Hydrogen-Fueled Detonation Ramjet Model: Wind Tunnel Tests

被引：0

作者：

Ivanov, V. S. ^{[1
]}

Frolov, S. M. ^{[1
]}

Zvegintsev, V. I. ^{[2
]}

Aksenov, V. S. ^{[1
]}

Shamshin, I. O. ^{[1
]}

Vnuchkov, D. A. ^{[2
]}

Nalivaichenko, D. G. ^{[2
]}

Berlin, A. A. ^{[1
]}

Fomin, V. M. ^{[2
]}

Shiplyuk, A. N. ^{[2
]}

Yakovlev, N. N. ^{[3
]}

机构：

[1] Russian Acad Sci ICP RAS, Semenov Inst Chem Phys, Moscow, Russia

[2] Khristianovich Inst Theoret & Appl Mech, 4-1 Inst Skaya Str, Novosibirsk 630090, Russia

[3] Joint Stock Co Turaevo Machine Bldg Design Bur So, Lytkarino, Russia

来源：

INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2018) | 2018年 / 2027卷

基金：

俄罗斯科学基金会;

关键词：

EXPERIMENTAL PROOF; ENERGY EFFICIENCY; AIR; COMBUSTION; PROPAGATION; ENGINE;

D O I：

10.1063/1.5065135

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

Experimental studies of an axisymmetric hydrogen-fueled detonation ramjet model 1.05-meter long and 0.31 in in diameter with an expanding annular combustor were performed in a pulse wind tunnel under conditions of approaching air stream Mach number M = 4, 5, 6 and 8 with the stagnation temperature T-0 = 293 K and M = 5.7 with T-0 = 1500 K. In a supersonic air flow entering the combustor, stationary continuous and longitudinally pulsating modes of hydrogen detonation were obtained depending on the test conditions. The maximum measured values of the fuel-based specific impulse were 3600 s for the tests with T-0 = 293 K and 3300 s for the tests with T-0 = 1500 K.

引用

页数：12

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