GB904546A - Improvements in or relating to rotor blades of turbines and compressors - Google Patents

Abstract

904,546. Turbines and compressors. ROLLSROYCE Ltd. March 17, 1959 [March 17, 1958], No. 8561/58. Class 110 (3). A rotor blade of an axial flow compressor or turbine contains at least two independent internal flow paths, each comprising a plurality of passages running substantially the length of the blade, the passages of a path terminating in one of a pair of openings in or adjacent the surface of a blade root and being connected together at the opposite end of the blade. A cooling fluid, such as compressed air is fed through openings 37 in the rotor disc 10 to a circumferential slot 33. The air enters the blade through bores 22, 29. A vee-sectioned passage 20, adjacent the leading edge conducts the air to a recess 26 in the tip and passages 24 conduct the air back to the root. The trailing edge is similarly cooled through a passage 28 and a recess 31 communicating with passages 30. The recesses 26, 31 are covered by a blanking plate 27 which prevents communication between the two. The coolant passes through drillings 24a, 30a into spaces 25 and then to outlets 25a. Plates have circumferentially spaced dogs 19b which locate behind lugs 11a in the rotor disc. The dogs and lugs are so spaced that each disc can be offered up to the rotor with the dogs angularly between the lugs and can then be rotated to bring the dogs behind the lugs. The plates are fixed to the disc by set-screws 19c and when in position also hold the blade roots axially. Additional passages may be provided in the medial portion of the blade for passing coolant from the root to openings in the tip. The invention is also applicable to the heating of compressor blades.