Gas Turbine Platform Design for Variable Speed Low Pressure Compressor
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Solution Overview
Problem
Gas turbine engines designed using point design methodologies operate efficiently at optimized conditions but incur inefficiencies when operating at non-optimized conditions, while platform design approaches compromise engine performance for cost efficiency.
Innovation Solution
Creating classes of gas turbine engines from a common engine platform by configuring the low pressure compressor to run at different speeds to produce varying power outputs, maintaining a consistent gas path profile and using common components across classes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If point design methodology is used, then engine efficiency at design conditions is improved, but efficiency at non-optimized conditions deteriorates
Solution Approach 1:
The patent creates a platform design where a single core engine configuration serves multiple applications and operating conditions. The common core includes standardized components (compressor, combustor, turbine, gas path) that can be adapted to different power requirements through peripheral component variations, enabling the engine to function efficiently across diverse operational scenarios rather than being optimized for 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 segments the engine into a common core portion and application-specific peripheral portions. The core contains standardized components that can be reused across multiple engine classes, reducing development costs. Meanwhile, peripheral components can be customized for specific performance requirements, maintaining optimal engine performance for each application without requiring complete redesign
3Use of energy by moving object
If different engine designs are created for different power outputs, then performance optimization is improved, but device complexity and recertification efforts increase
Solution Approach 1:
The patent establishes a universal core engine design that can produce multiple power output classes by varying operational parameters and peripheral components. This single standardized core replaces the need for multiple completely different engine designs, reducing certification complexity while maintaining performance optimization through parameter adjustments and component selections
Data Source
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AI summary
An aircraft engine has a high pressure spool including a high pressure turbine drivingly connected to a high pressure compressor. A low pressure spool including a low pressure compressor is fluidly connected to the high pressure compressor. A low pressure turbine is drivingly connected to the low pressure compressor to drive the low pressure compressor. A load is drivingly connected to the low pressure turbine, 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 is disclosed.