Patent ID: 11859508
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 9:
10. A compressor for an aircraft turboshaft engine that longitudinally extends along an axis X and oriented from upstream to downstream, said compressor comprising:
a low pressure compressor located upstream of a high pressure compressor and an intermediate casing axially connecting the low pressure compressor and the high pressure compressor;
a primary vein in which a primary air flow accelerated by said compressor circulates from upstream to downstream;
said high pressure compressor comprising an inlet guide wheel comprising a retaining annulus internally delimiting the primary vein;
an external high pressure compressor casing externally delimiting said primary vein and a plurality of vanes extending into said primary vein between the retaining annulus and the external high pressure compressor casing;
the intermediate casing comprising an internal shell internally delimiting the primary vein and an external shell externally delimiting said primary vein and connected to the external high pressure compressor casing;
the intermediate casing comprising a plurality of support arms extending into the primary vein and connecting the internal shell and the external shell; and
a blocking device, said blocking device comprising:
a first member comprising a plurality of faces and being integral with the internal shell of the intermediate casing and located at a same angular position as at least one of the plurality of support arms with respect to the axis X; and
a second member having a base, the second member being integral with the retaining annulus and positioned to cooperate with the first member to block a tangential movement of the retaining annulus with respect to the intermediate casing along the axis X.