Compressor Flowpath Heat Exchanger for Gas Turbine Thermal Management
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Solution Overview
Problem
Gas turbine engines face inefficiencies due to the inability to adjust temperatures of components during operation, leading to potential damage and premature wear, which existing cooling systems fail to address effectively.
Innovation Solution
A thermal management system incorporating a flowpath heat exchanger and thermal transport bus, with heat source and sink heat exchangers, is integrated into the compressor section, allowing for efficient heat transfer from airflow to a heat exchange fluid and subsequent dissipation, and utilizing a heat transfer member with a longer chord length than compressor stator vanes to enhance heat exchange.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If existing cooling systems are used to maintain component temperatures, then component temperature control is achieved, but engine operational efficiency deteriorates
Solution Approach 1:
The system changes the temperature parameter of the airflow through the compressor by introducing a flowpath heat exchanger that transfers heat from the airflow to a heat exchange fluid. This allows the airflow temperature to be adjusted within a desired range, improving component temperature control while maintaining engine efficiency through optimized thermal parameters
Solution Approach 2:
A heat exchange fluid serves as an intermediary medium between the airflow and the cooling system. The flowpath heat exchanger transfers heat from the airflow to this intermediary fluid, which then carries the heat away through the thermal transport bus to heat sink heat exchangers, enabling efficient temperature control without directly cooling the airflow with cold air
2Productivity
If heat transfer member chord length is increased, then heat exchange efficiency is improved, but device complexity increases
Solution Approach 1:
The heat transfer member is designed with a longer chord length than traditional compressor stator vanes, serving multiple functions: it acts as both a structural component and a heat exchange surface. This multi-functional design improves heat exchange efficiency by increasing the thermal contact area with the airflow while avoiding the need for separate complex heat exchange structures
Solution Approach 2:
The invention extends the heat transfer member in the chord length dimension (spanwise direction) rather than adding complexity in other dimensions. By increasing the chord length, the system utilizes the existing airflow passage volume more effectively for heat exchange, improving thermal performance without proportionally increasing structural complexity
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 system effectively reduces airflow temperature within the compressor, increasing the overall pressure ratio and operational efficiency of the turbomachine, while maintaining component temperatures within a desired range.
Implementation Method 1
a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath
Implementation Method 2
utilizing a heat transfer member with a longer chord length than compressor stator vanes to enhance heat exchange
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
A gas turbine engine includes a turbomachine 16 including a compressor section, a combustion section 26, a turbine section, and an exhaust section 32 arranged in serial flow order and together defining at least in part a core air flowpath 37. The gas turbine engine also includes a thermal management system 100 including a flowpath heat exchanger coupled to, or integrated into, one or more components of the compressor section, the combustion section 26, the turbine section, or the exhaust section 32 such that the flowpath heat exchanger is directly thermally coupled to an airflow through the core air flowpath 37.