초록 ▼

A method and system for controlling the position of a variable pitch vane stage (34) in a gas turbine engine (10) uses a feedback loop comparing the current compressor pressure ratio to a reference compressor pressure ratio. The reference pressure ratio is determined from a plurality of current engi

A method and system for controlling the position of a variable pitch vane stage (34) in a gas turbine engine (10) uses a feedback loop comparing the current compressor pressure ratio to a reference compressor pressure ratio. The reference pressure ratio is determined from a plurality of current engine operating parameters which identify a unique point on the compressor operating line.

대표청구항 ▼

A method for controlling the position of a variable area stator vane stage in a gas turbine engine having a first, low pressure compressor disposed upstream of a second, high pressure compressor, said first compressor having a compressor inlet for receiving a flow of gas to be compressed, the second

A method for controlling the position of a variable area stator vane stage in a gas turbine engine having a first, low pressure compressor disposed upstream of a second, high pressure compressor, said first compressor having a compressor inlet for receiving a flow of gas to be compressed, the second compressor including a compressor outlet for exhausting the compressed gas, and said first and second compressors each further including a rotor having at least one stage of rotating blades, comprising the steps of: a) measuring the total gas pressure at the compressor inlet; b) measuring the total gas pressure at the compressor outlet; c) determining, responsive to the measured inlet and outlet gas pressures, the current pressure ratio for the compressor; d) determining, responsive to at least one of a plurality of current engine operating characteristics, including the overall compressor pressure ratio of the first and second compressors, a desired compressor pressure ratio including the steps of: determining, in advance, a series of preferred engine operating points, each preferred point, having a corresponding value of each engine operating characteristic and compressor pressure ratio, determining the current value of each engine operating characteristic, identifying a preferred engine operating point responsive to the determined current characteristic, said preferred point being selected from among the series of preferred points, and setting the desired compressor pressure ratio equal to the compressor pressure ratio corresponding to the preferred engine operating point; e) comparing the current pressure ratio to the desired pressure ratio; and f) causing the position of the stator vane stage to be varied responsive to the comparing step for minimizing the different between the current and desired pressure ratios.