US 11,965,426 B2
Turbine for a turbine engine comprising heat-shielding foils
Franck Davy Boisnault, Moissy-Cramayel (FR); Florent Pierre Antoine Luneau, Moissy-Cramayel (FR); and Axel Sylvain Loïc Thomas, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/024,670
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Aug. 26, 2021, PCT No. PCT/FR2021/051489
§ 371(c)(1), (2) Date Mar. 3, 2023,
PCT Pub. No. WO2022/049338, PCT Pub. Date Mar. 10, 2022.
Claims priority of application No. 2009012 (FR), filed on Sep. 4, 2020.
Prior Publication US 2023/0250732 A1, Aug. 10, 2023
Int. Cl. F01D 9/04 (2006.01); F01D 11/00 (2006.01); F01D 25/08 (2006.01)
CPC F01D 25/08 (2013.01) [F01D 9/042 (2013.01); F01D 11/005 (2013.01); F05D 2260/30 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A turbine for a turbomachine,
the turbine having a main axis and comprising:
a casing comprising an annular hook,
a movably mounted wheel,
a ring extending facing the wheel along a radial direction of the main axis,
a nozzle including a blade provided with a platform,
the platform being extended radially outwards by a spoiler,
the spoiler being radially mounted on the hook of the casing,
foils each having a channel-like profiled shape along a direction circumferential to the main axis,
the foils extending successively along the circumferential direction,
each foil extending between the spoiler and the hook, and
stops to prevent a displacement of the foils along the circumferential direction,
wherein each foil comprises a protrusion extending circumferentially facing another protrusion of another circumferentially adjacent foil.