| 摘要 |
1467499 Gas turbine combustion chamber GENERAL MOTORS CORP 12 Dec 1974 [4 Feb 1974] 53740/74 Heading F1L A combustion chamber for a gas turbine engine includes a liner 11 defining in sequence an upstream pre-chamber 27 in which liquid fuel is vaporized and mixed with air, a combustion zone 23, and a dilution zone 24, fuel being fed to the pre-chamber 27 through tangential slots 54 around its periphery from a manifold 46 encircling the pre-chamber and enclosed by a cooling air jacket 48, the liquid fuel forming a layer on the inner surface of the liner wall which is formed with intersecting helical grooves to facilitate vaporization. A heat shield 39 surrounds the cooling jacket. Air is fed to the prechamber via swirl blades 30 to vaporize and mix with the layer of liquid fuel. Further primary air is admitted to the pre-chamber via slots 60, and dilution air is fed to zone 24 via slots 70, both sets of slots being progressively covered or uncovered by valve sleeves 66, 71 respectively, to vary the ratio of primary air to secondary air. The sleeves may move together, as shown, or, Fig. 12, (not shown), slots 60 may be replaced by holes (122) not provided with adjustment means. The engine may be started with gaseous fuel or, as shown, by fuel sprayed through a nozzle 110 at the centre of the swirl vanes.
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