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US 11,952,950 B2Granted
Axial turbine engine, and rectifier stage with variable orientation vanes for an axial turbine engine
AssigneeSafran Aircraft Engines
InventorsLilian Yann Dumas, Baptiste René Roger Batonnet, Romain Nicolas Lagarde
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Abstract
An axial turbomachine comprising a compression device with a variable-orientation vane rectifier stage; a combustion chamber downstream of the compression device; a turbine device downstream of the combustion chamber; and a leak passage of air compressed by the compression device, between the compression device and the turbine device for cooling the turbine device; and where the rectifier stage is configured to modulate the section of the leak passage according to the orientation of the vanes of the stage.
Claims7
A turbomachine, said turbomachine comprising:
- a compression device with a rectifier stage with variable orientation vanes;
- a combustion chamber downstream of the compression device;
- a turbine device downstream of the combustion chamber;
- and
- a leak passage of air compressed by the compression device, between the compression device and the turbine device, in order to cool the turbine device;
- wherein the rectifier stage is configured to modulate a section of the leak passage according to an orientation of the vanes of the rectifier stage;
- and
- wherein the rectifier stage comprises an inner ring comprising an upstream edge facing a downstream edge of an annular duct on an intermediate casing of the turbomachine, with a clearance between the edges forming a leak passage with a non-modulating section in parallel with the leak passage with a modulating section formed by the rectifier stage.
5 more elements
Dependencies are inferred from the claim text.