Turbine-propeller power units for aircraft
864,540. Aircraft power plants. NAPIER & SON Ltd., D. Dec. 4, 1958 [Dec. 12, 1957], No. 38687/57. Class 4. [Also in Group XXVI] In a turbine-propeller power unit for aircraft a reduction gearing casing carrying various engine driven auxiliaries is constructed as a unit 17 separate from the engin...
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Zusammenfassung: | 864,540. Aircraft power plants. NAPIER & SON Ltd., D. Dec. 4, 1958 [Dec. 12, 1957], No. 38687/57. Class 4. [Also in Group XXVI] In a turbine-propeller power unit for aircraft a reduction gearing casing carrying various engine driven auxiliaries is constructed as a unit 17 separate from the engine 10 and is provided with means for mounting it in an aircraft independently of the engine. The power unit comprises an engine 10 having an air intake 11, an axial flow compressor 12, combustion chambers 13, a turbine casing 14, and a built-in reduction gearing unit 57. The separate reduction gearing unit 17, Fig. 3, is mounted in front of, and connected by shaft 15 to, the power unit and has an input shaft 18 which drives the output shaft 25 through spur gears 23, 24. Auxiliary equipment requiring a high speed drive such as a cabin air blower 27 and an electric generator 28 are driven from the spur gear 24 which also has internal teeth meshing with gear wheels such as 32 on the shafts of the above equipment. Auxiliary equipment requiring a lower speed drive such as the propeller pitch control governor 29 and the hydraulic pump 30 are driven from the input shaft 18 through gears meshing with a gear wheel 36 on this shaft. The power unit is suspended beneath a wing 38 of the aircraft with the air intake 11 in approximate vertical alignment with an air intake 55 in the leading edge of the wing. The engine 10 is mounted in a ring frame 39 from which the engine 10 is supported by a triangulated frame of struts 43, 44, 45, and from which the separate reduction gear unit 17 is separated supported by similar struts 49, 50, 51. |
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