Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
-
Yang Xiao
,
Li-Ming He
Abstract
This paper investigates the ignition performances of plasma-assisted ignition in propane/air mixture. The results show that a shorter ignition delay time is obtained for the plasma ignition than the spark ignition and the average ignition delay time of plasma-assisted ignition can be reduced at least by 50%. The influence of air flow rate of combustor, the arc current and argon flow rate of plasma igniter on ignition delay time are also investigated. The ignition delay time of plasma-assisted ignition increases with increasing air flow rate in the combustor. By increasing the arc current, the plasma ignition will gain more ignition energy to ignite the mixture more easily. The influence of plasma ignition argon flow rates on the ignition delay time is quite minor.
Funding statement: Funding: This research was supported by the National Natural Science Foundation of China under contract No. 51436008 and 51106179.
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Articles in the same Issue
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
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- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
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Articles in the same Issue
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
- Effect of Inlet Clearance on the Aerodynamic Performance of a Centrifugal Blower
- Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
- Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
- Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
- Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
