The article discusses the direction of development of promising multimode aviation gas turbine engines (GTE). It is shown that the development of GTE is on the way to increase the parameters engine workflow: gas temperatures in front of the turbine T*g and the degree of pressure increase in the compressor P*K. It is predicted that the next generation engines will operate with high parameters of the working process, T*g = 2000 – 2200 K, π*K = 60 - 80. At this temperature of gases in front of the turbine, the working mixture in the combustion chamber (CC) is stoichiometric, which sharply narrows the range of stable operation of the CC and its efficiency drops sharply in off-design gas turbine engine operation modes. To expand the range of effective and stable work, it is proposed to use an advanced aviation GTE: Adaptive Type Combustion Chamber (ATCC). A scheme of the ATCC and the principles of its regulation in the system of a multi-mode gas turbine engine are presented. In the regulation of ATCC, algorithms for adaptive choice of options and self-adjusting adaptive algorithms can be used. The use of ATCC in future aviation multimode GTEs will greatly expand their range of stable and efficient operation.