Disk Engine Radial Swirl Combustor for Compact Axial Layout
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Solution Overview
Problem
Existing gas turbine engines are limited by their axial length, which cannot meet the requirements of certain applications needing a more compact design.
Innovation Solution
A disk engine with a radial flow combustor and circumferential swirl combustor design that minimizes axial space by enhancing mixing of combustion reactants through high centrifugal loading and swirling, allowing for a compact engine architecture with reduced axial length and improved combustion efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If a traditional axial flow gas turbine engine is used, then the engine can achieve stable combustion and reliable operation, but the axial length of the engine becomes too long for compact applications
Solution Approach 1:
The patent transitions from an axial flow combustor to a radial flow combustor, changing the flow direction from the axial dimension to the radial dimension. This dimensional change allows the combustor to achieve stable combustion in a radial direction while minimizing the axial length of the engine, directly resolving the contradiction between compact axial length and combustion stability
Solution Approach 2:
The patent introduces circumferential swirl to the radial flow combustor, changing the flow parameters by adding a rotational component. This swirl parameter change enhances mixing and combustion stability in the radial flow path, enabling reliable combustion operation while maintaining the compact radial combustor design with reduced axial length
2Length of moving object
If a radial flow combustor is used to reduce axial length, then the axial space is minimized, but the mixing of combustion reactants becomes insufficient
Solution Approach 1:
The patent adds a circumferential dimension to the radial flow by introducing swirl motion. This creates a three-dimensional flow pattern combining radial inward flow with circumferential rotation, significantly enhancing mixing between fuel and oxidizer in the compact radial combustor geometry
Solution Approach 2:
The patent uses fluid dynamic principles by introducing high centrifugal loading through circumferential swirl. The swirling radial flow creates intense turbulence and mixing through pneumatic effects, achieving efficient combustion reactant mixing within the compact axial space of the radial combustor
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 design achieves equal performance to traditional gas turbine engines while significantly reducing axial length and weight, with enhanced mixing leading to faster combustion and lower NOx emissions.
Implementation Method 1
Swirling the reactants at a high centrifugal loading inside the combustion cavity has been shown to enhance Rayleigh-Taylor instabilities leading to enhanced mixing of the reactants
Implementation Method 2
Swirling the reactants at a high centrifugal loading inside the combustion cavity has been shown to enhance Rayleigh-Taylor instabilities leading to enhanced mixing of the reactants
Data Source
AI summary
A disk engine and system configured to provide high power at a reduced axial length is disclosed herein. The disk engine includes a radial compressor, a compressor discharge manifold positioned circumferentially about compressor, a combustion chamber positioned within the discharge manifold and a radial turbine positioned radially inward of the combustion chamber.