Optimization of cross-flow micro-channel heat exchanger module for application in high Mach aircraft gas turbine engines
Abstract
This study explores the design of highly compact air-fuel heat exchangers for high Mach aircraft turbine engines. The heat exchangers consist of a large number of modules that can be brazed together into a rectangular or annular heat exchanger outer envelope. In the module, fuel flows through parallel micro-channels while air flows externally perpendicular to the direction of the fuel flow over rows of short, straight fins. A theoretical model recently developed by Nacke for a single module is both validated experimentally, by simulating aircraft fuel with water, and expanded to actual heat exchangers and JP-8 aircraft fuel. An optimization study of the module's geometrical parameters is conducted at supersonic engine operating conditions in pursuit of highest heat transfer rate. These parameters are then adjusted based on such considerations as micro-fabrication limits, stress and rupture, and the need to preclude clogging of the fuel and air passage. Using the revised parameters, the analytical model is used to generate effectiveness plots for both rectangular and annular heat exchangers with one air pass and one, two and three fuel passes. These results demonstrate both the effectiveness of the module design and the versatility of the analytical tools at designing complex heat exchangers for high Mach aircraft gas turbine engines.
Degree
M.S.M.E.
Advisors
Mudawar, Purdue University.
Subject Area
Aerospace engineering|Mechanical engineering
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