Numerical and experimental investigation on detonation tube for simulating the rocket exhaust gas at high enthalpy shock tunnel

Kazuma Shigematsu, Akiko Matsuo, Katsuhiro Itoh, Tomoyuki Komuro

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

The numerical investigation on the detonation tube for simulating the exhaust gas of rocket combustor are examined with the various cross-sectional area ratio A/A*, initial gas pressure and equivalence ratio. Preliminary experiment on detonation tube is also conducted to obtain its primary operation characteristics for the engine test. Numerical study suggests the operation time t, which is normalized by the length of the detonation tube, as the duration time of plateau pressure and presented for each initial pressure and equivalence ratio of the detonation tube. The effect of A/A* is examined by changing the geometric term of governing equation, and the plateau pressure is observed in all A/A* cases. As the A/A* increases, the plateau pressure increases due to the regulation effect of the throat. The throat gas composition and pressure are presented for each initial gas condition, and the linear relation of the throat pressure and the initial pressure are exhibited. In the experiment, the pressure history shows the pressure rise due to the exhaust gas through the detonation tube. A typical DDT phenomenon is observed in the detonation tube, and it causes the reduction of the operation time τ predicted by numerical results.

Original languageEnglish
Title of host publication16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
Publication statusPublished - 2009
Event16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference - Bremen, Germany
Duration: 2009 Oct 192009 Oct 22

Other

Other16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
CountryGermany
CityBremen
Period09/10/1909/10/22

Fingerprint

Detonation
Rockets
Exhaust gases
Enthalpy
Tunnels
Gases
Combustors
Experiments
Engines

ASJC Scopus subject areas

  • Engineering(all)

Cite this

Shigematsu, K., Matsuo, A., Itoh, K., & Komuro, T. (2009). Numerical and experimental investigation on detonation tube for simulating the rocket exhaust gas at high enthalpy shock tunnel. In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference [2009-7339]

Numerical and experimental investigation on detonation tube for simulating the rocket exhaust gas at high enthalpy shock tunnel. / Shigematsu, Kazuma; Matsuo, Akiko; Itoh, Katsuhiro; Komuro, Tomoyuki.

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009. 2009-7339.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Shigematsu, K, Matsuo, A, Itoh, K & Komuro, T 2009, Numerical and experimental investigation on detonation tube for simulating the rocket exhaust gas at high enthalpy shock tunnel. in 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference., 2009-7339, 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, Germany, 09/10/19.
Shigematsu K, Matsuo A, Itoh K, Komuro T. Numerical and experimental investigation on detonation tube for simulating the rocket exhaust gas at high enthalpy shock tunnel. In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009. 2009-7339
Shigematsu, Kazuma ; Matsuo, Akiko ; Itoh, Katsuhiro ; Komuro, Tomoyuki. / Numerical and experimental investigation on detonation tube for simulating the rocket exhaust gas at high enthalpy shock tunnel. 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009.
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