Patent ID: 11952950
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. 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.