| 摘要 |
1,138,547. Gas turbine engine combustion chambers. GENERAL ELECTRIC CO. Aug. 23, 1966 [Jan. 19, 1966], No. 37705/66. Heading F1L. A gas turbine engine flame tube or other structure to be cooled has a wall formed by axially and radially spaced rings 10, 12 connected by a ring member 20 having an upstream extending leg 22 welded to the ring 10 and downstream extending radially spaced legs 24, 26, leg 26 being welded to ring 12. Apertures 28 in leg 26 allow cooling air 14 to enter the annular chamber 30 between legs 24, 26 and thence effect film cooling of ring 12. Axially extending slits (34), Fig. 3 (not shown), may be provided in leg 24 to reduce thermal stresses. In a modification, Fig. 5 (not shown), rings 10, 12 and connecting ring 20 are frustoconical. |
