发明名称 |
Gas turbine group with reheat combustor |
摘要 |
In a gas turbine group which consists essentially of a compressor (2), a first combustion chamber (3), a first turbine (4), a second combustion chamber (5) and a second turbine (6), the first combustion chamber (3) is configured as an annular combustion chamber. This annular combustion chamber (3) is operated by a number of premixing burners (11) which are distributed at the periphery. The first turbine (4) is designed in such a way that its exhaust gases have a temperature level which is above the self-ignition temperature of the fuel (13) used in the second combustion chamber (5). This second combustion chamber (5) consists of a burnerless, annular combustion space in which a number of vortex-generating elements (14) are integrated. The turbomachines, namely compressor (2), first turbine (4) and second turbine (6) are disposed on a rotor shaft (1), this rotor shaft (1) being supported in two bearings (9, 15).
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申请公布号 |
US5577378(A) |
申请公布日期 |
1996.11.26 |
申请号 |
US19950525040 |
申请日期 |
1995.09.08 |
申请人 |
ABB MANAGEMENT AG |
发明人 |
ALTHAUS, ROLF;FARKAS, FRANZ;GRAF, PETER;H+E,UML A+EE USERMANN, FREDY;KREIS, ERHARD |
分类号 |
F02C3/045;F02C3/14;F02C6/00;F02C6/02;F02C6/18;F23R3/28;F23R3/46;F23R3/58;(IPC1-7):F02C3/14 |
主分类号 |
F02C3/045 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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