Multidirectional Turbine Engine with Opposing Rotors
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Solution Overview
Problem
Conventional gas turbine engines with multiple turbines arranged in series do not maximize thrust output as energy is dissipated between turbines, preventing simultaneous and equal direction of high velocity, high pressure gas mixtures for optimal thrust generation.
Innovation Solution
The gas turbine engine design features at least two turbines mounted opposite each other, with a central gear shaft regulator allowing independent rotation, enabling simultaneous and equal direction of the combustion gas mixture to both turbines for maximum thrust output, and adjustable nozzles for variable thrust direction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If multiple turbines are arranged in series, then the engine can generate thrust, but the thrust output is dissipated as energy travels from turbine to turbine, preventing simultaneous and equal direction of high velocity gas mixture
Solution Approach 1:
The combustion chamber is segmented into multiple outlet sections, with each section directing high velocity gas mixture to a separate turbine. This segmentation allows simultaneous and equal direction of gas flow to multiple turbines, eliminating energy dissipation issues inherent in series arrangements.
Solution Approach 2:
The patent transitions from a linear series arrangement to a multidimensional configuration where turbines are positioned at different spatial locations around the combustion chamber. This dimensional change enables simultaneous gas flow distribution to multiple turbines without energy dissipation between them.
2Device complexity
If turbines are mounted on the same side of the compressor in series, then the structure is simplified, but the thrust output is dissipated and cannot be maximized
Solution Approach 1:
The combustion chamber outlets are segmented to serve different turbines positioned at different locations. This segmentation enables a distributed turbine arrangement that maximizes thrust output while maintaining reasonable structural complexity through modular design.
Solution Approach 2:
The patent employs multidimensional spatial arrangement of turbines around the combustion chamber rather than a single-sided linear arrangement. This dimensional approach optimizes thrust output by enabling simultaneous gas flow distribution while managing structural complexity through systematic positioning.
3Device complexity
If only one turbine is used, then the structure is simple, but greater thrust cannot be generated
Solution Approach 1:
The combustion chamber is divided into multiple outlet sections, each serving a separate turbine. This segmentation enables multiple turbines to operate simultaneously with equal and simultaneous gas flow, generating greater thrust while maintaining manageable structural complexity through modular architecture.
Solution Approach 2:
Multiple turbines are merged into a single system sharing a common combustion chamber and gas flow source. This merging enables simultaneous operation of multiple turbines with equal gas distribution, achieving greater thrust output while avoiding the complexity of independent turbine systems.
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 maximizes thrust output by ensuring that the high pressure, high velocity gas mixture is directed equally to both turbines, enhancing the engine's efficiency and thrust generation capabilities compared to series arrangements.
Implementation Method 1
The compressed air is communicated to the combustion chamber, where it is mixed with gas and ignited to undergo combustion. The resulting combustion produces a high pressure, high velocity gas mixture
Implementation Method 2
The high pressure, high velocity gas mixture is directed to the turbine, motivating the turbine to generate force. The gas mixture is expelled through a nozzle in the turbine, generating thrust by accelerating the hot exhaust gas mixture
Data Source
AI summary
A gas turbine engine comprising a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating multidirectional thrust.