Multi-stage FLADE Fan Assembly for Pressure Ratio
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Solution Overview
Problem
Existing gas turbine engine configurations with aft-mounted Fan on Blade (FLADE™) face challenges in achieving adequate pressure ratios and installation due to limited axial distance for flow redirection, leading to high total pressure loss and potentially excessive weight with single-stage FLADE™.
Innovation Solution
A multi-stage FLADE™ is mounted on a fan stage near the forward portion of the gas turbine engine, comprising an outer fan first and second stage with radially extending blades and inter-stage vanes, allowing for variable pressure ratios and enhanced flow redirection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single-stage FLADE™ is used, then the device complexity is reduced, but the pressure ratio capability is insufficient
Solution Approach 1:
The fan stage is segmented into multiple stages (first stage and second stage) with separate blade rows. Each stage contributes to the overall pressure ratio, allowing the system to achieve higher pressure ratios than a single stage could provide alone, while maintaining manageable complexity through modular design
2Length of moving object
If an aft-mounted FLADE™ is used, then the axial distance for flow redirection is reduced, but the total pressure loss increases
Solution Approach 1:
The multi-stage fan configuration performs flow redirection and pressure increase in sequential stages rather than attempting single-stage redirection. The first stage begins the flow redirection process, and the second stage completes it, allowing gradual adaptation of the flow and reducing total pressure loss
3Weight of moving object
If a single-stage FLADE™ is used, then the weight is reduced, but the pressure ratio capability is insufficient
Solution Approach 1:
The fan stage is divided into multiple lighter stages rather than one heavy single stage. Each stage uses smaller, lighter blades that collectively achieve the required pressure ratio, distributing the weight burden while maintaining pressure ratio capability through cumulative effect of multiple stages
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 multi-stage FLADE™ configuration increases pressure ratios beyond single-stage capabilities, reduces total pressure loss, and facilitates easier engine installation by increasing axial distance for flow redistribution, while maintaining constant airflow.
Implementation Method 1
a radially inner portion of the blade works as a turbine blade that extracts energy from a flow of a hot combustion gas stream
Implementation Method 2
a radially outer portion of the blade (FLADE™) works as a fan to impart energy into a flow of a relatively cooler air stream to raise its pressure
Data Source
AI summary
A fan assembly having an outer fan system is disclosed, the fan assembly comprising an outer fan first stage and an outer fan second stage both extending radially outward from an arcuate platform.