| 摘要 |
1,075,975. Gas turbine rotors. NATIONAL AEROSPACE LABORATORY OF THE SCIENCE & TECHNOLOGY AGENCY. Aug. 18, 1965 [Aug. 19, 1964]. No. 35438/65. Headings F1G and F1T. A gas turbine rotor disc 2 carries blades 3 having shanks 4. Plates 5, (6), Fig. 1A (not shown) on opposite sides of the disc 2 overlap the spaces between adjacent shanks 4 in such a manner that a cooling air entry 7 to each space is formed at the radially inner edge of each upstream plate 5 and an air outlet 8 at the radially outer edge of each downstream plate (6). An open ended box structure is mounted in each space, the interior of the box receiving cooling air through inlet 7. A cooling air stream 7' also flows to the space between the box walls and the shanks 4, this air leaving through a gap 8' between adjacent blade platforms 9. The shanks 4 may have fins (10), Fig. 2 (not shown), for additional cooling. Tongues (11, 12), Fig. 3 (not shown), are integral with, or welded to, the plates 5, (6) to prevent leakage of hot working gas into zones (16, 17) radially inwards of the guide vanes (13, 15). The tongues may, alternatively, be provided on the blade platforms 9. Deflecting rings (18, 19) assist in directing cooling air on to the rotor, which has concave portions (20, 21) and may be of titanium. |
