Gas Turbine Engine Modular Core with Bypass Compression
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Solution Overview
Problem
Conventional gas turbine engines face limitations in modular design, requiring redesign of the engine core to meet different air pressure requirements for optimal performance across various configurations, such as civil and military applications, which is costly and time-consuming.
Innovation Solution
Incorporating a fan unit and bypass air compression means that ensure air exiting the bypass duct is at a higher pressure than entering the engine core, allowing for greater control over pressure rise and enabling the reuse of common engine core modules across different configurations by adjusting only the fan unit and/or adding bypass air compression.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the engine core is redesigned to meet different air pressure requirements for various configurations, then optimal performance is achieved for each configuration, but development cost and time increase significantly
Solution Approach 1:
The engine is divided into modular components: a common engine core and variable fan unit configurations. The fan unit can be selectively configured with or without bypass air compression means, allowing the same core to serve different applications (military vs civil) without redesign. This segmentation enables independent optimization of each module while maintaining compatibility across configurations.
Solution Approach 2:
The engine core is designed as a universal module that can be used across multiple engine configurations (military and civil aircraft). By making the core configurable rather than configuration-specific, the patent achieves multi-functionality where a single core design serves multiple purposes, eliminating the need for separate core designs for different applications.
2Stress or pressure
If additional low pressure fan stages are added to boost air pressure, then air pressure for engine core operation is improved, but device complexity increases
Solution Approach 1:
The fan unit is designed with dynamic configurability where bypass air compression means can be added or removed based on the specific engine configuration requirements. This allows the system to adapt its pressure-boosting capability dynamically rather than requiring permanent complex multi-stage fan arrangements, achieving variable performance with simpler base design.
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 allows for the use of a common engine core in different configurations without the need for redesign, reducing development costs and time, while maintaining optimal performance by ensuring air pressure is appropriate for both engine core operation and thrust production.
Implementation Method 1
bypass air compression means are provided such that, under substantially all engine power conditions, air at exit from the bypass duct is at a greater pressure than air delivered to the engine core intake
Data Source
AI summary
A gas turbine engine (2) comprises a fan unit (4,18,36,42,44,46) in flow relationship with an engine core and a bypass duct, of which said engine core and bypass duct (16) are in parallel flow relationship with each other. The engine core comprises a compressor (6), a combustor (8) and a turbine (10), with an inner casing (12) provided around said engine core which defines the engine core intake (32). The bypass duct (16) is defined by an outer casing (14) radially spaced apart from the fan unit (4,18,36,42,44,46) and the inner casing (12) along at least part of the length of the gas turbine engine (2). Bypass air compression means (28) are provided such that, under substantially all engine power conditions, air at exit from the bypass duct (16) is at a greater pressure than air delivered to the engine core intake (32).