Cooled Cooling Air Assembly for Turbine Blade Temperature Control
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Solution Overview
Problem
Existing gas turbine engines face challenges in efficiently cooling components due to high temperatures, as pressurized airflows from the compressor section are either too hot or lack sufficient pressure to effectively cool critical components like the stage 1 high pressure turbine rotor blade.
Innovation Solution
A cooled cooling air system (CCA) is implemented, utilizing low pressure airflow from a cold location to cool high pressure airflow through a heat exchanger, which then cools hot components of the turbomachine via a cold side and hot side bleed assembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If pressurized airflows from the compressor section are used for cooling, then cooling capability is improved, but the airflow is either too hot or lacks sufficient pressure to effectively cool critical components
Solution Approach 1:
The cooling system is divided into separate cold side and hot side assemblies with distinct functions. The cold side assembly handles cooling airflow extraction and delivery, while the hot side assembly manages the hot airflow path and heat exchanger integration. This segmentation allows independent optimization of each subsystem to resolve the contradiction between cooling effectiveness and reliability.
Solution Approach 2:
A heat exchanger is introduced as an intermediary component between the cold and hot airflow systems. This heat exchanger enables thermal energy transfer from the hot airflow to the cold airflow, allowing the cold side to provide effective cooling while the hot side maintains proper airflow characteristics without direct mixing of the two streams.
2Productivity
If high pressure airflow is used for cooling, then cooling performance is improved, but interference with other engine systems increases
Solution Approach 1:
The system provides different airflow pressures to different locations based on local requirements. The cold side bleed assembly extracts airflow at specific pressure levels appropriate for cooling component surfaces, while the hot side maintains higher pressure for heat exchanger operation. This localized pressure differentiation optimizes cooling performance while minimizing interference with other engine systems that require specific pressure ranges.
Solution Approach 2:
The cooling system incorporates variable geometry components and controllable airflow paths that can dynamically adjust pressure and flow rates based on engine operating conditions. This dynamic capability allows the system to maintain optimal cooling performance across different flight regimes while adapting to minimize interference with other engine systems under varying operational demands.
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 configuration enhances the operational efficiency and performance of gas turbine engines by effectively cooling critical components while minimizing interference with other systems.
Implementation Method 1
a cooled cooling air system (CCA) is implemented, utilizing low pressure airflow from a cold location to cool high pressure airflow through a heat exchanger
Data Source
AI summary
A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a cooled cooling air (CCA) system, the CCA system including: a CCA heat exchanger; a cold side bleed assembly; a hot side bleed assembly; and a valve assembly operable with the cold side bleed assembly and with the hot side bleed assembly, the valve assembly structured to modulate airflows through the cold side bleed assembly and through the hot side bleed assembly in tandem.