Patent ID: 7966965
Filing Date: 2011-06-28
Classification: F01D,F16N

Abstract:
1. An aircraft gas turbine oil tank, comprising: a casing, which is connected to a filler port; an optical indicator associated with the oil tank, which includes at least first, second and third powered light emitters, each for emitting an optical signal at a specified oil tank filling level; the first powered light emitter emitting an optical signal when an actual oil level in the oil tank is between, inclusive, a low acceptable filling level and a high acceptable filling level of the tank; the second powered light emitter emitting an optical signal when the actual oil level in the oil tank is above the high acceptable filling level of the tank; the third powered light emitter emitting an optical signal when the actual oil level in the oil tank is below the low acceptable level but above a low quantity filling level at which a given quantity of oil added to the oil tank will bring the actual oil level in the oil tank to between, inclusive, the low acceptable filling level and the high acceptable filling level of the tank.