Aircraft Precooler Heat Exchanger Nacelle Relocation
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Solution Overview
Problem
Current aircraft turbine engine precooler heat exchangers are mounted in the strut, which complicates access and increases the number of interfaces, requiring multiple pipes and potentially unnecessary thermal protection due to the presence of hot and cold air flows.
Innovation Solution
The precooler heat exchanger is relocated to the nacelle, where it can be integrated into the engine's outer annular housing, reducing the need for separate lines and simplifying access by using the air flow directly from the fan duct, thereby reducing the number of interfaces with the strut and eliminating the need for thermal blankets or double-skin pipes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the precooler heat exchanger is mounted in the strut, then the system structure is established, but access for maintenance becomes difficult and the number of interfaces increases
Solution Approach 1:
The precooler heat exchanger is extracted from the strut and relocated to the engine nacelle. This removes the complex piping interfaces from the strut structure, simplifying both the strut design and maintenance access. The heat exchanger is now directly accessible in the nacelle without requiring strut disassembly.
Solution Approach 2:
The heat exchanger is integrated into the engine nacelle structure, merging two previously separate systems (heat exchanger mounting and nacelle structure). This consolidation reduces the number of separate components and interfaces, particularly eliminating the need for separate piping to route hot and cold air flows through the strut.
2Reliability
If hot and cold air flows are routed through the strut, then the heat exchanger functions, but thermal protection becomes necessary increasing system complexity
Solution Approach 1:
The hot and cold air flow paths are extracted from the strut structure. Only the mixed and cooled air pipe remains in the strut, eliminating the need for thermal protection of multiple high-temperature and low-temperature lines. This separates the thermal management function from the structural mounting function.
Solution Approach 2:
Instead of routing hot and cold air flows through the strut and providing thermal protection, the approach is inverted: the heat exchanger is relocated to the nacelle where it can directly utilize the engine's air flow, and only the final cooled air needs to be routed to the strut.
3Device complexity
If the precooler is mounted in the nacelle, then access for maintenance is improved and system is simplified, but the heat exchanger must be integrated into the engine structure
Solution Approach 1:
The heat exchanger is merged with the engine nacelle structure, utilizing existing spaces and airflow paths within the nacelle. This integration leverages the existing engine infrastructure rather than requiring completely new mounting structures, simplifying the overall system architecture.
Solution Approach 2:
The engine nacelle structure serves multiple functions: it houses the heat exchanger, provides airflow paths for the precooler, and maintains structural integrity. This multi-functionality reduces the need for separate dedicated structures for each 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
This configuration simplifies and lightens the system, improves access for maintenance, and reduces the risk of fire-related issues by eliminating the need for thermal protection, as only cooled air is routed to the strut.
Implementation Method 1
The exchanger comprises a first air circuit, the input of which is connected by a line to means for taking off hot air, and the output is connected to means for supplying hot air to the aircraft. The air is taken off at the engine and transported to the first air circuit of the exchanger through a line which passes through the secondary duct to the inside of a structural arm and is then connected to the input of the first air circuit. The exchanger comprises a second air circuit which is supplied with air which is taken off in the fan duct of the turbine engine, the air then being discharged to the outside after exchanging heat with the air from the first air circuit, for the purpose of the cooling thereof.
Data Source
AI summary
An aircraft turbomachine including a nacelle and an engine further including at least one outflowing jet of air, wherein a heat exchanger of the precooler type for supplying air to the aircraft is mounted in the nacelle. The exchanger includes a primary circuit, the inlet of which is connected to a supply of compressed air from the engine and the outlet of which is connected to an air supply for supplying air to the aircraft, and a secondary circuit supplied with air taken from said air flow.