| 摘要 |
A method for controlling a rocket engine and a gas turbine engine is provided to improve driving force, and to increase internal pressure of plural exhaust ports artificially by exploding continuously with expanding and discharging gas alternately. A gas turbine is composed of two A and B combustion chambers formed in a circular body. The turbine is turned by discharging high pressure through an exhaust port with high pressure combustion in the A combustion chamber. The exhaust port of the A combustion chamber is closed and an exhaust port of the B combustion chamber is opened to turn the gas turbine by discharging high pressure exhaust gas in pressing a pressure pushing plate(2) with pressure of the B combustion chamber higher than pressure of the A combustion chamber. Combustion pressure is increased by opening and closing plural circular exhaust ports of plural combustion chambers. Fuel efficiency is improved by measuring pressure of each combustion chamber and opening and closing the exhaust ports automatically and alternately.
|
