Flow modulating airfoil apparatus
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The cooling systems in modern gas turbine engines face inefficiencies due to the bleed flow reducing thrust efficiency and causing excess cooling in certain operating conditions, necessitating a precise control of the bleed flow to maintain adequate cooling across varying engine operations.
Innovation Solution
A flow modulating airfoil apparatus within the cooling system, featuring dividers with rotatable flaps and a pin axis, allows for adjustable airflow through a heat exchanger, enabling precise control of bleed air flow by transitioning between fully-open and partially-closed states to optimize cooling based on operational conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If bleed flow is used for cooling engine components, then cooling effectiveness is improved, but thrust efficiency deteriorates
Solution Approach 1:
The patent employs a modulator with movable dividers that can dynamically adjust the cross-sectional area of the cooling passage. This allows the system to adapt the bleed flow rate according to real-time operating conditions, providing optimal cooling effectiveness while minimizing thrust efficiency loss by reducing unnecessary bleed flow during conditions where less cooling is required.
2Temperature
If bleed flow rate is increased to maintain adequate cooling, then cooling adequacy is improved, but excess cooling occurs in certain operating conditions
Solution Approach 1:
The system incorporates a modulator that responds to operating conditions and adjusts the bleed flow rate accordingly. This feedback mechanism prevents excess cooling by reducing the bleed flow rate when cooling demand is low, while ensuring adequate cooling is maintained when required, thus eliminating the harmful effects of over-cooling.
3Loss of energy
If the amount of bleed flow is reduced to minimize thrust efficiency loss, then thrust efficiency is improved, but cooling adequacy deteriorates
Solution Approach 1:
The modulator with adjustable dividers enables dynamic control of the cooling passage cross-sectional area, allowing the system to optimize the balance between thrust efficiency and cooling adequacy. By adapting the bleed flow rate to actual cooling requirements, the system ensures adequate cooling is maintained while minimizing unnecessary thrust efficiency loss.
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
This solution effectively manages bleed air flow to maintain sufficient cooling while minimizing thrust efficiency loss, ensuring adequate cooling during all engine operating conditions and preventing excess cooling, thus optimizing engine performance.
Implementation Method 1
a heat exchanger and a modulator positioned in the cooling duct
Implementation Method 2
The modulator includes dividers that extend parallel to each other and are arranged across the duct, and each divider includes two flaps that are rotatable about an axis in opposite directions
Data Source
AI summary
A gas turbine engine includes a fan, a compressor, a combustor, a turbine, a bypass duct downstream of the fan and outward of the compressor, and a cooling system. The cooling system includes an inlet for receiving air from the bypass duct, an outlet for returning air to the bypass duct, a cooling duct, and a heat exchanger and a modulator positioned in the cooling duct. The modulator includes dividers that extend parallel to each other and are arranged across the duct, and each divider includes two flaps that are rotatable about an axis in opposite directions.