Losses in a diffuser 26 for a radial discharge compressor including an impeller 10 with impeller blades 16 terminating in radially outer discharge ends 18 are minimized by means of first and second stages of diffuser vanes 30 and 32, which vanes 30 and 32 have cross sectional shapes configured as supercritical airfoils.
To provide a jet engine booster structure capable of obtaining a desired pressure ratio with fewer stages. The moving blade of a booster is a boundary layer control tandem moving blade.
A tandem turbine-blade cascade for a turbine, turbo-engine or power engine includes at least two rows of blades disposed substantially directly in line with one another in the rotor or stator. The second row of blades has a larger number of blades than the first row of blades and the second row of blades are distributed nonuniformly. The spacing (s.sub.1) between two blades of the first row of blades is substantially equal to the sum (s.sub.2) of two successive blade spacings (s.sub.12, s.sub.22) in the second row of blades and the distribution quotient (s.sub.12 /s.sub.22) of the blade spacings in the second row is in the range between 0.4 and 1.0.
A collector for a vaned diffuser in a centrifugal compressor, wherein the radial cross-sectional area of the collector housing at the entrance to the collector outlet duct is 40% to 80% of the entrance area of the outlet duct and progresses smoothly to the outlet duct entrance area. Progression in collector housing cross-sectional area is produced by variation of the collector axial height. At the intersection with the outlet duct, the collector has a step in axial height so as to at least partially direct circumferential flow from the collector into the outlet duct entrance.
At least one embodiment of the present inventive technology focuses on a vaneless diffuser adapted for establishment extra-radially of a centrifugal fan, wherein the diffuser may effect an optimal transformation of velocity pressure into static pressure of a fluid (e.g., air) impelled by a centrifugal fan by decreasing that fluid's tangential velocity as it travels through the diffuser, without causing recirculation of air output from the diffuser back into the diffuser. Such diffuser may effect such a decrease in tangential velocity by radially extending the interface through which impelled air is output from the diffuser to a downflow fluid handling environment such as, e.g., a scroll and/or a plenum. The diffuser may converge in a direction parallel with the axis of rotation of the centrifugal fan to avoid fluid recirculation and/or may incorporate acoustical material so as to reduce the amount of material necessary for effective noise reduction as compared with convention noise reduction methods.
A diffuser (30) for a centrifugal compressor (60) having a flow slot (34) formed between the leading edge portion (36) of a diffuser vane (32) and an adjoining diffuser wall (70) for the passage of working fluid (67) over the vane from the pressure side ((40) to the suction side (42) of the vane. The portion (38) of the working fluid passing over the vane is injected into the flow boundary region (43), thereby minimizing the growth of a flow separation zone (58) along the suction side.
