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Environmental safety issues are a priority in the modernization development of aviation or ground-based combustion chambers of gas turbine engines. In order to reduce the emission of harmful substances from combustion products, a low-emission combustion system, which is based on the concept of LPP (Lean-premixed and prevaporised), is being used today. This concept implements the principle of burning “ultra-poor” premixed air-fuel mixtures. The operational experience of combustion chambers developed in accordance with the indicated concept shows that one of the implementation problems is the difficulty in ensuring a good start. This paper presents the results of adjusting the operating process of a modern combustion chamber, launching a gas turbine unit, including drawing up a fuel supply control algorithm, experiments with igniting ignition devices and setting the gas turbine on idle mode. A feature of the commissioning work is the debugging of the operating process of the combustion chamber directly as part of the gas turbine unit, bypassing the traditional pilot-testing on the rig.

Environmental safety of aviation engines is a very important problem for designers. The importance of this problem increases with the aviation engine thrust, because of the increase in such thermodynamic parameters as the temperature and pressure in the combustion chamber. In this case, the rise of temperature in the combustion zone results in the formation of NO x. Using the multinozzle fuel burning mode in the combustion chamber will make it possible to decrease the formation of harmful substances signifi cantly. Multinozzle combustion chambers of aviation gas turbine engines designed by the JSC "Kuznetsov" (Samara City, Russian Federation) in the course of the few last decades comply with the current requirements imposed on emissions. Comparative ecological characteristics of widespread aviation engines are presented in the article. The results of procedures of environmental testing of low-emission multinozzle combustion chambers for aviation gas turbine engines are described. It is shown that a multinozzle combustion chamber provides low NO x pollutant emissions and high reliability of aviation engine operation in diff erent operating conditions.

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