Turbo-propeller engine

摘要

937,915. Gas turbine propeller engines. M.A.N.-TURBOMOTOREN G.m.b.H. Aug. 2, 1961 [Aug. 2, 1960], No. 28105/61. Class 110 (3). A gas turbine propeller engine comprises a compressor, one or more combustion chambers, a turbine driving the compressor and a separate power turbine which drives the propeller through reduction gearing, the output shaft or shafts of the gearing driving a hollow shaft which extends around the engine for at least part of the length thereof and is connected to the hub of the propeller, the hollow shaft being provided adjacent the propeller with inlet openings for air passing into the compressor. The reduction gearing is disposed in part at least between the compressor and turbines. The engine shown comprises a compressor 1 which is driven by means of a turbine 3 through a shaft 2, the air delivered by the compressor passing to a chamber 4 and thence by way of ducts 5, 51 to the combustion chamber 6. The combustion gases act first on the compressor driving turbine 3 and then on the separate power turbine 8, the gases then discharging through outlet 9. The power turbine 8 drives the hollow shaft 10, the pinion 11 of which meshes with three gears 12 which drive shafts 13. Pinions 14 on the shafts 13 engage with an internal ring gear on a sleeve 16 which is secured to a hollow shaft 15 mounted in a bearing 21, the shaft 15 extending over the engine compressor 1 for part of the length thereof. The shaft 15 is connected by means of struts 17 to the hub 18 of the propeller 19, the hub being mounted on a bearing 20. The annular space between the shaft 15 and hub 18 affords an air inlet to the compressor.