| 摘要 |
<p>A program-controlled heat management system for an aircraft's bypass gas turbine (turbofan) engine installation, in which the engine's fuel system (100) is put into direct heat exchange relationship with the engine's own oil system (200), and with an engine-driven electrical generator's oil system (300), by means of respective fuel/oil heat exchangers (107,109) and also into selective indirect heat exchange relationship with a variable proportion of the engine's bypass air by means of an engine oil/air heat exchanger (202). The fuel system (100) is switchable between four different fuel flow configurations in order to vary the heat flows between the fuel system (100) and the oil systems (200,300), two of the fuel flow configurations also involving recirculation of fuel from the engine's fuel system (100) to a fuel tank (102) in the aircraft wing (105) in order to put the fuel system (100) into selective heat exchange relationship with the tank (102) and hence with the airstream passing over the wing (105). Temperatures in the oil and fuel systems are monitored and kept within predetermined limits by selecting the appropriate fuel flow configuration and selectively dumping heat to the environment through the engine oil/air heat exchanger (202) and the aircraft wing (105) in a way which maximises the fuel efficiency of the engine.</p> |
