Turbomachine sealing system and turbomachine including the sealing system

Abstract

A sealing system is described for effecting a seal of a gap (G1; G2) in a turbomachine (1) between a first structural member (21; 23) and a second structural member (31). The sealing system includes a sealing apparatus comprising a sealing member (47; 77) comprising a first edge portion (49; 79) and a second edge portion (51; 81). The two edge portions are parallel to one another and the first edge portion (49; 79) forms a pivoting connection to the first structural member (21; 23). The first structural member (21; 23) further comprises a seat (55; 85) rotatably housing the first edge portion (49; 79) of the sealing member (47; 77). The second edge portion (51; 81) comprises a curved contact surface (51.1; 81.1), in sealing contact with a contact surface (67; 97) of the second structural member (31). Further disclosed herein is a gas turbine engine (1) with a combustor liner (31) and a sealing arrangement to seal a gap (G1; G2) between the combustor liner (31) and the turbine nozzles of the first turbine stage.

Dependencies are inferred from the claim text.