| 摘要 |
<p>The invention relates to gas-turbine engines with continuous combustion in high-velocity gas flow by open circuit on high-calorific gas-turbine fuels. It can be used in transport, for instance aviation, and in power engineering installations, and as drive in gas transportation units. The engine includes at least low pressure compressor, high pressure compressor with high-pressure turbine, high pressure combustion chamber placed between those, with device for fuel supply, low pressure combustion chamber with device for fuel supply. The engine is arranged with possibility of bypass for part of working medium between the outlet of the low pressure compressor by high pressure compressor, high pressure combustion chamber, high pressure turbine, and the input of the turbine stage of respective low pressure, directly or through low pressure combustion chamber, with free flow and free re-distribution of mass flow rate between both flows of working medium, output of the low pressure combustion chamber is connected to the input of the respective low pressure turbine stage, at that the bypass of part of working medium is possible in one direction only–from compressor to turbine.</p> |
