US 12,372,004 B2
Turbine blade for an aircraft turbomachine, provided with a channel for ejecting a primary flow towards an inter-lip cavity
Jean Charles Marie Coussirou, Moissy-Cramayel (FR); Thomas Langevin, Moissy-Cramayel (FR); and Benoit Guillaume Silet, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/256,317
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Dec. 1, 2021, PCT No. PCT/FR2021/052170
§ 371(c)(1), (2) Date Jun. 7, 2023,
PCT Pub. No. WO2022/123148, PCT Pub. Date Jun. 16, 2022.
Claims priority of application No. 2012975 (FR), filed on Dec. 10, 2020.
Prior Publication US 2024/0035391 A1, Feb. 1, 2024
Int. Cl. F01D 11/12 (2006.01); B33Y 80/00 (2015.01); F01D 5/14 (2006.01); F01D 11/00 (2006.01); F01D 11/04 (2006.01); F01D 11/10 (2006.01)
CPC F01D 11/122 (2013.01) [F01D 5/143 (2013.01); F01D 5/145 (2013.01); F01D 5/147 (2013.01); F01D 11/001 (2013.01); F01D 11/04 (2013.01); F01D 11/10 (2013.01); B33Y 80/00 (2014.12); F05D 2220/323 (2013.01); F05D 2240/80 (2013.01)] 8 Claims
OG exemplary drawing
 
1. An assembly for a turbine of a turbomachine extending around a longitudinal axis, comprising:
a blade;
a sealing element, said sealing element forming an abradable, the blade comprising a platform and an airfoil extending from the platform, the platform forming a first surface from which the airfoil extends and intended to delimit a primary duct wherein the airfoil extends in order to receive a fluid flowing in a direction going from a leading edge towards a trailing edge of the airfoil and going from an upstream part towards a downstream part of the platform, the sealing element being connected to the platform and forming a second surface intended to delimit an inter-lip cavity;
an internal channel passing through the platform and having a suction opening which opens onto the first surface of the upstream part of the platform and an ejection opening which opens onto the second surface, the blade including a root between the platform and the sealing element, and the internal channel including an angled portion passing through the platform, and a radially extending portion passing through the root and the sealing element; and
a rotor element carrying lips of a dynamic sealing joint, the inter-lip cavity extending longitudinally between two of said lips and radially between the abradable and the rotor element carrying the lips,
wherein the suction opening is positioned upstream of the leading edge of the airfoil relative to a direction of flow of the fluid in the primary duct.