| 摘要 |
1298643 Turbomachine blade shrouding GENERAL MOTORS CORP 19 April 1971 [6 May 1970] 22063/71 Heading FIT In a gas turbine engine the stationary shroud surrounding the tips of turbine rotor blades comprises a ring 23 supporting via flanges 43,44 a laminated porous sheet 34, the pores 75 of which communicate with a preponderant number of the cells of a honeycomb facing 32 secured to the sheet. The latter is formed from three slightly spaced layers 38,39,40 the pores 75 of which are out of alignment so that cooling air supplied to the chamber defined between layer 40 and a ring 42 follows a tortuous path in flowing through sheet 34 to honeycomb 32. The forward end of the chamber is defined by a laminated flange 64 also having cooling passages. Sheet 34 and associated ring 42 and honeycomb 32 are formed as 90‹ arcuate segments the adjacent ends of which are skewed at 36, Fig.7 (not shown). To prevent leakage of cooling air channel section blocks (76) Figs.8, 9 (not shown) are welded between layer 40 and ring 42 at the ends of each segment. Support ring 23 is made in two 180‹ halves and is itself supported by a mounting ring 20 bolted to the turbine casing. Circumferential movement of ring 23 is prevented by dowels 26 engaging slots 27 in the ring. The cooling air is supplied from the engine compressor via passages (56, 57, 59, 60) Figs. 1, 2, 5 (not shown) in the respective rings, baffles (63) being secured over the passages (60) in ring 42 to prevent direct impingement of the coolant on layer 40.
|
