FIELD: turbomachine sealing systems.
SUBSTANCE: invention relates to sealing in a turbomachine. A sealing system is described for sealing the gap (G1, G2) in the turbomachine (1) between the first structural element (21; 23) and the second structural element (31). The sealing system includes a sealing device containing a sealing element (47, 77) having a first edge section (49; 79) and a second edge section (51; 81). The two edge sections are parallel to each other, and the first edge section (49; 79) forms a rotary connection with the first structural element (21; 23). The first structural element (21; 23) additionally contains a seat (55; 85), in which the first edge section (49; 79) of the sealing element (47; 77) is placed with the possibility of rotation. The second edge section (51; 81) contains a curved contact surface (51.1, 81.1), which is in sealing contact with the contact surface (67; 97) of the second structural element (31). The present document also describes a gas turbine engine (1) with a heat pipe (31) and a sealing structure for sealing the gap (G1; G2) between the heat pipe (31) and the turbine nozzles of the first stage of the turbine.
EFFECT: invention provides an increase in the sealing efficiency and an increase in the service life.
14 cl, 5 dwg
