Gas turbine engine compressor

1,064,362. Compressor blades. ROLLS-ROYCE Ltd. Feb.8, 1965, No.5470/65. Heading F1T. The rotor or stator blades 22 of the compressor in an axial flow gas turbine engine are interconnected by radially spaced stiffening bridge pieces 24 electron beam welded to flanges (23), Fig.4 (not shown), on adjac...

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Bibliographische Detailangaben
1. Verfasser:	MORLEY FREDERICK WILLIAM WALTON
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Zusammenfassung:	1,064,362. Compressor blades. ROLLS-ROYCE Ltd. Feb.8, 1965, No.5470/65. Heading F1T. The rotor or stator blades 22 of the compressor in an axial flow gas turbine engine are interconnected by radially spaced stiffening bridge pieces 24 electron beam welded to flanges (23), Fig.4 (not shown), on adjacent blades to form a complete ring, or 90 degree sectors, of interconnected blades. The blades have an aspect ratio of 10: 1 or 11:1.