assembly and kühlanordnung for läuferscheiben ordered laufschaufeln of turbomachinery, preferably gas turbines

摘要

1,209,419. Turbine rotor blade fixing. WESTINGHOUSE ELECTRIC CORP. May 27, 1969 [June 24, 1968], No.26738/69. Heading F1T. The roots 5 of gas turbine blades 6 are locked in position in axial slots 4 in the rotor periphery 3 by upstream and downstream side plates 10, 11 engaging in respective circumferential slots 16, 17 in blade platforms 7 and in corresponding slots 14, 15 in the rotor periphery 3. Adjacent plates 10 or 11 have inter-fitting lips 20, 21 to prevent cooling air leakage and also have tabs 22 engaging deeper portions 18 of slots 16, 17 to prevent circumferential movement of the plates 10, 11 from their assembled position. Prior to assembly of plates 10, 11 and their associated blades 6 on the rotor, a first blade 6 is mounted on the rotor and locked in position by special locking plates 30. Fig. 3, at the upstream and downstream sides of its root 5. The plates 30 do not have tabs 22 and are chamfered at 31 to permit assembly of the plates in slots 14 to 17 in the manner shown dotted, rather than by the circumferential sliding necessary for plates 10, 11. The plates 30 are locked in position by screws 34, 35 having tab washers 40 and then the remaining blades 6 and plates 10, 11 are assembled one by one on the rotor. The last locking plates inserted comprise a further set of special plates 30 adjacent the plates 30 first inserted. The plates 10 have holes 54 through which cooling air enters an annular chamber 39A to flow through gaps 50 to 53 between the blade roots 5 and the mounting slots 4, thence into an annular chamber 39 before exhausting through holes 55 in plates 11. Similar holes 56 are also provided in plates 30. (For Figure see next page)