US 12,372,007 B2
Stator vane comprising a heat pipe
Laurent Schweitzer, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/720,918
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Dec. 19, 2022, PCT No. PCT/FR2022/052426
§ 371(c)(1), (2) Date Jun. 17, 2024,
PCT Pub. No. WO2023/118720, PCT Pub. Date Jun. 29, 2023.
Claims priority of application No. 2114033 (FR), filed on Dec. 20, 2021.
Prior Publication US 2025/0059896 A1, Feb. 20, 2025
Int. Cl. F01D 25/12 (2006.01); F01D 9/02 (2006.01); F01D 9/04 (2006.01); F15B 21/04 (2019.01); F15B 21/0423 (2019.01); F15B 21/0427 (2019.01)
CPC F01D 25/12 (2013.01) [F01D 9/02 (2013.01); F01D 9/041 (2013.01); F15B 21/04 (2013.01); F15B 21/0423 (2019.01); F15B 21/0427 (2019.01); F05D 2240/12 (2013.01); F05D 2260/208 (2013.01)] 9 Claims
OG exemplary drawing
 
1. A turbomachine aerodynamic element including a body extending according to a radial main direction and a radial end located at a radial end of the body,
the aerodynamic element further including a heat exchanger between an internal fluid of the turbomachine and an airflow flowing around the body of the aerodynamic element,
wherein the heat exchanger includes a heat pipe in which a working fluid circulates and comprising an evaporation portion in which the working fluid exchanges heat with the internal fluid and a condensation portion in which the working fluid exchanges heat with the airflow,
wherein the condensation portion includes cooling tubes which are in fluid communication with the vapour pipe, which open into a recuperator and in which the working fluid circulates,
wherein each of said cooling tubes has a first end ensuring fluid communication with the vapour pipe and a second end ensuring fluid communication with the recuperator, and wherein the vapour pipe and the recuperator are axially separate chambers.