US 11,698,003 B2
Cooling device for a turbine of a turbomachine
Baptiste Marie Aubin Pierre Jouy, Moissy-Cramayel (FR); Nicolas Contini, Moissy-Cramayel (FR); Arnaud Doublier, Moissy-Cramayel (FR); Vincent Dubois Dorogi, Moissy-Cramayel (FR); and Sébastien Jean Laurent Prestel, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 16/347,538
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Oct. 27, 2017, PCT No. PCT/FR2017/052964
§ 371(c)(1), (2) Date May 3, 2019,
PCT Pub. No. WO2018/083403, PCT Pub. Date May 11, 2018.
Claims priority of application No. 1660708 (FR), filed on Nov. 4, 2016.
Prior Publication US 2021/0293179 A1, Sep. 23, 2021
Int. Cl. F01D 25/14 (2006.01); F01D 11/24 (2006.01)
CPC F01D 25/14 (2013.01) [F01D 11/24 (2013.01); F05D 2220/36 (2013.01); F05D 2260/201 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A cooling device (11) for a turbine of a turbomachine extending along an axis, comprising at least one radially inner metal sheet (14) and one radially outer metal sheet (15) that are joined to one another and delimit, between them, cooling air circulation channels (17) extending circumferentially from a connection region (16), each channel of the cooling air circulation channels (17) comprising at least one air inlet and air ejection orifices (19), that are designed to be oriented toward a region to be cooled, characterized in that
the cooling device comprises means for cooling the at least one radially inner metal sheet and the at least one radially outer metal sheet comprising at least one cooling duct (21) intended for the circulation of cooling air,
the at least one cooling duct (21) being located radially outside the at least one radially inner metal sheet and the at least one radially outer metal sheet and adjacent to or in contact with the at least one radially inner metal sheet and the at least one radially outer metal sheet so as to cool the at least one radially inner metal sheet and the at least one radially outer metal sheet,
the at least one cooling duct (21) extending axially and arranged at a distance away from the at least one air inlet and towards circumferential end regions of the cooling air circulation channels (17),
characterized in that each cooling duct (21) of the at least one cooling duct comprises at least one series of cooling air ejection orifices (22) oriented toward the at least one radially inner metal sheet and the at least one radially outer metal sheet.