Detonation Combustion of Carbon-free Ammonia/Hydrogen - Air Mixtures
F. A. Bykovsky1, S. A. Zhdan1,2, E. F. Vedernikov1, A. N. Samsonov1
1Lavrentyev Institute of Hydrodynamics, Siberian Branch, Russian Academy of Sciences, Novosibirsk, Russia
2Kutateladze Institute of Thermal Physics, Siberian Branch, Russian Academy of Sciences, Novosibirsk, Russia
Keywords: continuous spin detonation, continuous multifront detonation, ammonia, air, hydrogen, transverse detonation waves, annular combustion chamber
Abstract
Continuous spin and multifront detonation modes of carbon-free ammonia/hydrogen-air fuel-air mixtures were implemented for the first time in a flow-through annular cylindrical combustion chamber with a diameter of 503 mm. Binary fuel (ammonia/hydrogen) with H2 mass fractions in the fuel of 0.105 ÷ 0.485 was studied in the range of specific mixture flow rates of 22 ÷ 347 kg/(s ∙ m2) at an excess fuel coefficient of φ= 0.47 ÷ 1.55. In ammonia/hydrogen --- air mixtures with fuel of three compositions NH3 + 8H2, NH3 + 4H2 and NH3 + 2H2, single-wave and two-wave modes of continuous spin detonation with a velocity of 1.15 ÷ 1.59 km/s and a wave rotation frequency of 0.73 ÷ 1.81 kHz at φ= 0.73 ÷ 1.2 are realized, and for the NH3 + H2 composition --- continuous multifront detonation with two counter transverse detonation waves with a frequency of about 1.0 kHz at φ= 0.72 ÷ 1.0. The region of implementation of continuous spin detonation and continuous multifront detonation modes is determined depending on the ammonia content in the binary fuel and on the pressure in the air manifold. High-frequency sensors measured pressure profiles in the air manifold and in the combustion chamber in the region of rotation of transverse detonation waves. Thrust forces and specific impulses were determined. The highest thrust impulses obtained in the chamber were 2300, 1500, 1350, and 900 s for mixtures with hydrogen mass fractions in the binary fuel of 0.485, 0.32, 0.19, and 0.105.
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