| 摘要 |
1284743 Gas turbine engine combustion equipment GENERAL ELECTRIC CO 14 April 1969 [17 April 1968] 19087/69 Heading F1L A gas turbine engine has, within the outer duct of a combustion region, a cylindrical liner defining a coolant passageway between the duct and the exterior of the liner, which liner has a plurality of circumferential corrugations with slots located at the radially inward peak of each corrugation to direct cooling air from the coolant passageway along the interior surface of the liner. As shown in Fig.2, the augmentor duct 42 of a turbo-fan engine is shielded from the hot augmentor gases by a liner 38 cooled by a portion of the engine bypass air which flows through a passageway 40 between the liner 38 and the duct 42. A mixer 36 of serpentine cross-sectional shape provides circumferentially spaced inlets alternately communicating with the cold by-pass air and the hot turbine exhaust gases so that the flow exiting from the mixer 36 has alternate regions of cold and hot gases to provide substantial mixing in a short axial distance. Circumferentially located about each radially inward corrugation peak 38a are a plurality of slots 44, Fig.4, a portion of the cooling air flowing through the passageway 40 being directed through the slots 44 to provide a cool boundary layer along the interior surface of the liner 38. The liner 38 is formed from a plurality of annular sections having the desired corrugated shape with corrugated strips 46 between the overlapping portions of the sections. Each strip 46 is a metal strip having its corrugations alternately attached to the exterior and interior surfaces of adjacant liner sections. The ratio of the pitch to the depth of the liner corrugations is in the range 40:1 to 10:1. A liner of this construction will resist buckling stresses caused by severe circumferential temperature gradients, is self-supporting and is sufficiently cooled on both its interior and exterior surfaces to eliminate failure due to overheating.
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