The Ignition of Two Phase Detonation by a Branching Detonation Tube
-
Cha Xiong
,
Hua Qiu
Abstract
A branching tube is available to deliver sufficient energy to directly initiate a detonation wave. But sustaining the detonation wave through a branching tube is a challenge. In this study, a preliminary exploration about a branching pulsed detonation engine with a gas-liquid mixture was carried out to evaluate filling conditions on detonation initiation. Two detonation tubes were connected by three different schemes, such as Tail-Tail, Tail-Mid, and Tail-Head. Experimental results showed only end-head connected tubes can be ignited by the branching tube, which is quite different from the results using gas fuels or pre-evaporated liquid fuel. Liquid fuel distribution is crucial for successful detonation traveling through the branching tube.
Funding statement: This work was supported by the National Natural Science Foundation of China (No. 51306154, 91441201), and Natural Science Basic Research Plan in Shaanxi Province of China (2015JM5221).
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Articles in the same Issue
- Frontmatter
- Expanded R&D by Jet-engine-steering Revolution
- Scientific Paper
- Switching LPV Control with Double-Layer LPV Model for Aero-Engines
- On-Board Real-Time Optimization Control for Turbo-Fan Engine Life Extending
- Investigation of Engine Oil-cooling Problem during Idle Conditions on Pusher Type Turbo Prop Aircraft
- Regulating Effect of Asymmetrical Impeller on the Flow Distributions of Double-sided Centrifugal Compressor
- Numerical Prediction of the Influence of Thrust Reverser on Aeroengine’s Aerodynamic Stability
- Performance Evaluation of an Experimental Turbojet Engine
- The Design and Semi-Physical Simulation Test of Fault-Tolerant Controller for Aero Engine
- The Ignition of Two Phase Detonation by a Branching Detonation Tube
- Tab Geometry Effect on Supersonic Elliptic Jet Control
Articles in the same Issue
- Frontmatter
- Expanded R&D by Jet-engine-steering Revolution
- Scientific Paper
- Switching LPV Control with Double-Layer LPV Model for Aero-Engines
- On-Board Real-Time Optimization Control for Turbo-Fan Engine Life Extending
- Investigation of Engine Oil-cooling Problem during Idle Conditions on Pusher Type Turbo Prop Aircraft
- Regulating Effect of Asymmetrical Impeller on the Flow Distributions of Double-sided Centrifugal Compressor
- Numerical Prediction of the Influence of Thrust Reverser on Aeroengine’s Aerodynamic Stability
- Performance Evaluation of an Experimental Turbojet Engine
- The Design and Semi-Physical Simulation Test of Fault-Tolerant Controller for Aero Engine
- The Ignition of Two Phase Detonation by a Branching Detonation Tube
- Tab Geometry Effect on Supersonic Elliptic Jet Control
