UAV Gas Turbine Engine Airframe Integrated Bypass Duct
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Solution Overview
Problem
The existing gas turbine engines for aircraft require a robust outer bypass duct for structural support, which increases the size, weight, and cost of the aircraft, particularly in small pilotless vehicles like UAVs where space and weight are critical.
Innovation Solution
The outer bypass duct is eliminated, and the airframe is modified to form the bypass duct, integrating the engine and airframe structure, reducing the overall size, weight, and cost by utilizing the airframe's inner wall as the bypass duct outer wall.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a robust outer bypass duct is used for structural support, then the engine can accommodate thrust and maneuver loads, but the size, weight, and cost of the aircraft increase
Solution Approach 1:
The patent merges the outer bypass duct function with the aircraft airframe structure. The airframe's inner wall directly forms the bypass duct outer wall, eliminating the need for a separate robust outer bypass duct. This integration maintains structural support capability while significantly reducing the weight and size of the aircraft.
Solution Approach 2:
The airframe structure serves multiple functions: it provides the aircraft's structural framework and simultaneously acts as the outer bypass duct. This multi-functionality eliminates the need for dedicated engine mounting structures and bypass ducts, reducing overall aircraft weight and complexity.
2Strength
If a robust outer bypass duct is used for structural support, then the engine can accommodate thrust and maneuver loads, but the size and cost of the aircraft increase
Solution Approach 1:
The patent merges the outer bypass duct function with the aircraft airframe structure. The airframe's inner wall directly forms the bypass duct outer wall, eliminating the need for a separate robust outer bypass duct. This integration maintains structural support capability while significantly reducing the weight and size of the aircraft.
3Weight of stationary object
If the outer bypass duct is eliminated and the airframe forms the bypass duct, then the aircraft size and weight are reduced, but the airframe structure must bear additional loads
Solution Approach 1:
The patent merges the outer bypass duct function with the aircraft airframe structure. The airframe's inner wall directly forms the bypass duct outer wall, eliminating the need for a separate robust outer bypass duct. This integration maintains structural support capability while significantly reducing the weight and size of the aircraft.
Solution Approach 2:
The patent modifies the airframe structure parameters (thickness, material properties, geometric configuration) to ensure it can bear the additional thrust and maneuver loads while maintaining the weight reduction benefits.
4Length of stationary object
If the outer bypass duct is eliminated and the airframe forms the bypass duct, then the aircraft size and cost are reduced, but the integration complexity increases
Solution Approach 1:
The patent merges the outer bypass duct function with the aircraft airframe structure. The airframe's inner wall directly forms the bypass duct outer wall, eliminating the need for a separate robust outer bypass duct. This integration maintains structural support capability while significantly reducing the weight and size of the aircraft.
Data Source
AI summary
A small aircraft such as a UAV having a gas turbine engine with the outer bypass elements removed from the engine, and where the airframe is modified to form the bypass duct and exhaust nozzle for the fan produced bypass flow of the engine in order to reduce weight, size and cost of the small aircraft. The outer casing and the exhaust nozzle is removed from the engine and optimally integrated into the airframe structure.