| 摘要 |
1291694 Gas turbine engines GENERAL ELECTRIC CO 13 Jan 1970 [29 Jan 1969] 1588/70 Headings F1G and FIT The turbine rotor of a gas turbine engine is cooled by a fluid, e.g. air from the engine compressor, which is delivered through a nozzle ring 36, Fig. 3, from a chamber 34 to a chamber 38 partly defined by the rotor. The fluid is accelerated through the nozzle ring so that it is thereby cooled, and is so directed by the ring as to move substantially axially relative to the rotor and thereby flow smoothly into holes 40 in turbine rotor disc 42. Thereafter it passes through passages 44 in blade roots 46, through passages (not shown) in the blades and is eventually discharged into the hot gas stream. Some of the fluid may continue through holes 40 to cool a second turbine stage. Labyrinth seals 79, 85 are provided. |
