Turbofan Thrust Vectoring Nozzle for Short Runway Operations
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Solution Overview
Problem
Conventional aircraft engines with fixed nozzles are not optimized for take-off and landing conditions, limiting their ability to operate on shorter runways due to a fixed thrust angle that does not provide the best performance during these phases.
Innovation Solution
A turbofan engine system with a controller that alters the nozzle exit area to change the thrust vector in response to take-off and landing conditions, using hinged flaps to manipulate the bypass flow and provide a downward thrust vector, reducing the required take-off field length.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a fixed nozzle is used to provide best overall performance throughout the flight envelope, then the engine maintains consistent performance across different flight conditions, but the thrust angle is not optimized specifically for take-off conditions
Solution Approach 1:
The nozzle is made dynamically adjustable through a thrust vector control system that can change the nozzle exit area and thrust angle in real-time. During take-off, the controller increases the nozzle exit area to generate a downward thrust vector component, while during cruise it maintains a fixed configuration for optimal overall performance.
Solution Approach 2:
The system changes the physical parameters of the nozzle (exit area and angle) based on flight conditions. The controller adjusts the nozzle geometry during take-off to optimize thrust vector for reduced take-off field length, while maintaining fixed parameters during cruise for general efficiency.
2Productivity
If the nozzle exit area is increased to achieve a downward thrust vector for take-off, then the take-off field length is reduced, but the device complexity increases
Solution Approach 1:
The thrust vector control system serves multiple functions: it optimizes take-off performance by creating downward thrust, maintains cruise efficiency, and can potentially assist during landing. This multi-functionality justifies the added complexity by providing benefits across multiple flight phases.
Solution Approach 2:
The controller automatically detects take-off conditions and adjusts the nozzle configuration without pilot intervention. The system self-regulates the thrust vector based on flight phase detection, reducing the operational complexity burden on the pilot while maintaining performance benefits.
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
Enables aircraft to operate on shorter runways by optimizing thrust direction during take-off and landing, reducing the required take-off velocity and field length, while maintaining efficient performance and noise levels across various flight conditions.
Implementation Method 1
a bypass flow path downstream from the turbofan and arranged between the core and fan nacelles, the bypass flow path including a nozzle exit area
Data Source
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AI summary
A turbofan engine control system and method includes a core nacelle housing (12), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan nacelle (34). A bypass flow path (39) is arranged downstream from the turbofan between the core and fan nacelles. The bypass flow path includes a nozzle exit area (40). A controller (50) detects at least one of a take-off condition and a landing condition. The controller changes effectively the nozzle exit area to achieve a thrust vector in response to the take-off and landing conditions.