Patent ID: 10550707

Abstract:
A seal system for a turbomachine, in particular a gas turbine, which includes a first component (10A, 10B), a second component (20), a flap (30) for sealing a gap between the first and second components, and a leaf spring, which includes a first leg (41) and a second leg (42), in a mounting state in which the flap and the second component do not contact each other, a projection of an abutment area (11) of the first component (10A, 10B), against which the first leg (41) is supported via the flap (30), is situated perpendicularly to a contact line (K) through at least two contact points of the first leg (41) with the flap (30), at least partially within a bearing surface (A) of the first component (10A, 10B), against which the second leg (42) of the pretensioned leaf spring is supported.