Bladed rotors for multistage axial flow compressors, turbines and like fluid flow machines

摘要

749,279. Turbine and compressor rotors. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Nov. 1 1954 [Dec. 5, 1953], No. 33898/53. Class 110(3) A bladed rotor for a multi-stage axial flow turbine or compressor comprises a number of rotor elements 1 each carrying a row of rotor blades 2, adjacent rotor elements being axially spaced apart by means of axially-extending tubular members 4 co-axial with the rotor elements and each (made up of packs of radially-extending plane' laminae. The rotor elements 1 in the Figure each comprises three sheet metal discs 1a, 1b, 1c spaced apart by washers 8. The roots 2a of the blades are slotted to engage the rotor discs 1a, 1b, 1c and they are retained by means of pins 3. The tubular members 4 comprise sheet metal rings which may be provided with lightening holes or the inner edges thereof may be scallopped. The rotor elements and the tubular spacers are held together by means of a number of through bolts 7. Frusto-conical bearer members with stub shafts 6 are also secured by means of the through bolts. Some of the spacer rings such as 4a may be of greater outside diameter than the others to provide a stop for the heads of the blade-retaining pins 3. Alternatively the pins may be fitted with split pins at the end opposite to the head, or the head dispensed with and split pins used at both ends. Specifications 724,123, 724,281, 738,656 and 740,757 are referred to