Grimes Karborany: Monograph. - M .: MIR Publishing House, 1974.

2. Artemov O.A. Ramjet engines (calculation of characteristics): Monograph. - M .: Sputnik + Company, 2006.

3. Tom Anderlis. The way to hyper plane // The Industrial Physicist American Institute of Physics, Dean Andreadis, March 2005.

4. Petrukhin N.V., Sergeev S.M., Prokopenko O.A. Fuel requirements for hypersonic engines of rocket and space technology // Collection of scientific papers of FSUE NPO named after S.A. Lavochkina ”on current issues in the design of space systems and complexes. - M.: FSUE NPO them. S.A. Lavochkina, 2011.

5. Bakulin V.N., Dubovkin N.F., Kotov V.N., Sorokin V.A., Frantskevich V.P., Yanovsky L.S. Energy-intensive fuels for aircraft and rocket engines / Ed. L.S. Yanovsky. - M .: FIZMATLIT, 2009.

6. Patent of Russia No. 2288207.

Claims (1)

Fuel for a hypersonic ramjet engine based on a T-10 hydrocarbon fuel, characterized in that a mixture of T-10 fuel and 1,7-dimethyldicarb-closo-octocarborane is prepared to obtain a composition, wt.%:
1,7-dimethyldicarb-closo-octocarborane 70 fuel T-10 thirty