| 摘要 |
1,198,515. Turbine and compressor blading. W. DETTMERING. July 19, 1967 [July 21, 1966], No.33237/67. Heading F1T. A deceleration blade lattice for supersonic inflow, for the rotor or stator of a turbo machine, such as an axial-flow compressor or turbine, comprises two inter-digitated rows of blades. The supersonic inflow is retarded to subsonic in region A by a normal shock wave stabilized by throttling. Thereafter, the flow is deflected in region B which is of substantially constant crosssection, and passes through regions C and D of constant or slightly divergent cross-section to a deceleration region E of divergent cross-section. The flow-path may be slightly deflected in the reverse direction in region D, as shown, to substantially equalize, by centrifugal effects, the pressures at point 2 and the directions of flow of the part-flows issuing from regions C and D. The discharge flow may be purely axial as shown or may include a peripheral component. In the embodiment of Fig. 3 (not shown), the deflecting and deceleration regions are both arranged in the downstream blade row, the blades of the upstream row being very thin and substantially straight with their leading edges each defining an included angle of about 6 degrees or less. |
