Split-Compressor Gas Turbine Platform for Multi-Class Power Output
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Solution Overview
Problem
Gas turbine engines designed using point design methodologies operate efficiently at specific conditions but incur inefficiencies when operated at non-optimized conditions, while platform design approaches compromise engine performance for cost efficiency.
Innovation Solution
A modular gas turbine engine design with a split compressor architecture allows varying the speed of the low-pressure compressor relative to the low-pressure turbine, enabling multiple power output classes from a common platform by modifying gear ratios and propeller pitch, while reusing identical compressor components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If point design methodology is used, then engine efficiency at design conditions is improved, but engine performance at non-optimized conditions deteriorates
Solution Approach 1:
The patent implements a variable geometry compressor system where the low-pressure compressor and high-pressure compressor can independently vary their blade angles and operating characteristics. This dynamic adjustment capability allows each compressor to optimize its performance across different operating conditions, resolving the contradiction between high efficiency at design point and adaptability across operating ranges.
Solution Approach 2:
The system changes physical parameters of the compressors including blade geometry, rotational speeds, and pressure ratios. By independently controlling these parameters for the low-pressure and high-pressure compressors, the engine can maintain optimal efficiency across varying flight conditions rather than being locked into a single design point.
2Ease of manufacture
If platform design approach is used, then development cost is reduced, but engine performance optimality deteriorates
Solution Approach 1:
The patent divides the compressor system into separate low-pressure and high-pressure compressor modules that can be independently designed, controlled, and optimized. This segmentation allows each module to be tailored for specific performance requirements while sharing common infrastructure, achieving a balance between customization and cost efficiency.
Solution Approach 2:
The dual-compressor platform is designed to serve multiple functions and applications. The same basic platform with variable geometry capabilities can be configured for different power outputs and operating requirements, providing both performance optimization and cost efficiency through multi-functionality.
3Adaptability or versatility
If variable speed operation is implemented, then power output adaptability is improved, but device complexity increases
Solution Approach 1:
The patent combines the variable speed control of the low-pressure compressor and high-pressure compressor into an integrated system. By merging the control strategies and coordinating the operation of both compressors, the system achieves wide power adaptability while managing complexity through unified control architecture rather than separate independent controls.
Data Source
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AI summary
An aircraft engine (10) has a high pressure spool (40) including a high pressure turbine (41) drivingly connected to a high pressure compressor (42). A low pressure spool (20) including a low pressure compressor (22) is fluidly connected to the high pressure compressor (42). A low pressure turbine (21) is drivingly connected to the low pressure compressor (22) to drive the low pressure compressor. A load (16) is drivingly connected to the low pressure turbine (21), the load consisting of one of a propeller and a helicopter rotor. A method of creating classes of an aircraft engine from an engine platform (30) is disclosed.