Experimental Study of Propulsion Performance by Single-Pulse Rotating Detonation with Gaseous Fuels-Oxygen Mixtures
-
Kazuhiko Toshimitsu
,
Kosei Hara
Abstract
A rotating detonation engine (RDE) is one of candidates of aerospace engines for supersonic cruse, which is better for propulsion system than a pulse detonation engine (PDE) from the view of continuous thrust and simple structure. The propulsion performance of a proto-type RDE and a PDE by single pulse explosion with methane-oxygen is investigated. Furthermore, the performance of the RDE with acetylene-oxygen gas mixtures is investigated. Its impulse is estimated through ballistic pendulum method with maximum displacement and damping ratio. The comparison of specific impulses of the mixture gases at atmospheric pressure is shown. The specific impulses of the RDE and the PDE are almost same with methane-oxygen gas. Furthermore, the fuel-base specific impulse of the RDE with acetylene-oxygen gas is about over twice as large as one of methane-oxygen, and its maximum specific impulse is 1100 seconds.
Nomenclature
- F
Thrust of an engine [N]
Impulse of an engine [Ns]
- m
Mass of gas [kg]
- M
Mass of an engine [kg]
- T
Period of free oscillation of an engine [s]
- x
Maximum displacement of free oscillation of an engine [m]
Damping coefficient of free oscillation of an engine
- Subscripts
- sp
Specific impulse
- t
Thrust
Acknowledgements
This work is written based on the presentation paper in APCATS 2015. We would like to express thanks to other collaborators; Mr. Mitsuhiro Iwamoto (National Institute of Technology, Oita College), Mr. Ryo Takahashi (Kyushu Institute of Technology), Ms. Wakaba Uno (Hitachi Construction Machinery Co., Ltd.) and Mr. Shouhei Kawano (Toray Industries Inc.).
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©2016 by De Gruyter
Artikel in diesem Heft
- Frontmatter
- Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace
- Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility
- Investigation of Detailed Flow in a Variable Turbine Nozzle
- A Study on the Installed Performance Seeking Control for Aero-Propulsion under Supersonic State
- Study of the Standard k-ε Model for Tip Leakage Flow in an Axial Compressor Rotor
- Experimental Study of Propulsion Performance by Single-Pulse Rotating Detonation with Gaseous Fuels-Oxygen Mixtures
- Finite Element Analysis for Turbine Blades with Contact Problems
- CFD Modeling of Mixed-Phase Icing
- Effect of Steam Addition on the Flow Field and NOx Emissions for Jet-A in an Aircraft Combustor
- An Integrated Optimization Design Method Based on Surrogate Modeling Applied to Diverging Duct Design
- Numerical Study of Unsteady Properties of Ethylene/Air Turbulent Jet Diffusion Flame with Detached Eddy Simulation
- Influence of Rotor-Stator Interaction on Flow Stability in Centrifugal Pump Based on Energy Gradient Method
Artikel in diesem Heft
- Frontmatter
- Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace
- Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility
- Investigation of Detailed Flow in a Variable Turbine Nozzle
- A Study on the Installed Performance Seeking Control for Aero-Propulsion under Supersonic State
- Study of the Standard k-ε Model for Tip Leakage Flow in an Axial Compressor Rotor
- Experimental Study of Propulsion Performance by Single-Pulse Rotating Detonation with Gaseous Fuels-Oxygen Mixtures
- Finite Element Analysis for Turbine Blades with Contact Problems
- CFD Modeling of Mixed-Phase Icing
- Effect of Steam Addition on the Flow Field and NOx Emissions for Jet-A in an Aircraft Combustor
- An Integrated Optimization Design Method Based on Surrogate Modeling Applied to Diverging Duct Design
- Numerical Study of Unsteady Properties of Ethylene/Air Turbulent Jet Diffusion Flame with Detached Eddy Simulation
- Influence of Rotor-Stator Interaction on Flow Stability in Centrifugal Pump Based on Energy Gradient Method
