METHOD OF DEFINING GAS TURBINE GAS-DYNAMIC STABILITY MARGIN Russian patent published in 2009 - IPC G01M15/14 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aviation and is intended for testing aircraft incorporating gas turbine engines at whatever flight conditions. The proposed method includes measuring the flight altitude and Mach number and, at the engine intake, the air flow complete pressure fields matrix and complete pressure pulsations matrix. Circular irregularity and intensity of pulsations of complete pressure are defined. The parameter of flow irregularity and engine gas-dynamic stability margin is computed. The proposed method differs in that, to define the pulsations intensity, the pulsation frequency range is selected peculiar to the engine and direct Fourier transformation of the pulsation matrix is carried out, the transformation results are filtered in the selected pulsation frequency range, the matrix dispersion is defined for complete pressure pulsation intensity to be defined.

EFFECT: accurate determination of gas turbine stability margin at whatever operating conditions.

2 dwg