Gas Turbine Engine Controller Radial Height Optimization
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Solution Overview
Problem
There is a challenge in designing turbofan engines with large fans to maximize propulsive efficiency while minimizing the size and weight of the outer nacelle, particularly due to the need to reduce the radial height of the engine controller without excessive weight gain.
Innovation Solution
The solution involves optimizing the design of the engine controller by establishing a relationship between the ratio of the radial extent of the engine controller to the fan diameter and a normalized engine controller radius, which helps in reducing the radial height of the nacelle while maintaining desired propulsive efficiency and packaging considerations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of stationary object
If the radial height of the engine controller is reduced to minimize nacelle size, then the nacelle weight is reduced, but the engine controller may become excessively heavy due to packaging constraints
Solution Approach 1:
The patent applies parameter changes by establishing a mathematical relationship between the normalized radius and radial height ratio, using optimized parameter ranges (normalized radius between 1.25-8, K between 40-65%) to balance controller dimensions and weight, preventing excessive weight gain while reducing radial height
Solution Approach 2:
The patent introduces a normalized radius parameter (r') that combines radial dimension with volume information, creating a new dimensional relationship that allows optimization beyond simple radial height reduction, enabling weight-balanced design through multi-dimensional parameter correlation
2Loss of energy
If large diameter fans are used to increase propulsive efficiency, then propulsive efficiency is improved, but the nacelle size and weight increase
Solution Approach 1:
The patent applies preliminary action by pre-establishing the mathematical relationship between normalized radius and radial height ratio before final nacelle design, allowing designers to predict and control weight implications of large fan selections, enabling proactive optimization rather than reactive weight management
Data Source
AI summary
A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (Δr) along the radial direction, a total volume (V), and a normalized radius (r′). The normalized radius (r′) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation:0.1(r′)-1<Δrr<K(r′)-4/3,wherein the normalized radius (r′) is between 1.25 and 8 and K is equal to 40%, or the normalized radius (r′) is between 2.75 and 4.5 and K is equal to 65%.