Gas Turbine Engine Heat Exchanger for Compressor Exit Cooling
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Solution Overview
Problem
Conventional turbofan engine design is limited by high temperatures at the exit stage of the high pressure compressor, which restricts compressor pressure ratio and overall engine performance, as reducing gas temperatures for cooling core components is costly and inefficient.
Innovation Solution
Incorporating a cooled cooling air system that uses a heat exchanger to reduce the temperature of airflow from the compressor, which is then used to cool critical components like the high pressure turbine rotor blades, allowing them to withstand higher operating temperatures while maintaining or increasing thrust output.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional turbofan engine design operates at high temperatures at the exit stage of the high pressure compressor, then compressor pressure ratio is restricted and engine performance is limited, but reducing gas temperatures for cooling core components is costly and inefficient
Solution Approach 1:
The patent segments the cooling system into multiple independent cooling channels that can be controlled separately. Each cooling channel can be adjusted to provide optimal cooling to different core components based on their specific thermal requirements, allowing the engine to operate at higher temperatures overall while maintaining necessary cooling where required.
Solution Approach 2:
The patent implements variable geometry cooling channels that can change their flow area and cooling capacity as engine operating conditions change. This allows the cooling system to adapt to different temperature and pressure conditions, enabling the engine to operate efficiently across a wider range of temperatures including higher temperatures that improve performance.
2Strength
If a cooling system is added to reduce temperatures of core components, then components can withstand higher operating temperatures, but the size and weight of the engine increase
Solution Approach 1:
The patent integrates cooling channels directly within the structure of core components such as turbine blades and combustor liners. The cooling channels are nested within the component geometry itself, eliminating the need for separate external cooling systems and reducing overall engine weight while maintaining effective cooling capability.
Solution Approach 2:
The patent employs thin-walled component designs with integrated cooling channels that provide efficient heat transfer with minimal material. The thin film walls allow effective cooling while reducing the weight penalty associated with thicker, heavier cooling structures.
3Strength
If a cooling system is added to reduce temperatures of core components, then components can withstand higher operating temperatures, but the complexity of the system increases
Solution Approach 1:
The patent combines multiple cooling functions into unified cooling channels that serve multiple components or regions simultaneously. By merging cooling pathways and using shared cooling air sources, the system reduces the number of independent cooling subsystems and simplifies overall system architecture while maintaining comprehensive cooling coverage.
Solution Approach 2:
The patent designs cooling channels that utilize the engine's own operating conditions (such as pressure differentials and available cooling air from compressor stages) to drive the cooling process. This self-regulating approach reduces the need for complex external control systems and active management of the cooling function.
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 cooled cooling air system enables the turbofan engine to operate at higher temperatures with improved performance by reducing component stress and maintaining or enhancing thrust output, while minimizing the size and weight increases associated with cooling systems.
Implementation Method 1
Incorporating a cooled cooling air system that uses a heat exchanger to reduce the temperature of airflow from the compressor
Data Source
AI summary
A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000).