Heat Exchanger Integration in V-Shaped Gearbox
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Solution Overview
Problem
Integrating a heat exchanger into an aircraft turbine engine equipped with a V-shaped gearbox poses challenges due to spatial constraints and the need for efficient cooling of equipment, while existing solutions often require extensive piping and additional structural reinforcement.
Innovation Solution
Mounting the heat exchanger between the lateral arms of the V-shaped gearbox, which allows for optimal use of unused space and eliminates the need for long cooling fluid pipes, and incorporating means for fixing the exchanger to the gearbox to rigidify it and reduce deformation, potentially eliminating transverse reinforcing members.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of stationary object
If the heat exchanger is mounted between the arms of the V-shaped gearbox, then the integration is facilitated and the assembly mass is reduced, but the space between the arms must be sufficiently large to accommodate the exchanger
Solution Approach 1:
The heat exchanger is integrated into the V-shaped gearbox structure by mounting it between the two arms, combining two separate components (gearbox and heat exchanger) into a single compact assembly. This eliminates the need for separate mounting structures and reduces overall assembly mass while utilizing previously unused space.
Solution Approach 2:
The heat exchanger is positioned in the spatial dimension between the two arms of the V-shaped gearbox, utilizing the three-dimensional space that would otherwise be empty. This dimensional placement allows integration without increasing the footprint or requiring additional structural support.
2Weight of stationary object
If the exchanger is located close to the equipment supported by the gearbox, then the mass of the assembly is reduced by eliminating long pipes, but the positioning must be precisely controlled
Solution Approach 1:
The heat exchanger is integrated directly into the gearbox structure with the equipment, eliminating separate piping systems. The cooling fluid circuit is formed by directly connecting the exchanger to the equipment it serves, removing the need for long external pipes and reducing overall assembly mass.
3Strength
If means for fixing the exchanger to the gearbox are incorporated, then structural rigidity is improved and deformation is reduced, but the device complexity increases
Solution Approach 1:
The fixing means for securing the heat exchanger to the gearbox are integrated into the overall assembly structure. The same structural elements that provide mechanical support for the gearbox also serve to secure the heat exchanger, eliminating the need for separate fixing mechanisms and maintaining structural rigidity without increasing complexity.
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 facilitates efficient integration of the heat exchanger, reduces the assembly's mass, and provides easier access for maintenance by locating the gearbox at the lower portion of the turbine engine, while the exchanger's proximity to the gearbox eliminates the need for lengthy cooling fluid output pipes and enhances structural rigidity.
Implementation Method 1
air taken off in a flow of the turbine engine being intended to circulate in a first circuit to exchange thermal energy with the oil circulating in the second circuit, the oil thus cooled
Data Source
AI summary
Aircraft turbomachine comprising at least one heat exchanger (40) and a gearbox (10) in a V-shaped overall configuration and comprising two lateral arms (20) joined together by a central joining piece, the heat exchanger being mounted between the arms of the gearbox.