METHOD TO CONTROL OIL CONSUMPTION IN AIRCRAFT GAS TURBINE ENGINE Russian patent published in 2010 - IPC F02C9/00 

FIELD: engines and pumps.

SUBSTANCE: in compliance with proposed method, oil consumption of aircraft gas turbine engine q_M is determined in cruising conditions and engine steady state. Additionally, flight altitude H is measured as well as parametre "П" describing gas turbine engine operating conditions. Oil system oil temperature t_M is also measured. Note here that maximum flight altitude magnitude H^max is generated as well as lower and upper values of parametre "П" of aircraft cruising conditions "П"^1max and "П"^2max, respectively, and maximum amplitude of variation of said parametre for preset time interval dT of cruising flight d"П"^max. Then, measured altitude H is compared with H^max, while "П" is compared with "П"^1max and "П"^2max as well as variation of parametre "П" with d"П"^max. If H≥H^max and "П"^1max≤"П"≤"П"^2max, and "П" and П≤d"П"^max, then q_M is calculated proceeding from mathematical dependence. where Q_MH is the amount of oil in oil tank at the beginning of time interval dT; d - coefficient of the thermal expansion of oil; t_{M inlet} is the oil temperature in at engine inlet; Q_MK is the amount of oil in oil tank (4) at the end of time interval dT; t_{M inlet} is the oil temperature at the engine inlet at the end of dT; dT is preset time interval from the first measurement of q_m to the last measurement of said value. Generated also are maximum q_M at the starting period of engine operation for every subsequent flight, q_{M add.1}. q_M mean arithmetic values is determined. Maximum tolerable deviation of q_M at final period of engine operation is generated. Magnitudes q_M are compared with q_{M add.1} dq_M with dq_{M add.2}. Magnitudes 2 dq_M are compared with dq_{M add2}. In case q_M<q_{M add1} and dq_M<dq_{M add2}, gas turbine engine operation is continued. Otherwise, fault case is sought for.

EFFECT: higher quality and accuracy of control over qM.

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