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

共 50 条

[31] Hydrogen-fueled pollution-free transportation
Oman, H
IEEE AEROSPACE AND ELECTRONIC SYSTEMS MAGAZINE, 2002, 17 (03) : 34 - 40
[32] STUDY ON HYDROGEN-FUELED DIESEL COMBUSTION.
Ikegami, Makoto
Miwa, Kei
Shioji, Masahiro
Esaki, Masataka
Bulletin of the JSME, 1980, 23 (181): : 1187 - 1193
[33] CASE FOR HYDROGEN-FUELED TRANSPORT AIRCRAFT.
Brewer, G.Daniel
Astronautics and Aeronautics, 1974, 12 (05): : 40 - 51
[34] DRAG REDUCTION BY COOLING IN HYDROGEN-FUELED AIRCRAFT
RESHOTKO, E
JOURNAL OF AIRCRAFT, 1979, 16 (09): : 584 - 590
[35] Wind Tunnel Testing of a Detonation Ramjet Model at Approach Air Stream Mach Number 5.7 and a Stagnation Temperature of 1500 K
Frolov, S. M.
Zvegintsev, V., I
Ivanov, V. S.
Aksenov, V. S.
Shamshin, I. O.
Vnuchkov, D. A.
Nalivaichenko, D. G.
Berlin, A. A.
Fomin, V. M.
Shiplyuk, A. N.
Yakovlev, N. N.
DOKLADY PHYSICAL CHEMISTRY, 2018, 481 : 100 - 103
[36] Wind Tunnel Testing of a Detonation Ramjet Model at Approach Air Stream Mach Number 5.7 and a Stagnation Temperature of 1500 K
S. M. Frolov
V. I. Zvegintsev
V. S. Ivanov
V. S. Aksenov
I. O. Shamshin
D. A. Vnuchkov
D. G. Nalivaichenko
A. A. Berlin
V. M. Fomin
A. N. Shiplyuk
N. N. Yakovlev
Doklady Physical Chemistry, 2018, 481 : 100 - 103
[37] Updated conceptual design of hydrogen/ethylene fueled detonation ramjet: Test fires at Mach 1.5, 2.0, and 2.5
Ivanov, V. S.
Frolov, S. M.
Zangiev, A. E.
Zvegintsev, V. I.
Shamshin, I. O.
AEROSPACE SCIENCE AND TECHNOLOGY, 2022, 126
[38] Continuous Detonation Combustion of Hydrogen: Results of Wind Tunnel Experiments
Frolov, S. M.
Zvegintsev, V., I
Ivanov, V. S.
Aksenov, V. S.
Shamshin, I. O.
Vnuchkov, D. A.
Nalivaichenko, D. G.
Berlin, A. A.
Fomin, V. M.
COMBUSTION EXPLOSION AND SHOCK WAVES, 2018, 54 (03) : 357 - 363
[39] Hydrogen-Fueled Regenerative Burners in a Reheating Furnace
Karambelkar, Anurag
Uzor, Chukwunedum
Walla, Nicholas
Silaen, Armin
Johnson, Kurt
Zhou, Chenn
PROCEEDINGS OF ASME 2023 HEAT TRANSFER SUMMER CONFERENCE, HT2023, 2023,
[40] Continuous Detonation Combustion of Hydrogen: Results of Wind Tunnel Experiments
S. M. Frolov
V. I. Zvegintsev
V. S. Ivanov
V. S. Aksenov
I. O. Shamshin
D. A. Vnuchkov
D. G. Nalivaichenko
A. A. Berlin
V. M. Fomin
Combustion, Explosion, and Shock Waves, 2018, 54 : 357 - 363

← 1 2 3 4 5 →