US 11,859,508 B2
Aircraft turboshaft engine compressor comprising a device for immobilising a retaining annulus
Thomas Nolwenn Emmanuel Delahaye, Moissy-Cramayel (FR); Blaise Bergon, Moissy-Cramayel (FR); Laurent Jablonski, Moissy-Cramayel (FR); Lilian Yann Dumas, Moissy-Cramayel (FR); Thomas Etienne Camille Marie Van De Kerckhove, Moissy-Cramayel (FR); Noël Joseph Camille Robin, Moissy-Cramayel (FR); and Guillaume Sevi, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/628,523
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jul. 10, 2020, PCT No. PCT/EP2020/069474
§ 371(c)(1), (2) Date Jan. 19, 2022,
PCT Pub. No. WO2021/023470, PCT Pub. Date Feb. 11, 2021.
Claims priority of application No. 1908992 (FR), filed on Aug. 6, 2019.
Prior Publication US 2022/0251975 A1, Aug. 11, 2022
Int. Cl. F01D 25/24 (2006.01); F01D 9/04 (2006.01)
CPC F01D 25/246 (2013.01) [F01D 9/042 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01); F05D 2240/14 (2013.01); F05D 2260/30 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A compressor for an aircraft dual-flow turboshaft engine longitudinally extending along an axis X 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:
at least a first member 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
at least a second member integral with the retaining annulus, the at least one second member:
having a U-shape defining two side legs and a base, and a concavity of the U-shape being radially inwardly oriented, or
comprising at least one upstream protruding portion from the retaining annulus which is tangentially offset from the first member and configured to form a tangential stop,
so as to be configured to cooperate with the first member in order to block a tangential movement of the retaining annulus with respect to the intermediate casing along the axis X while allowing axial movement and radial movement of said retaining annulus with respect to said intermediate casing along the axis X.