a supersonic aircraft has a fuselage with wings (20), (22) and (24), a stabilizer bar (34 to 38), duck (30 and 32) and a pair of turbine engine (44)46 / 70) on the body (20).each engine (44, 46, 70) is of relatively simple design, with a fixed head.a compressor (80, 82) and a turbine (84) with a single driving shaft (76) between the impeller (84) and the compressor (80).the engine (44, 46, 70) may use a gas ejection tuyere geometry of fixed or variable (75) as a function of the presence or absence of the post combustion.the motor (70) is designed to provide maximum rated thrust for a given position through the control of gas flow when the aircraft is propelled by the engine (70) has a number ofsupersonic cruise mach in e pre-set.it has a maximum allowable speeds below pre-set cruise mach number in the air was obtained without new variable geometry in the flow of air in the correct word(70) has a substantially constant value by correcting the air flow predeterminee in supersonic cruise mach number.the flow of air to correct engine (70) is kept at a constant value by controlling a parameter of operation of the engine with the air flow by adjusting the flow of correct and combustibl(e) of the motor (70) to reduce the speed of the compressor (80) real) and the turbine (84).
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