Gas Turbine Engine Wings for Geared Architecture Weight Offset
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engines with geared architectures face increased weight, which can affect their efficiency and fuel consumption, and existing designs do not effectively distribute this weight to reduce lift effort during flight.
Innovation Solution
The integration of first and second engine wings, airfoil-shaped and mounted directly to the fan case, which project radially outward from the nacelle, providing lift to offset the weight of the gas turbine engines and distribute it more evenly, while also incorporating a geared architecture to drive the fan at a lower speed than the shaft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If a geared architecture is used to drive the fan at lower speed, then fuel efficiency is improved, but engine weight increases
Solution Approach 1:
The patent applies the anti-weight principle by configuring engine wings that generate lift to counterbalance the increased weight of the geared architecture. The wings are positioned and sized to produce aerodynamic lift during flight, which offsets a portion of the engine weight, thereby mitigating the negative impact of the heavier geared system on overall aircraft performance and fuel consumption.
Solution Approach 2:
The engine wings serve multiple functions: they generate lift to counteract engine weight, improve aerodynamic efficiency, and work in conjunction with the geared architecture to enhance overall engine performance. This multi-functionality allows the system to address both the weight penalty and fuel efficiency goals simultaneously.
2Force
If engine wings are added to counteract weight, then lift effort is reduced, but device complexity increases
Solution Approach 1:
The patent merges the engine structure with aerodynamic wings, integrating the weight-compensation function directly into the engine assembly. By combining the engine housing with attached wings, the design reduces the need for separate weight-compensation mechanisms, thereby limiting the increase in device complexity while still achieving the lift generation objective.
3Force
If wings project radially outward beyond the nacelle, then lift generation is improved, but aerodynamic drag increases
Solution Approach 1:
The patent applies local quality by varying the wing geometry along its span, with the chord length changing from root to tip. This allows optimization of lift generation at different locations while managing drag. The swept leading edge and tapered chord create favorable local flow conditions that balance lift production with drag minimization.
Solution Approach 2:
The airfoil-shaped cross-section and swept leading edge of the wings introduce curved aerodynamic surfaces that optimize flow attachment and reduce drag. The curved geometry of the wings, rather than flat surfaces, improves aerodynamic efficiency by managing boundary layer flow and reducing form drag, thereby mitigating the drag penalty of projecting beyond the nacelle.
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 wings generate sufficient lift to counteract the weight of the gas turbine engines, particularly the geared architecture, enhancing the engine's efficiency and reducing the lift effort required by the aircraft wings, thereby improving overall performance and fuel efficiency.
Implementation Method 1
The first engine wing and the second engine wing are airfoil-shaped in cross-section... the engine wings generate sufficient lift to counteract the weight of the gas turbine engines
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A gas turbine engine (68) according to an exemplary aspect of the present disclosure includes, among other things, an engine wing (72, 74). This disclosure also relates to an airplane (60) including an engine wing (72, 74).