|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/204 ; 60/243 ; 244/46|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 21 인용 특허 : 0|
A supersonic airplane has a fuselage, a wing, a vertical stabilizer, a canard and a pair of turbine engines mounted in the fuselage. Each engine is of relatively simple design with a fixed inlet, a compressor and a turbine with a single drive shaft interconnecting the turbine and compressor. The engine can employ either fixed or variable exhaust nozzle geometry, depending on whether an afterburner is installed. The engine is point designed to provide maximum design thrust at a given intermediate throttle setting when the airplane is being propelled by th...
In a turbine engine designed to provide a predetermined amount of thrust at a given throttle setting when propelling an airplane at a predetermined supersonic Mach number, the improvement comprising: control means for maintaining the corrected airflow in said engine substantially at a constant value at flight Mach numbers below said predetermined supersonic Mach number.