| 摘要 |
A turbogas system multistage compressor (1) extends along a longitudinal axis (A), and has an inlet (4), and an outlet diffuser (5), between which are located in succession a first stage (10), a number of intermediate stages (11), and a final stage (12); the final stage (12) has an array of fixed blades (15a) on which an airflow impinges; and the fixed blades are substantially equally spaced about the axis (A) of the compressor (1), and are designed to produce a deflection, substantially ranging between approximately 15° and 30°, of the airflow impinging on the fixed blades (15a). |
