Stator vane comprising a heat pipe
AssigneeSafran Aircraft Engines
InventorLaurent Schweitzer
Life of this patent
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Abstract
An aerodynamic element of a turbomachine 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 includes a heat exchanger between an internal fluid of the turbomachine and an airflow flowing around the body of the aerodynamic element. The heat exchanger includes a heat pipe in which a working fluid circulates and as well as 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.
Claims9
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.
Dependencies are inferred from the claim text.