|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/734; 417/244; 417/251; 417/300|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 3 인용 특허 : 11|
The invention relates to a method for the fuel supply of an aero gas turbine installed in an aircraft and to a fuel supply system. In order to avoid negative effects by out-gassed air in the fuel lines, the invention provides for an increased flow rate of the fuel in the fuel lines and for a fuel return line ( 6 ) for the return of excess fuel to the tank.
1. A fuel supply system for an aircraft equipped with at least one gas turbine engine and at least at least one fuel tank, comprising:a low pressure pump;a first fuel line connecting the fuel tank to the low-pressure pump from the fuel tank to the low-pressure pump;a high pressure pump;a second fuel line connecting the high-pressure pump to the low-pressure pump downstream of the low-pressure pump for supplying fuel from the low-pressure pump to the high-pressure pump;a fuel return line connected downstream of at least one of the low-pressure pump and th...