| 摘要 |
In a gas turbine, a supplemental seal (60) is provided between an annular axially facing sealing surface (54) of a nozzle support ring (44) and an annular axially opposed sealing surface (50) formed by circumferentially adjacent nozzle segments. Each segment carries an inner rail (52) mounting a chordal hinge seal which engages the sealing surface of the nozzle support ring. That seal is supplemented by a generally arcuate V-shaped seal (60) between the sealing surfaces which opens radially inwardly toward a high pressure leakage path past the chordal hinge seal. The supplemental seal is initially compressed and maintained in a compressed condition during installation by application of a solder. At operating temperature, the solder melts away, releasing the supplemental seal to seal between the nozzle support ring and nozzle segments. <IMAGE> |
