Lubricant system for gas turbine aircraft engine, has ejector-device, where part of lubricant flow stream removed from tank is supplied to ejector device, and low pressure arises in tank for return flow of lubricant from load into tank

摘要

The system (10) has a lubricant tank (15) for holding lubricant. A lubricant flow pump (16) is provided for withdrawing lubricant from the tank and for supplying the lubricant to the loads (11, 12, 13, 14) in a direction. A lubricant return flow device (22) is designed as an ejector-device, where a part of a lubricant flow stream removed from the tank is supplied to the ejector device, and a low pressure arises in the lubricant tank for return flow of the lubricant from loads into the tank.