GB798689A - Improvements relating to bladed rotor constructions for fluid-flow machines - Google Patents

Abstract

798,689. Turbine and compressor-bladed rotors. ROLLS-ROYCE, Ltd. Feb. 10, 1956 [Feb. 10, 1955], No. 4067/55. Class 110 (3). In a machine such as an axial-flow turbine or compressor, fluid is passed through passages in the rotor blades for cooling or heating purposes. The assembly of blades 11 is provided at the blade tips with a circumferentiallyextending gas flow defining surface 15 which cooperates with stationary structure so as to provide a space 26 into which fluid under pressure is introduced, and the rotor blades are each formed with at least one longitudinallyextending passage 29 which communicates with the space, whereby fluid may pass at least radially inwardly through the blades and be discharged to a low pressure region. The invenengine in which the blades each comprise a root portion 12, a blade platform 14, a blade portion proper 11 and a shroud portion 15, the root portion 12 and platform 14 being connected by a stem 13. The blade is formed with three longitudinal bores 29, 30, 31 which communicate at their inner ends with a space formed between blades stems 13 of adjacent blades and sealing rings 32, 33. The shroud portions 15 are each formed with radial projections 23 which co-operate with an inward radial projection 22 on the stator ring 21 and the edges 24 of the shroud portions co-operate with surfaces 25 of the inlet nozzle guide vanes 19 so as to define an annular space 26 to which air under pressure is supplied either from the air space of the combustion equipment or directly from the air compressor of the engine. The air flows radially inwardly through the passage 29 and radially outwardly through the passages 30, 31 into the annular space 34, finally discharging into the gas stream flowing through the turbine. In place of separate shroud portions 15, an annular ring in one or more sections may be secured to the blade tips.