US 11,814,967 B2
Cooling device for a turbomachine casing
Ulysse Jacques Bernard Danteny, Moissy-Cramayel (FR); and Laurent Cédric Zamai, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/617,692
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jun. 11, 2020, PCT No. PCT/FR2020/050999
§ 371(c)(1), (2) Date Dec. 9, 2021,
PCT Pub. No. WO2020/249908, PCT Pub. Date Dec. 17, 2020.
Claims priority of application No. 1906225 (FR), filed on Jun. 12, 2019.
Prior Publication US 2022/0243605 A1, Aug. 4, 2022
Int. Cl. F01D 11/24 (2006.01); F01D 25/12 (2006.01); F01D 25/14 (2006.01); F02C 3/067 (2006.01); F02C 7/18 (2006.01)
CPC F01D 11/24 (2013.01) [F01D 25/12 (2013.01); F01D 25/14 (2013.01); F02C 3/067 (2013.01); F02C 7/18 (2013.01); F05D 2250/182 (2013.01); F05D 2250/44 (2013.01); F05D 2260/201 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A turbine for a turbomachine comprising a first rotor and a second rotor configured to pivot about an axis (X) in two opposite directions of rotation, the first rotor comprising a radially outer drum from which blades extend radially inwards, the turbine comprising cooling means attached with respect to the outer drum, said cooling means comprising a support plate comprising at least one first orifice, the cooling means further comprising at least one calibration plate attached to the support plate and located radially inside the support plate, the at least one calibration plate comprising at least one second calibration orifice turned towards the outer drum to allow passage of cooling air radially from the outside to the inside through the at least one first orifice and the at least one second orifice.