Turbofan Engine Variable Nozzle for Supersonic Noise Reduction
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Solution Overview
Problem
Current supersonic aircraft engines from military technology are not suitable for the civil sector due to inadequate noise reduction and fuel efficiency, necessitating a specialized turbofan engine design for efficient supersonic operation.
Innovation Solution
A turbofan engine with a multi-stage fan, a core engine comprising a compressor, combustor, and turbine, integrated with a variable convergent-divergent exhaust nozzle and thrust reverser, featuring adjustable nozzle areas and sound-absorbing linings to reduce noise and enhance efficiency for supersonic flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a military turbofan engine is used for supersonic operation, then supersonic flight capability is achieved, but noise levels are excessive and fuel consumption is high
Solution Approach 1:
The engine is divided into distinct functional sections: a military-derived core engine for supersonic capability, and a separately optimized fan section with multi-stage design and adjustable nozzle for noise and efficiency optimization. This segmentation allows each section to be optimized for its specific function while working together as an integrated system.
Solution Approach 2:
The patent combines the military turbofan core engine with a civil-oriented noise-reduction system comprising multi-stage fans and adjustable convergent-divergent nozzles. This merging creates a hybrid engine that retains supersonic capability while adding noise control and fuel efficiency features required for civil aviation.
2Device complexity
If a fixed-area thrust nozzle is used, then structural simplicity is maintained, but compressor efficiency cannot be optimized across different flight conditions
Solution Approach 1:
The thrust nozzle is designed with adjustable throat area and outlet area, allowing dynamic adaptation to different flight conditions. The nozzle sections can be moved axially to change the flow area, optimizing compressor efficiency across the supersonic flight envelope while maintaining a relatively simple structural implementation.
3Ease of operation
If a thrust reverser is added to the nozzle, then braking capability is improved, but nozzle structure complexity increases
Solution Approach 1:
The thrust reverser mechanism is integrated into the existing adjustable nozzle structure, combining the thrust reversal function with the nozzle area adjustment mechanism. This merging allows braking capability to be added while minimizing additional structural complexity by utilizing the movable nozzle sections for both area adjustment and thrust reversal.
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 engine achieves efficient supersonic operation with reduced noise and structural loads, enabling short braking distances and adaptable thrust settings, suitable for commercial aircraft operating within specific thrust and speed ranges.
Implementation Method 1
an engine intake (1) designed and configured for supersonic operation, which slows the incoming air below the speed of sound
Data Source
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AI summary
The invention relates to a turbofan engine for a civil supersonic aircraft, comprising: an engine inlet (1); a multi-stage fan (3) arranged behind the engine inlet (1); a core engine comprising a compressor (7), a combustion chamber (11) and a turbine (91, 92); a primary flow channel (6) passing through the core engine; a secondary flow channel (5) passing by the core engine; an adjustable convergent-divergent thrust nozzle (4) forming a nozzle throat surface (16) and a nozzle outlet surface (17), wherein at least the nozzle throat surface (16) is adjustable; and a thrust reverser (15) integrated into a forward, non-adjustable portion (41) of the thrust nozzle (4).