Trapezoidal Pre-Cooler Layout for Aircraft Pylon Integration
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Solution Overview
Problem
Existing precooler designs with parallelepiped geometry hinder flexibility in integration with surrounding aircraft components, particularly the pylon, limiting space utilization and efficiency.
Innovation Solution
A heat exchanger with a longitudinal arrangement and trapezoidal geometry, featuring plates with stepped leading edges and gaps between lateral walls, optimizing coolant flow and maximizing heat exchange area within constrained spaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a parallelepiped shape is used for the heat exchanger, then the structure is simple and easy to manufacture, but the flexibility in integration with surrounding elements like the pylon is compromised
Solution Approach 1:
The heat exchanger is divided into multiple plates arranged in a stacked configuration, allowing each plate to be independently manufactured and then assembled. This segmentation enables the complex trapezoidal overall shape to be created from simpler individual components, maintaining ease of manufacture while achieving the required adaptability to the pylon geometry.
Solution Approach 2:
The heat exchanger employs a trapezoidal shape with asymmetric dimensions, where the first dimension (longitudinal) is longer than the second dimension (transverse). This asymmetric geometry allows the heat exchanger to conform to the specific spatial constraints of the pylon mounting location, providing flexibility in integration while still maintaining structural simplicity through the regular stacked plate arrangement.
2Ease of manufacture
If a parallelepiped shape is used for the heat exchanger, then the manufacturing process is straightforward, but the space utilization within constrained aircraft environments is limited
Solution Approach 1:
The trapezoidal shape with specific dimensional relationships (first dimension longer than second dimension) allows the heat exchanger to efficiently utilize the available space within the pylon constraints. The asymmetric geometry enables better fitting into the constrained volume compared to a standard parallelepiped, maximizing space utilization while keeping the manufacturing process relatively straightforward through the use of stacked plates.
Solution Approach 2:
The heat exchanger transitions from a conventional three-dimensional block (parallelepiped) to a two-dimensional stacked plate arrangement viewed in cross-section. This dimensional reorganization allows the heat exchanger to flatten and adapt to the constrained space available in the aircraft pylon, effectively maximizing space utilization by utilizing the available length and width more efficiently through the stacked configuration.
3Productivity
If the heat exchanger is designed to maximize heat exchange area, then the cooling capacity increases, but the device complexity increases
Solution Approach 1:
The heat exchange function is segmented across multiple identical or similar plates arranged in a stack. Each plate contributes to the total heat exchange area, and the plates can be manufactured using standardized processes. This segmentation allows the system to achieve high cooling capacity through cumulative area while keeping individual component complexity low and enabling modular assembly.
Solution Approach 2:
The plates serve multiple functions simultaneously: they provide heat exchange surfaces, define the trapezoidal overall shape, create internal channels for coolant flow, and structure the internal hollow areas for bleed air flow. This multi-functionality reduces device complexity by eliminating the need for separate components for each function, while still maximizing heat exchange area through the stacked plate configuration.
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
Enhances heat exchange performance and space utilization, allowing for higher cooling capacity within limited aircraft environments.
Implementation Method 1
at least a plurality of the plates comprise an inner hollow area configured to be in fluidic communication with a source of hot bleed air and to conduct a flow of the hot bleed air therethrough
Implementation Method 2
a plurality of channels defined between contiguous plates; wherein each of the plurality of plates comprises a leading edge oriented towards the inlet and configured for diverting the incident flow of coolant towards the contiguous channels
Data Source
AI summary
An aircraft heat exchanger arranged longitudinally and including a casing with an inner chamber configured so that coolant flows longitudinally from an inlet to an outlet, a plurality of laterally spaced longitudinally extending inner chamber plates, and a plurality of channels defined between contiguous plates. Each plate includes a leading edge oriented towards the inlet and configured to divert coolant towards the channels. A plurality of the plates include an inner hollow area configured to conduct a flow of hot bleed air therethrough. Leading edges of a first group of plates are arranged in a stepped pattern. A gap defined between the first group of plates and a first casing lateral wall establishes a fluid coolant communication through the first group of plates between the casing inlet and outlet. The lateral distance between each leading edge of the first group of plates and the first lateral wall decreases longitudinally.