发明名称 |
Lean premix burner of a gas-turbine engine provided with a concentric annular central body |
摘要 |
This invention relates to a lean premix burner of a gas-turbine engine with an annular central body 2, which, while being essentially concentric to a burner center axis 1, is provided with an annular duct 4 connected to a supply line 3 and with a film applicator 5 which conically widens at the fuel exit side and into whose radially inward area at least one fuel exit opening 6 issues which is connected to the annular duct, characterized in that the film applicator 5 has, adjacently to and downstream of the fuel exit openings 6 in the area facing the fuel exit side 8, a step-like, annular protruding area 7 disposed radially to the burner center axis. |
申请公布号 |
US8943828(B2) |
申请公布日期 |
2015.02.03 |
申请号 |
US201113098610 |
申请日期 |
2011.05.02 |
申请人 |
Rolls-Royce Deutschland Ltd & Co KG |
发明人 |
Bagchi Imon-Kalyan;Lazik Waldemar |
分类号 |
F23R3/28;F23R3/14 |
主分类号 |
F23R3/28 |
代理机构 |
Shuttleworth & Ingersoll, PLC |
代理人 |
Klima Timothy J.;Shuttleworth & Ingersoll, PLC |
主权项 |
1. A lean premix burner of a gas-turbine engine comprising:
an annular central body being essentially concentric to a burner center axis and including an annular duct connected to a supply line, a film applicator conically widening toward a fuel exit side, and at least one fuel exit opening connected to the annular duct and issuing into a radially inward area of the film applicator, wherein the film applicator includes a step-like, annular protruding area adjacent to and downstream of the at least one fuel exit opening toward the fuel exit side, the protruding area protruding radially toward the burner center axis; wherein the protruding area is cone-shaped; wherein the protruding area has a cone angle which is equal to an angle of a conical area of the film applicator upstream of the at least one fuel exit opening; wherein an inflow area of the protruding area is rounded. |
地址 |
DE |