Combustion turbine power units

摘要

787,739. Gas turbine plants. NAPIER & SON, Ltd., D. March 23, 1956 [April 7, 1955], No. 10320/55. Class 110 (3). In a gas-turbine power plant, the compressor A supplies air under pressure to combustion equipment- B, the gases from which drive the turbine C which drives the compressor and may also supply external shaft power through shaft L1; alternatively a separate power turbine may be utilized. The power shaft L1 drives through reduction gearing contained in casing D. The power plant is supported by struts G, G1 connected to brackets G3 secured to the duct between the compressor A and combustion equipment B, and a torque transmitting coupling is provided comprising a part rigid with the reduction gear, casing D and a part which is rigidly connected to the airframe of an aircraft in which the power plant is installed. The invention is applicable in the case of a power plant driving a helicopter rotor, in which case the engine is mounted in a vertical position as shown, or a power plant driving an aircraft propeller. The supporting struts G, G1 are mounted at their lower ends on the helicopter airframe. The torque-transmitting coupling is shown in Fig. 5 and comprises a ring member J1 having dog teeth J2 which is connected to the upper end of the reduction gear casing D. Dog teeth J3 on a ring member J4 engage with the teeth J2, the ring J4 being mounted on the casing K of the helicopter rotor reduction gear which is itself mounted on the airframe. A sealing ring J5 is disposed between the ring member J1 and an outer casing J6. The coupling between the output shaft L2 of the reduction gearing (D) and the shaft K1 of the helicopter rotor reduction gearing (K) is shown at L3. The method of supporting the reduction gear casing D from the turbine casing C constitutes the subject-matter of Specification 787,738. Specification 761,442 also is referred to.