US 11,814,987 B2
Turbine engine comprising a straightening assembly
Cédric Zaccardi, Moissy-Cramayel (FR); Kaëlig Merwen Orieux, Moissy-Cramayel (FR); and William Henri Joseph Riera, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed on Oct. 23, 2018, as Appl. No. 16/167,951.
Claims priority of application No. 1759977 (FR), filed on Oct. 23, 2017.
Prior Publication US 2019/0120071 A1, Apr. 25, 2019
Int. Cl. F01D 9/04 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 9/042 (2013.01); F05D 2240/12 (2013.01); F05D 2250/15 (2013.01); F05D 2260/31 (2013.01); F05D 2300/603 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A dual-flow turbine engine (30) comprising a fan wheel (38) arranged at an upstream end of the turbine engine (30) and a straightening assembly (28) positioned axially downstream of the fan wheel (38), said assembly (28) comprising two radially inner and outer coaxial shells (32, 34) between which extend vanes (36) made of composite material, the radially inner shell (32) being arranged around a compressor and delimiting with the radially outer shell (34) an annular stream for the flow of a secondary air flow, the vanes (36) being fastened at a first end portion (44) on the radially inner shell (32) and at a second end portion (46) on the radially outer shell (34), the vanes (36) further comprising a useful part (48) extending between said first and second end portions (44, 46), characterized in that:
a) for each vane (36), in a plane perpendicular to the axis of the radially inner and outer shells (32, 34), a straight line (d) passing through a junction between said first and second end portions (44, 46) and the useful part (48) forms an angle α with a radius (R) of the radially inner shell (32) passing through the junction between said first end portion (44) and the useful part (46) of said vane (36) such that 0°<α≤30°,
b) the difference in radius between the inner (32) and outer (34) shells ranges from 200 to 900 mm;
wherein the radially inner shell (32) comprises, on its radially outer periphery, breaks (56) forming walls that extend radially between a radially outer surface of a first portion of the radially inner shell (32) and a radially inner surface of a second portion of the radially inner shell (32), a pressure surface of the first end portion (44) of the vanes (36) resting against and fastened to said breaks.