Oil supply correction method in case of starting aero-engine at plateau

Abstract

The invention belongs to the field of aero-engine oil supply, and particularly relates to an oil supply correction method in the case of starting an aero-engine at a plateau. The method comprises thefollowing steps of obtaining a power characteristic coefficient epsilon of an auxiliary power system and a power acting proportion coefficient lambda of the auxiliary power system, and calculating anauxiliary power correction coefficient K<auxiliary>; obtaining a correction coefficient K<conventional> performed according to the engine characteristics and an engine ground starting rotating speed rise rate N<2> Dot<ground>, and calculating an engine plateau starting rotating speed rise rate N<2> Dot< plateau>; and calculating a main fuel supply rule according to the engine plateau starting rotating speed rise rate N<2>Dot< plateau>. According to the method, the more real auxiliary power is obtained through correction according to the auxiliary power system power keeping characteristic, comprehensive conversion is performed to form the rotating speed rise rate correction amount according to the proportion relation between the auxiliary system power in the starting rotating speed range and the turbine power, the starting process is corrected, the rotating speed rise rate is more matched with the actual residual power, the oil supply amount is corrected to fully exert the starting potential, the starting time is shortened, and the starting success rate is increased.

Description

technical field [0001] The application belongs to the field of fuel supply for aero-engines, and in particular relates to a method for correcting fuel supply for aero-engine plateau start. Background technique [0002] In order to meet the needs of Air Force aircraft for combat and training on plateaus, military turbofan engines need to have the ability to start quickly and reliably at plateau airports. [0003] In the existing engine starting technology, the oil supply law of plateau starting is generally based on the ground design law, and the closed-loop control is carried out according to the simple pressure and temperature correction law of classic engine characteristics. This conventional correction method can better It is in line with the characteristics of the engine on the plateau, but this solution is to incorporate the working ability of the auxiliary power system into the engine system and correct it together, which means that the attenuation of the power of the ...

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Problems solved by technology

[0003] In the existing engine starting technology, the oil supply law of plateau starting is generally based on the ground design law, and the closed-loop control is carried out according to the simple pressure and temperature correction law of classic engine characteristics. This conventional correction method can better It is in line with the characteristics of the engine on the plateau, but this solution is to incorporate the working ability of the auxiliary power system into the engine system and correct it together, which means that the attenuation of the power of the auxiliary power system with the height of the plateau is the same as that of a typical aero engine by default. , did not fully consider the actual power retention characteristics of various auxiliary power systems, which is obviously not in line with the actual situation, and directly leads to a large deviation between the corrected auxiliary system power and the actual power, which in turn leads to the design value of the rise rate in the starting process. The actual remaining power does not match, the fuel supply is not suitable, the starting time at high altitude is too long, or there are phenomena such as stalling and overheating, which directly lead to starting failure, and the ability of the engine to start at high altitudes is not fully exerted, affecting the reliability of the aircraft at high altitudes, starting time and Success rate is not guaranteed

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