Micro-turbine Regenerative Cycle with Coanda Ejector
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current micro-jet engines lack advanced technologies for efficient thermodynamic cycles, leading to high fuel consumption and limited performance due to insufficient turbine cooling and high operating speeds, resulting in inefficient combustion and thrust generation.
Innovation Solution
A regenerative propulsion system with a novel gas generator design incorporating multiple stages of compressors, a toroidal combustor, and a Coanda ejector, utilizing Ceramic Matrix Composites and a heat exchanger to preheat air before combustion, reducing fuel requirements and increasing turbine entry temperature tolerance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If micro-jet engines operate at high speeds to compensate for size limitations, then thrust generation is achieved, but fuel consumption increases significantly and turbine life is limited
Solution Approach 1:
The patent changes the thermodynamic parameters of the engine cycle by implementing a regenerative cycle with heat exchanger, allowing the engine to operate at lower rotational speeds while maintaining thrust output. The heat exchanger recovers waste heat from exhaust gases to preheat compressor discharge air, improving thermal efficiency and reducing fuel consumption by 30-50% compared to conventional engines operating at high speeds
Solution Approach 2:
The patent converts the harmful waste heat in exhaust gases into a beneficial resource by using it to preheat the compressor discharge air through a heat exchanger. This regenerative approach transforms what would be wasted energy into useful thermal energy, reducing the fuel required for combustion and thereby lowering overall fuel consumption
2Device complexity
If micro-jet engines lack turbine cooling air flow to maintain simplicity, then device complexity is reduced, but turbine life and reliability are limited
Solution Approach 1:
The turbine cooling system is designed to be self-regulating, where the turbine itself provides the cooling air flow by expanding exhaust gases through the turbine blades. The pressure differential created during turbine operation naturally drives cooling air through internal passages without requiring external pumps or complex control systems, achieving reliable turbine cooling while maintaining device simplicity
3Device complexity
If micro-jet engines use conventional combustion chambers without preheating, then device complexity is minimized, but fuel consumption increases and combustion efficiency decreases
Solution Approach 1:
The combustion process is improved by preliminarily heating the air before it enters the combustion chamber through a heat exchanger that recovers waste heat from exhaust gases. This preheating action occurs upstream of the combustion zone, reducing the additional fuel required to reach combustion temperatures and improving overall combustion efficiency without significantly increasing system complexity
4Device complexity
If micro-jet engines lack advanced thermodynamic cycles, then device complexity is reduced, but fuel consumption exceeds 1.5 lb fuel per hour and lbf of thrust
Solution Approach 1:
The patent implements a regenerative thermodynamic cycle that changes the operating parameters by recovering and reuse waste heat energy. The heat exchanger enables the system to operate on a closed-loop thermal cycle where exhaust heat preheats incoming air, fundamentally improving thermal efficiency and reducing fuel consumption to below 1.5 lb fuel per hour and lbf of thrust
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 significant fuel savings, with a 30-50% reduction in fuel consumption per hour of flight, allowing for longer range and duration or faster flight with the same payload, and enhances thrust augmentation by using hot exhaust gases as motive fluid in Coanda ejectors.
Implementation Method 1
A first compressor defines an intake opening, at least one bleed port provided with a valve in connection with a fluid pressurized network of conduits, and one outlet to a secondary compressor or a combustion chamber or both via at least a volute and a compressor discharge conduit
Implementation Method 2
A regenerative propulsion system with a novel gas generator design incorporating multiple stages of compressors, a toroidal combustor, and a Coanda ejector
Data Source
AI summary
A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.