GB832360A - Improvements relating to fluid flow transforming devices - Google Patents

Abstract

832,360. Axial-flow compressors and turbines; gas - turbine jet - propulsion plant. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Aug. 15, 1957 [Oct. 15, 1956], No. 31271/56. Classes 110 (1) and 110 (3). One end of a fluid-flow ducting is arranged as a row of separate adjacent passages for fluidflows, alternate passages of the row at the one end being brought together at the opposite end of the ducting as a row of separate adjacent passages, and the passages interleaving the alternate passages at the one end being brought together at the opposite end as another row of separate adjacent passages. Annular ducting for introducing two flows into an axial-flow compressor stage is shown in developed form in Figs. 1 and 2 and comprises inner and outer annular walls 17, 18 (not shown in Fig. 1), and an intermediate annular wall 10 which separates the two flows. The outer flow passage is divided by radial walls 11 into a peripheral series of passages 12, and the inner flow passage is divided by radial walls 13 into a peripheral series of passages 14. The walls 13 are peripherally staggered in relation to the walls 11, as shown in Fig. 2. The walls 11 and 13 intersect outer and inner walls 15 and 16 respectively, the walls 15 and 16 sloping and tapering as shown to meet the wall 10. The walls 11 and 13 may be faired into the walls 15 and 16. Adjacent walls 15 and 16 are connected by walls 19 which have radial outlet edges and circumferentially-extending inlet edges which merge into the outlet edge of the wall 10. The ducting may vary in radial height and in distance from the axis and may be helically twisted to accommodate whirl components of motion in either flow, and the separating walls may be non-radial. The flow areas of the two passages may differ and may vary from inlet to outlet. Where the ducting is used to introduce a second flow into an intermediate stage, the flow which has already passed through the earlier stages can have its whirl component removed by blading before entering the passages 14, the additional flow being introduced to the passages 12 through a coaxial annular duct. The ducting may be used for dividing a flow into two partial flows, and in this case is traversed in the opposite direction to that shown by the arrow in Fig. 1. It may be used in this way to divide the flow leaving an axial-flow turbine stage or for separating the air compressed by the intake fan of a by-pass jet propulsion engine into two streams, one passing into a by-pass duct and the other passing to the main compressor, combustion system and turbines.