Radial Compressor Impeller in Fan Hub for Gas Turbine Engine
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Solution Overview
Problem
Conventional gas turbine engines face inefficiencies due to the need for separate compressor stages and increased engine length, which can result in higher fuel consumption and weight.
Innovation Solution
Incorporating a radial compressor impeller within the fan hub, which provides axial compression and structural support, allowing for a compact design that delivers compressed air directly to the core engine while enabling gear reduction for differential fan and turbine speeds.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If separate compressor stages are used in conventional gas turbine engines, then compression function is achieved, but engine length and weight increase
Solution Approach 1:
The patent combines the fan hub structure with a radial compressor impeller into a single integrated assembly. The impeller is positioned radially inwardly of the fan blades and within the hub, allowing the fan and compressor functions to share common structural support while eliminating the need for separate compressor stages, thereby reducing engine length without compromising compression capability
Solution Approach 2:
The fan hub is designed to serve multiple functions: it provides structural support for the fan blades, houses the radial compressor impeller, and acts as a structural support element itself through intermediate radial vanes. This multi-functionality allows a single component to replace what would traditionally require multiple separate components, reducing both length and complexity
2Stress or pressure
If additional compressor stages are added to increase pressure ratio, then compression capability improves, but engine weight and length increase
Solution Approach 1:
The patent changes the operational parameters of the radial compressor impeller by utilizing the high rotational speeds achieved through gear reduction. This allows the impeller to generate higher pressure ratios than would be possible at conventional fan speeds, enabling increased compression capability without adding weight through additional compressor stages
3Device complexity
If fan and turbine rotate at the same speed, then direct drive is simple, but fan size and compression efficiency are limited
Solution Approach 1:
The patent introduces a radial compressor impeller as an intermediary component between the fan and the core compression system. The impeller receives air from the fan's axial flow and converts it to radial flow for compression, enabling efficient energy transfer and allowing the fan and turbine to operate at different optimized speeds through gear reduction while maintaining high compression efficiency
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 configuration enhances engine efficiency by reducing overall length and weight, potentially lowering fuel burn and enabling higher pressure ratios without additional compressor stages.
Implementation Method 1
The radial compressor impeller is adapted for receiving air from the fan in an axial flow and for compressing the air radially outwardly thereof
Implementation Method 2
This has allowed the fan drive turbine and the fan rotor to rotate at different speeds. In another embodiment according to the previous embodiment, the fan rotor is driven to rotate through a gear reduction
Data Source
AI summary
A fan rotor has a hub, and a plurality of axial flow fan blades extending radially outwardly of the hub. A radial compressor impeller is positioned radially inwardly of the fan blades. The radial compressor impeller has an upstream inlet which extends generally in an axial direction defined by an axis of rotation of the hub. The radial flow compressor impeller has an outlet that extends radially outwardly of the inlet, and into a supply passage for supplying air to a core engine. An engine is also disclosed.