Turbomachine, in particular a gas turbine, with a sealing...

Details Turbomachine, in particular a gas turbine, with a sealing... Turbomachine, in particular a gas turbine, with a sealing...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 11/00 (2006.01)

Patent

CA 2372740

The invention relates to a turbo engine (1), especially a gas turbine, with a rotor (25) that extends along an axis of rotation (15). Said rotor (25) comprises a peripheral surface (31) that is defined by the outer radial delimiting surface of the rotor (25) and a receiving structure (33) and a first rotor blade (13A) and a second rotor blade (13B) which have each a blade root (43A, 43B) and a blade platform (17A, 17B). The blade platform (17A) of the first rotor blade (13A) and the blade platform (17B) of the second rotor blade (13B) adjoin. The blade platforms (17A, 17B) and the peripheral surface (31) define between them an intermediate space (49). A sealing system (51) is provided on the peripheral surface (31) in the intermediate space (49), said sealing system being of the labyrinth box type.

L'invention concerne une turbomachine (1), notamment une turbine à gaz, comprenant un rotor (25) s'étendant le long d'un axe de rotation (15). Ce rotor (25) présente une surface périphérique (31) définie par la surface de délimitation radiale extérieure du rotor (25), et une structure de logement (33) ainsi qu'une première aube mobile (13A) et une deuxième aube mobile (13B) qui présentent chacune une emplanture (43A, 43b) et une plate-forme (17A, 17B). La plate-forme (17A) de la première aube mobile (13A) et la plate-forme (17B) de la deuxième aube mobile (13B) sont adjacentes, et une zone intermédiaire (49) est formée entre les plates-formes (17A, 17B) et la surface périphérique (31). Un système d'étanchéité en labyrinthe (51) est situé dans la zone intermédiaire (49) sur cette surface périphérique (31).

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