| 发明名称 |
CRYOGENIC FUEL SYSTEM AND METHOD FOR DELIERING FUEL IN AN AIRCRAFT |
| 摘要 |
A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine. |
| 申请公布号 |
US2015344144(A1) |
申请公布日期 |
2015.12.03 |
| 申请号 |
US201314654925 |
申请日期 |
2013.11.26 |
| 申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
KAMATH Deepak Manohar;BUCHHOLZ Todd James;BALADI Mehdi Milani;EPSTEIN Michael Jay |
| 分类号 |
B64D37/30 |
主分类号 |
B64D37/30 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, comprising:
a tank for storing cryogenic fuel; a supply line operably coupling the tank to the combustion chamber; and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump. |
| 地址 |
Schenectady NY US |
