SEALING ARRANGEMENT WITH PRESSURE-LOADED FEATHER SEALS TO SEAL GAP BETWEEN COMPONENTS OF GAS TURBINE ENGINE

摘要

A sealing arrangement (10) in a gas turbine engine to seal a gap between first and second turbine components (12, 14) is provided. The sealing arrangement includes a first arcuate feather seal (16) connected to an anchoring assembly (18) of the sealing arrangement affixed to the first turbine component. A second arcuate feather seal (20) is affixed to the second turbine component. The first feather seal and the second feather seal are responsive to a pressure differential that develops across the gap to form a pressure-loaded sealing joint between respective sealing surfaces (24, 26) of the first arcuate feather seal and the second arcuate feather seal. The sealing arrangement provides substantial design flexibility since it can reliably provide appropriate sealing functionality while enabling multiple degrees of freedom, such as to accommodate radial and/or axial displacements that can develop between the first turbine component and the second turbine component.