Patent ID: 11959386
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A method for a gas turbine engine, comprising:
determining a first lubricant parameter during a first period of an engine operating cycle, the first lubricant parameter indicative of a first quantity of lubricant within a reservoir of the gas turbine engine, and the engine operating cycle corresponding to operation of the gas turbine engine for a single aircraft flight;
determining a second lubricant parameter during a second period of the engine operating cycle, the second lubricant parameter indicative of a second quantity of the lubricant within the reservoir; and
comparing the first lubricant parameter and the second lubricant parameter to determine a lubricant consumption parameter, the lubricant consumption parameter indicative of a quantity of the lubricant consumed by the gas turbine engine during the engine operating cycle.