Plasma Arc Torch for Supersonic Lean Combustion
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current gas turbine engines face challenges in achieving supersonic combustion and efficient lean fuel combustion, particularly with low BTU fuels like syngas, due to flame holding issues, high fuel requirements, and the need for multiple engine configurations for subsonic to hypersonic flight, which complicates transition and increases costs and emissions.
Innovation Solution
A supersonic lean fuel combustion plasma arc turbine system is developed, utilizing a plasma arc torch and cyclone combustor with a turbocharger, creating a vortex for energy transfer and flame stabilization, allowing for efficient combustion of low BTU fuels and enabling transition from subsonic to hypersonic flight with a single engine configuration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If lean fuel combustion is used to increase efficiency and lower emissions, then fuel efficiency is improved, but flame holding capability deteriorates
Solution Approach 1:
The plasma arc preheats and partially combusts the fuel before it enters the main combustion zone, creating a stable ignition source that enables subsequent lean combustion to be sustained without flame out
Solution Approach 2:
The plasma arc acts as an intermediary energy source that bridges the gap between fuel injection and stable combustion, providing the necessary activation energy to initiate and sustain lean combustion reactions
2Adaptability or versatility
If low BTU fuel such as syngas is combusted, then alternative fuel usage is improved, but combustion stability deteriorates
Solution Approach 1:
The plasma arc preheats and partially combusts the low BTU fuel before it enters the main combustion zone, creating a stable ignition source that enables subsequent lean combustion to be sustained without flame out
Solution Approach 2:
The plasma arc changes the temperature and chemical composition parameters of the fuel stream, converting low BTU fuel with poor combustion characteristics into a higher energy density mixture that burns more stably
3Device complexity
If a single engine configuration is used for subsonic to hypersonic flight, then device complexity is reduced, but combustion stability deteriorates
Solution Approach 1:
The plasma arc system dynamically adjusts its power output and operational characteristics to match different flight regimes, maintaining stable combustion across subsonic, supersonic, and hypersonic conditions without requiring physical engine reconfiguration
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The system achieves stable supersonic combustion and efficient lean fuel combustion, reducing emissions and fuel consumption, while enabling the use of renewable fuels and transitioning between flight modes with a single engine, thus addressing the limitations of existing technologies.
Implementation Method 1
plasma arc torch...creating a vortex for energy transfer and flame stabilization
Implementation Method 2
supersonic lean fuel combustion plasma arc turbine...utilizing a plasma arc torch
Implementation Method 3
cyclone combustor with a turbocharger, creating a vortex for energy transfer and flame stabilization
Implementation Method 4
cyclone combustor...creating a vortex...flame stabilization
Implementation Method 5
extracting a rotational energy from one or more hot gases, recuperating energy from the hot gases
Data Source
Figure 1
Figure 2
Figure 3
AI summary
The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, (b) extends into the cylindrical vessel, and (c) can be moved along the longitudinal axis, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle crate a plasma the discharges through the hollow electrode nozzle.