US 11,746,668 B2
Assembly of a turbomachine turbine ring and stator
Clément Jarrossay, Moissy-Cramayel (FR); Clément Emile André Cazin, Moissy-Cramayel (FR); Sébastien Serge Francis Congratel, Moissy-Cramayel (FR); Antoine Claude Michel Etienne Danis, Moissy-Cramayel (FR); and Aurélien Gaillard, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/913,917
Filed by Safran Aircraft Engines, Paris (FR)
PCT Filed Mar. 22, 2021, PCT No. PCT/FR2021/050465
§ 371(c)(1), (2) Date Sep. 23, 2022,
PCT Pub. No. WO2021/191534, PCT Pub. Date Sep. 30, 2021.
Claims priority of application No. 2002855 (FR), filed on Mar. 24, 2020.
Prior Publication US 2023/0118738 A1, Apr. 20, 2023
Int. Cl. F01D 11/08 (2006.01); F01D 11/00 (2006.01); F01D 25/24 (2006.01)
CPC F01D 11/005 (2013.01) [F01D 25/246 (2013.01); F05D 2260/201 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A turbomachine turbine assembly extending around an axis and comprising
a plurality of ring sectors forming a turbine ring;
a turbine ring support structure, each of said plurality of ring sectors having, in a section plane defined by an axial direction and a radial direction of said turbine ring, said axial direction corresponding to a flow direction of a gas flow in said turbomachine turbine assembly, a portion forming a base with, in the radial direction of said turbine ring, a radially inner face defining the inner face of said turbine ring and a radially outer face from which latching tabs project, said turbine ring support structure including a shroud from which radial flanges project, by which said latching tabs of each ring sector are retained;
a stator located, relative to said flow direction of the gas flow in said turbomachine turbine assembly, downstream of said turbine ring and mounted via a hook at a mounting zone in a recess of said turbine ring support structure, said stator including a vane provided with a radially outer platform, said outer platform extending axially facing said turbine ring;
an annular space being defined between said turbine ring, said turbine ring support structure and said outer platform, the annular space being traversed, during operation of said turbomachine turbine assembly, by a leakage air current originating in a space located radially outside said stator and which leaks while passing through said mounting zone,
wherein said turbomachine turbine assembly includes a hollow ring which occupies said annular space and which is formed to collect said leakage air current, to channel it and to expel it in a radially inner region of said annular space, between said turbine ring and the said outer platform.