| 摘要 |
The method is for the modification of a multi-stage compressor (101), whereby the rotor blades of the first rotor blade row (LA1) are exchanged for different rotor blades which have an identical blade profile (121) as the originals, and the blade angle of which differs from that (B'10) of the original. The blades of at least one other blade row (LAN,LEN) located downstream of the second compressor stage are exchanged for different blades which have an identical blade profile (125,126) as the originals, and a blade angle different from that (B'N0, B"N0) of the originals. Independent claims are included for the following: (A) a compressor modified by the aforesaid method; and (B) a gas turbine unit including the aforesaid compressor. |
