CMC Airflow Flow Guides for Gas Turbine Cooling
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Solution Overview
Problem
Cooling CMC components in gas turbine engines remains a challenge due to non-uniform cooling loads and the need for efficient airflow distribution within these components.
Innovation Solution
A cooling structure featuring a ceramic matrix composite component with an internal chamber, a spar within the chamber, and flow guides on the spar or matrix component to direct airflow towards specific areas, such as the leading and trailing edges, to enhance cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is supplied to CMC components, then cooling effect is achieved, but non-uniform cooling loads cannot be effectively addressed
Solution Approach 1:
The flow guides create localized flow control features on the spar surface that direct cooling air to specific high-heat areas such as the leading edge and trailing edge of the CMC component. This localizes the cooling effect where it is most needed, addressing the non-uniform cooling load problem by providing enhanced cooling at critical locations while maintaining adequate cooling across the entire component surface.
2Reliability
If flow guides are added to direct airflow, then cooling uniformity is improved, but device complexity increases
Solution Approach 1:
The flow guides are integrated directly onto the spar structure, merging the flow control function with the existing structural component. This eliminates the need for separate, additional flow control devices and reduces overall system complexity while still achieving the desired airflow distribution and cooling uniformity across the CMC component.
3Temperature
If cooling air is directed against CMC component, then thermal management is achieved, but airflow distribution efficiency is insufficient
Solution Approach 1:
The flow guides act as intermediary elements between the cooling air supply and the CMC component surface. They mediate the airflow by directing and shaping it to ensure efficient distribution across the component, particularly enhancing coverage at critical heat zones like the leading and trailing edges, thereby improving overall thermal management 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
The proposed solution effectively manages airflow to address non-uniform cooling loads, improving the thermal management of CMC components in gas turbine engines and enhancing their durability and performance.
Implementation Method 1
Flow guides are formed on one of an outer surface of the spar and the inner surface of the matrix component. The flow guides direct airflow towards a portion of the inner surface.
Data Source
AI summary
A component for a gas turbine engine includes a matrix composite component having a radially outer end and a radially inner end. The ceramic matrix component having an internal chamber defined by an inner surface. A spar is received within the internal cavity, and spaced from an inner surface of the matrix component defining a chamber with the inner surface. Flow guides are formed on one of an outer surface of the spar and the inner surface of the matrix component. The flow guides direct airflow towards a portion of the inner surface. An air inlet chamber is formed at one radial end of the spar and an air outlet chamber formed at an opposed radial end of the spar. The air inlet chamber is defined such that air will flow into the internal chamber, outwardly of the spar, and inwardly of the inner surface of the matrix component. A gas turbine engine is also disclosed.