Rolls-royce Corporation

Anthony J Rae

Michael Stephen Krautheim

Jonathan F Carrotte

Alastair Duncan Walker

Richard Northall

Ian Mariah

Robert John Miller

Christopher R Hall

Kiran S Auchoybur

Michael S Krautheim

An annular array of turning vanesis provided in a ductof a gas turbine engine. The annular array of turning vanescomprises aerodynamic vanesand strut-vanes. The strut-vaneshave greater chord length and extend further axially downstream than the aerodynamic vanes. The leading edge of the strut-vanesis upstream of the trailing edge of the aerodynamic vanes. The strut-vanes provide flow turning. The arrangement allows the ductto be axially short.

Gas turbine engine vanes

An annular array of turning vanesis provided in a ductof a gas turbine engine. The annular array of turning vanescomprises aerodynamic vanesand strut-vanes. The strut-vaneshave greater chord length and extend further axially downstream than the aerodynamic vanes. The leading edge of the strut-vanesis upstream of the trailing edge of the aerodynamic vanes. The strut-vanes provide flow turning. The space to chord ratio of the aerodynamic vanes that are closest to the suction surface of a strut-vane is higher than the space to chord ratio of aerodynamic vanes that are closest to a pressure surface of the strut-vane. The arrangement allows the ductto be axially short.

A multistage compressor for a gas turbine engine is disclosed. The compressor includes a plurality of compressor stages, each stage including in axial flow series a row of rotor blades and a row of stator vanes; a hub to which a radially inner end of each rotor blade of the rows of rotor blades is connected; and a casing that circumscribes the rows of rotor blades and the rows of stator vanes. An aerofoil portion of each of the rotor blades and/or the stator vanes of one or more of the plurality of compressor stages is profiled in a spanwise direction such that the aerofoil portion has a trailing edge that is angled more towards an axial direction of the multistage compressor in regions of the aerofoil portion proximal to the casing and the hub than in a mid-region of the aerofoil portion.

Multistage compressor with aerofoil portion profiled in a spanwise direction

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Derby, United Kingdom

Anthony J Rae