Integrating Heat Exchanger into Aircraft Turbine Intermediate Support Casing
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Solution Overview
Problem
Aircraft turbine engines face challenges in efficiently cooling oil due to increased thermal rejection, leading to the need for improved integration of heat exchangers that are compact, lightweight, and cost-effective.
Innovation Solution
A system integrating a heat exchanger within an intermediate support casing between the low-pressure and high-pressure compressors, allowing for heat exchange with air, which is partially or fully integrated into the casing, reducing obstruction and production costs while maintaining engine performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a heat exchanger is added to cool oil in the turbine engine, then oil cooling efficiency is improved, but device complexity and production cost increase
Solution Approach 1:
The heat exchanger is integrated into the intermediate support casing, merging two separate components (heat exchanger and support casing) into a single unified structure. This reduces the number of discrete parts, simplifies assembly, and lowers production cost while maintaining the oil cooling function.
Solution Approach 2:
The intermediate support casing serves dual functions: it provides structural support between the compressors and simultaneously acts as the housing for the heat exchanger. This multi-functionality eliminates the need for a separate dedicated heat exchanger component, reducing system complexity.
2Temperature
If a heat exchanger is added to cool oil in the turbine engine, then oil cooling efficiency is improved, but production cost increases
Solution Approach 1:
By integrating the heat exchanger into the intermediate support casing, the patent reduces the total number of components that need to be manufactured and assembled. This consolidation lowers production cost through reduced material usage, simplified manufacturing processes, and fewer assembly operations.
3Volume of moving object
If a heat exchanger is integrated into the intermediate support casing, then the turbine engine becomes more compact and lighter, but the primary duct obstruction increases
Solution Approach 1:
The heat exchanger is strategically positioned within the intermediate support casing at a location where it provides effective oil cooling while minimizing interference with the primary duct airflow. The design optimizes the local placement to balance cooling efficiency with aerodynamic performance.
Solution Approach 2:
The heat exchanger is configured to partially obstruct the primary duct, creating a controlled restriction that generates turbulence and enhances heat transfer efficiency. This partial obstruction is deliberately designed to achieve superior cooling performance while maintaining acceptable airflow characteristics.
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 integration results in a more compact, lighter, and cost-effective turbine engine with improved oil cooling efficiency, enhancing overall engine performance and reducing production costs.
Implementation Method 1
a heat exchanger (3) intended to cool the oil by heat exchange with air
Data Source
AI summary
A system for cooling oil in an aircraft turbine engine includes an intermediate support casing configured to be located between a low-pressure compressor and a high-pressure compressor of the aircraft turbine engine. The system further includes a heat exchanger for cooling the oil by heat exchange with air, wherein the heat exchanger is at least partially integrated into the intermediate support casing.