Interstage Micro-Turbine Alternator Layout for Higher Power Density
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Solution Overview
Problem
Conventional power generation systems for medium-sized UAVs face limitations due to low energy density of batteries and inefficiency of internal combustion engines at low power levels, leading to short mission times and restricted operational height and distance for tethered systems, necessitating a lightweight, high power density untethered power source.
Innovation Solution
The design of a micro-turbine alternator with an electric generator located between two stages of compressors, reducing the inlet diameter of the first stage compressor hub to enhance power generation and aerodynamic performance, while utilizing a permanent magnet alternator and alternator stator cooling heat exchanger to optimize power output.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the electric generator is disposed along the shaft between the first stage compressor and the second stage compressor, then the inlet diameter of the first stage compressor hub is reduced and power generation is enhanced, but the device complexity increases due to the interstage configuration
Solution Approach 1:
The electric generator is positioned in the axial dimension between compressor stages rather than at the ends, utilizing the intermediate space along the shaft to reduce the first stage compressor hub diameter and improve aerodynamic performance while generating power
2Productivity
If the first stage compressor hub diameter is reduced to enhance aerodynamic performance, then power generation efficiency increases, but the structural strength and stability may be compromised
Solution Approach 1:
The compressor system is divided into multiple stages with the electric generator positioned between them, allowing the first stage compressor hub to be smaller while the second stage compressor compensates to maintain overall compression performance and structural integrity
Solution Approach 2:
The electric generator is merged with the compressor shaft assembly, sharing the same rotational axis and structural support, which allows the reduced hub diameter to be compensated by the integrated generator-compressor structure
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
This configuration allows for increased power generation with lower inlet pressure, reduced physical size, and improved aerodynamic performance, enabling longer mission times and increased operational range for UAVs and electrically-powered systems without the constraints of a tether.
Implementation Method 1
The rotor element further includes an annular base member and an annular array of permanent magnets coupled to the annular base member. The stator element includes a hub, a plurality of spokes extending radially inward from the hub, and one or more conductive elements that are wound around the spokes to form windings.
Implementation Method 2
The micro-turbine alternator further includes an alternator stator cooling heat exchanger configured to utilize the compressed airflow from the first stage compressor to cool the electric generator.
Data Source
AI summary
An electrical power generation system including a micro-turbine alternator including a combustion chamber, at least one turbine driven by combustion gases from the combustion chamber, a first stage compressor, and a second stage compressor located aft of the first stage compressor. The first stage compressor and the second stage compressor being operably connected to the combustion chamber to provide a compressed airflow thereto. The micro-turbine alternator including one or more shafts connecting the at least one turbine to the first stage compressor and the second stage compressor such that rotation of the at least one turbine drives rotation of the first and second stage compressor. An electric generator is disposed along the one or more shafts such that electrical power is generated via rotation of the one or more shafts. The electric generator is disposed along the one or more shafts between the first and second stage compressors.