Patent ID: 8381510
Filing Date: 2013-02-26
Classification: F02C,F05D

Abstract:
1. A thrust control system for use in controlling the thrust output of a gas turbine engine, said thrust control system comprising: a first sensor for measuring a first engine operating parameter, wherein the first engine operating parameter is indicative of engine operation, and wherein said first engine operating parameter is at least one of a fan speed, a core engine pressure ratio, and a liner engine pressure ratio; a second sensor for measuring a first engine condition parameter, wherein the first engine condition parameter is a parameter whose change in value from a nominal value is indicative of deterioration of the gas turbine engine, and wherein said first engine condition parameter is at least one of a low pressure turbine discharge temperature, a high pressure rotor inlet temperature, a low pressure turbine rotor inlet temperature, and an exhaust gas temperature; a processor programmed to: an electric controller coupled to said processor for receiving the determined modified operating parameter demand value from the processor and first engine operating parameter value from the first sensor, said electric controller configured to control engine thrust based on a determined difference between the determined modified operating parameter demand of the first engine operating parameter and the first engine operating parameter value from the first sensor.