Abstract
Ignition experiments of Hydrogen and Ethylene were performed on direct-connected pulse combustion facility. Air stagnation temperatures were 900 K and stagnation pressures were 0.8 MPa, the entrance Mach number was approximate 2.0 provided by a two-dimension nozzle. The experimental results indicate that: (1) Hydrogen self-ignition won’t occur at stagnation 935 K when it is injected upstream the cavity in this combustor model. But with low input power igniter, hydrogen can be ignited reliably. (2) Ethylene cannot be ignited with igniter only even at high igniter power. Under the assistant of both igniter and pilot Hydrogen, Ethylene can be ignited reliably and maintain stable combustion after the igniter and pilot hydrogen completely turned off. (3) The lowest equivalence ratio of pilot hydrogen for successful ethylene ignition is 0.05 below that ignition will fail. (4) When pilot hydrogen and igniters were both employed for ignition, the function of igniter is to ignite the hydrogen and the input power of igniter has no influence on ignition performance.
Highlights
In Turbine based combined cycle (TBCC) propulsion system, the turbojet engine provides its highest speed of Ma 3-4, the Scramjet engine should startup near Mach 4 and maintain appropriate performance to accelerate to higher speed
These ignition experiments were carried out on the pulse facility, pilot hydrogen and torch igniter were employed as assistant for ignition, by adjusting the injection schemes and ignition time, Hydrogen and gaseous ethylene ignition succeed and stable combustion maintained at stagnation temperature approximate 900 K
Ignition experiments at stagnation temperature of 935 K were carried out on pulse facility, experimental technical for pulse facility was mastered, the ignition performance of low stagnation flow-field was researched, and some conclusions were summarized: (1) Hydrogen self-ignition won’t occur at stagnation 935 K when it is injected upstream the cavity in this test model
Summary
In Turbine based combined cycle (TBCC) propulsion system, the turbojet engine provides its highest speed of Ma 3-4, the Scramjet engine should startup near Mach 4 and maintain appropriate performance to accelerate to higher speed. All the experiments presented above were performed on continuous facility, continuous facility can provide longer igniting time and ignition processe started at hot wall temperature condition which has been proved to be efficient methods to facilitate ignition at low total temperature inflow. These ignition experiments were carried out on the pulse facility, pilot hydrogen and torch igniter were employed as assistant for ignition, by adjusting the injection schemes and ignition time, Hydrogen and gaseous ethylene ignition succeed and stable combustion maintained at stagnation temperature approximate 900 K
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