Rotor Blade Nozzle Geometry for Constant-Mass-Flow Jet Ejection
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Solution Overview
Problem
Existing reaction jet helicopters experience significant turbulence, noise, and energy loss due to the uniform cross-section apertures used in compressed gas ejection, leading to shear in the jet efflux and increased drag.
Innovation Solution
A compressed gas ejection system with a passage that maintains a substantially constant mass flow across its width, reducing shear and turbulence by varying the height of the fluid channels to ensure a consistent mass flow resistance, thereby optimizing the ejection of compressed air.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If uniform cross-section apertures are used for compressed gas ejection, then the structure is simple and easy to manufacture, but turbulence and energy loss increase due to shear in the jet efflux
Solution Approach 1:
The aperture cross-section is varied locally along its length, with the height changing from a first value at the inlet to a second value at the outlet. This local variation in geometry optimizes the flow characteristics and reduces turbulence in the jet efflux, thereby reducing energy loss while maintaining manufacturing feasibility.
Solution Approach 2:
The height parameter of the aperture cross-section is changed along the length of the aperture. This parameter variation allows optimization of the mass flow distribution and reduction of shear effects in the jet efflux, reducing turbulence and energy loss without significantly complicating the manufacturing process.
2Ease of manufacture
If uniform cross-section apertures are used for compressed gas ejection, then the manufacturing process is simple, but noise levels increase due to turbulence
Solution Approach 1:
The aperture cross-section is varied locally along its length, with the height changing from a first value at the inlet to a second value at the outlet. This local geometry optimization reduces turbulence in the jet efflux, thereby reducing noise generation while keeping the manufacturing process relatively simple.
Solution Approach 2:
The height parameter of the aperture cross-section is varied along the aperture length to optimize flow characteristics. This parameter change reduces turbulence-induced noise while maintaining ease of manufacture through a straightforward geometric modification.
3Device complexity
If uniform cross-section apertures are used, then the structure is simple, but turbulence increases due to shear in the jet efflux
Solution Approach 1:
The aperture cross-section is varied locally along its length, with the height changing from a first value at the inlet to a second value at the outlet. This local geometry variation optimizes the flow characteristics and reduces shear effects, thereby reducing turbulence while maintaining relatively simple structure.
Solution Approach 2:
The height parameter of the aperture cross-section is changed along the aperture length to optimize mass flow distribution. This parameter variation reduces shear in the jet efflux and turbulence, achieving flow stability with minimal structural complexity.
4Force
If high velocity compressed air jets are used to provide jet thrust and lift, then the propulsion force is sufficient, but drag and noise levels increase
Solution Approach 1:
The height parameter of the aperture cross-section is varied along the aperture length to optimize the velocity distribution of the ejected compressed air. This optimization maintains sufficient jet thrust while reducing shear effects and turbulence, thereby reducing drag and noise levels.
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 solution reduces turbulence, noise, and energy loss, enhancing the efficiency of the compressed gas ejection process in reaction jet helicopters.
Implementation Method 1
the compressed gas passage means comprises a compressed gas entrance and a compressed gas exit
Implementation Method 2
Variations in the velocity and mass flow of the compressed gas ejected through such apertures creates significant shear in the jet efflux resulting in increased turbulence and energy loss
Implementation Method 3
an engine-driven compressor produces compressed air which is ejected through ejection means such as jet nozzles at the tips of the rotor blades
Implementation Method 4
This causes the rotor blades to rotate, thereby producing lift and thrust for the aircraft
Data Source
AI summary
A compressed gas ejection assembly for a rotating wing aircraft blade comprising a compressed gas passage adapted to allow a substantially constant mass flow through the compressed gas ejection assembly across at least a portion of the width of the compressed gas ejection assembly.