TURBOMACHINE WITH SHROUD DEVICE Russian patent published in 2019 - IPC F01D11/12 

FIELD: machine building.

SUBSTANCE: invention relates to power engineering and can be used in axial turbochargers for gas turbine engines and installations. Turbomachine with a shroud device includes a housing with a flow path, an impeller with blades installed in the flow path between the cavities of high and low pressure with the formation of interscapular flow channels, and an annular shell of a shroud device placed in the path wall of the housing with the formation of an annular cavity communicated with the inter-blade flow channels, and having annular grooves located on the inner cylindrical surface of the shell, in which the outer part is fitted with sealing rings made of a material with a hardness lower than that of the material of the impeller blades, and placed in the annular cavity in such a way that the diameter of their inner surface is equal to the diameter of the flow path, each sealing ring is made in the form of a set of sector elements located obliquely to the longitudinal axis of the turbomachine, which are interconnected by locking parts with docking platforms and end surfaces. Each annular groove of the shell is provided with through slots in the number of sector elements of the sealing ring, each set of sector elements is equipped with an installation biscuit, located between the connecting end surfaces of two adjacent sector elements and rigidly connected therewith, and each sector element is provided with at least one protrusion located on the outer surface of the locking part, placed in the through slot of the annular groove and rigidly connected with the shell, and the connecting sites and the end surfaces of the locking parts of each sector element are rigidly connected, respectively, with the docking sites and the end surfaces of the adjacent sector elements.

EFFECT: technical result of the invention is to reduce the flow of working medium from the cavity of high pressure into the cavity of low pressure by minimizing the radial clearance between the end surface of the blades and the inner surface of the sealing rings.

4 cl, 5 dwg