GB985702A - Gas turbine engine - Google Patents

Abstract

985,702. Gas turbine plant. BENDIX CORPORATION. April 28, 1961 [May 2, 1960], No. 15395/61. Headings FIG and F1T. A gas turbine engine comprising a compressor supplying combustion air to a combustion chamber feeding a turbine driving the compressor and a separate power turbine has means responsive to the speed of the power turbine for controlling means for varying the direction of gas flow to the power turbine blades. A gas turbine, Fig. 3, comprises a compressor 16 supplying combustion air to a combustion chamber 18 feeding a turbine 20 driving the compressor and a separate power turbine 24 which drives through a clutch 26 and transmission gearing 28, 30, 32, 34 a load shaft 36. Air enters the engine through a filter 38 and is discharged by the compressor through movable throttle vanes 44 into the combustion chamber 18. A governor 53 driven by the compressor-turbine shaft controls the fuel supply to the combustion chamber. The combustion products are discharged through an annular duct 56, plate member 57, throttle 58 and stator 60 to drive the turbine 20. The plate member 57, throttle 58 and stator 60, Fig. 4, are formed with arcuate slots 82, 84, 86. Rotation of the throttle 58 varies the registration of openings 84 with openings 82, 86 and so varies the area of flow to the compressor turbine 20. The throttle vanes 44, governor 53 and throttle 58 are manually controlled by a lever 68. The stator 62 of the power turbine 24 has a number of pivotally mounted guide vanes 90 which are connected by levers 92 and links for simultaneous rotation by a governor 96 driven by the power turbine 24. The arrangement is such that the angle of incidence of the gas flow on the rotor vanes increases with increase of power turbine speed. In another modification, Fig. 16 the stator blades are formed in two parts 154, 168 and 178, 184 one of which 168,184 is rotatable with respect to the other to vary the flow area and angle of incidence. To reduce the leakage around the compressorturbine blades, a ring 130, Fig. 12 is welded to the casing 134. To prevent distortion of this ring due to differential heating the result of the partial admission of the working fluid, the ring is split at 136 in the regions where the working fluid is not admitted. Specification 888,104 is referred to.