Ducted-Fan Torque Stage with Dual Ring Vanes
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Solution Overview
Problem
Conventional propeller drives are inefficient, and existing turbofan engine designs fail to effectively generate thrust for both aircraft and watercraft, particularly in terms of torque and thrust vector control, with limitations in maneuverability and noise reduction.
Innovation Solution
A turbofan engine design featuring a two-layer jacket formed by two ring blades of different sizes, with a smaller ring blade acting as a guide ring and a larger ring blade forming an annular guide nozzle, creating a fluid-dynamically effective torque stage that induces torque and thrust through convergent and divergent cone angles, allowing for vertical takeoff and improved maneuverability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional propeller drives are used, then the structure is simple, but the efficiency is unsatisfactory
Solution Approach 1:
The propeller is segmented into multiple independent ring blades (at least two ring blades with different radii) arranged along the rotation axis. Each ring blade can be independently designed and positioned, allowing optimization of efficiency for different flight conditions while maintaining manageable structural complexity through modular design
Solution Approach 2:
The invention transitions from a conventional single-plane propeller to a three-dimensional arrangement of ring blades at different radial positions and axial locations. This dimensional expansion creates multiple thrust vectors and improves overall propeller efficiency by utilizing spatial distribution of aerodynamic forces
2Adaptability or versatility
If a single annular vane design is used, then the structure is simple, but the thrust generation and maneuverability are limited
Solution Approach 1:
The single annular vane is segmented into multiple independent ring blades with different radii positioned along the rotation axis. Each ring blade can be independently controlled or positioned, enabling differential thrust generation for enhanced maneuverability while maintaining relatively simple individual vane structures
Solution Approach 2:
The multiple ring blades serve multiple functions simultaneously: generating thrust, providing maneuverability control, and creating circulation flows for noise reduction. This multi-functionality increases adaptability without proportionally increasing structural complexity
3Force
If high thrust generation is pursued, then the propulsion force increases, but the noise level increases
Solution Approach 1:
The circulation flow generated by the multiple ring blades creates controlled vortex structures that reduce turbulent wake and associated noise. The aerodynamic interaction between ring blades produces stabilizing vortex rings that diminish harmful acoustic emissions while maintaining thrust generation
Solution Approach 2:
The invention converts potentially harmful turbulent flows and wake vortices into beneficial circulation patterns. The ring blades generate controlled circulation flows that reduce noise by organizing the wake structure, transforming what would be chaotic turbulence into ordered vortex rings that are less noisy
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 enhances thrust generation, reduces noise, and improves maneuverability by creating a circulation flow that generates tangential driving and thrust forces, suitable for both aircraft and watercraft, with the ability to function as landing gear and rudder propellers.
Implementation Method 1
Both annular wings have a fluid-dynamically effective, asymmetrical wing profile with a profile depth, a wing leading edge aligned in the thrust direction, and a profile chord extending between the leading edge and the trailing edge of the wing
Implementation Method 2
A circulation flow is generated which creates tangential driving and thrust forces
Data Source
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AI summary
The invention relates to a ducted-fan engine (1) which is designed to generate thrust for an aircraft (22) or for a watercraft (23) and which has at least one relatively small ring vane (C1), which is positioned upstream in the direction of thrust and which has the radius (r1), and a torque stage (2), which is formed by a downstream, relatively large ring vane (C2) with the radius (r2).