| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide an aerodynamic flame stabilizer with a minimal pressure drop in a gas turbine engine. <P>SOLUTION: The flame stabilizer (40) is in a fluid communication state with a combustor (18) of the gas turbine engine (10). The flame stabilizer (40) has a body (42), including an aerodynamic shape forming a flow recirculation zone (44) by injecting a fluid (48) through a plurality of holes (46) in the body of the flame stabilizer. The aerodynamic shape reduces the pressure loss in the combustor particularly, when absolutely no fuel is being supplied to the combustor (18). In addition, the size of the flow recirculation zone (44) can be adjusted, by selectively adjusting a flow rate of the fluid (48) passing through the holes (46), or by selectively adjusting size of the holes (46). <P>COPYRIGHT: (C)2011,JPO&INPIT</p> |
