| 摘要 |
A gas turbine (1) engine has a segmented inner ring (30) providing root fixture points for a radial array of guide vanes (16). The axial hub has a series of compressor stages each with a circular array of rotating compressor blades associated with a commensurate ring of guide vanes. The fixed guide canes and rotating turbine ring are linked by a non-contact gas seal (31) of labyrinth form (28). |
