Starting ignition oil supplying method of aviation gas turbine engine

Abstract

The invention discloses a starting ignition oil supplying method of an aviation gas turbine engine. The starting ignition oil supplying method is characterized in that a gradual oil supplying mode is adopted for ignition of a combustion chamber in a starting process: firstly, at the moment that an oil supplying condition is met in a process of starting the engine, a control system supplies oil according to the initial ignition oil quantity; the initial ignition oil quantity is as follows: the maximum oil supply deviation value of the control system is subtracted on the basis of the lean oil ignition boundary oil quantity of the combustion chamber of the engine; then the control system carries out the gradual oil supply according to the oil quantity rising slope, and the ignition oil quantity rising slope is the difference between the lean oil combustible oil quantity boundary and the rich oil combustible oil quantity boundary of the engine, and relates to the oil supply maximum deviation value of the control system and a ratio of the oil supply maximum deviation value to the theoretical specified ignition time. The starting ignition oil supplying method has the advantages that the defect of depending on oil quantity control and measuring precision in starting ignition oil supply according to an oil-gas ratio in the prior art is overcome, and the reliable ignition of the combustion chamber in ground and air starting processes of the engine can be ensured.

Description

technical field [0001] The invention relates to the field of starting design of an aviation gas turbine engine, in particular to an ignition fuel supply method for starting an aviation gas turbine engine. Background technique [0002] At present, the more common starting ignition and oil supply methods mainly include: [0003] control law, using a combination of parameters Referred to as oil-gas ratio to design ignition and fuel supply rules, this method is currently widely used in aero-engine control. This fuel supply method is based on the ignitable fuel-air ratio range determined by the characteristics of the components of the combustion chamber, which better reflects the physical characteristics of combustion. This oil supply method depends on the control and metering accuracy of the oil quantity, and is not very adaptable. When the oil quantity control and metering accuracy of the engine control system cannot meet the requirements, the actual oil supply during the ...

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Problems solved by technology

[0005] The purpose of the present invention is to provide a method for starting ignition and fuel supply of an aviation gas turbine engine, which solves the problem of relying on the control of oil quantity and the accuracy of metering that exists in the traditional method of starting ignition and fuel supply according to the oil-gas ratio. , use and other differences have better adaptability, which can ensure the reliable ignition of the combustion chamber of the aviation gas turbine engine during ground and air start-up

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