Some Preliminary Results for Conical Diffusers with high Subsonic entry mach Numbers

Abstract

Some preliminary results are presented for the variation of total pressure loss coefficient with entry Mach number for conical diffusers. Included angles of 5, 8 and 12°, area ratios from 2 to 16 and entry lengths from 0 to 65 diameters are considered. In these initial tests the junction between the parallel entry pipe and the cone is sharp.

The variation of Mach number and total pressure loss in the entry pipe is predicted simply using measured friction factors and typical velocity profiles. These calculations give the entry conditions to the diffusers in the absence of the diffusers. The effect of the junction of entry pipe and diffuser on the entry pipe flow is thus correctly attributed to the diffuser in the assessment of its total pressure loss. In addition a correctly specified mean entry Mach number is obtained. These considerations enable the losses in diffuser-pipe conjunctions of high Mach number to be logically analysed from separate pipe flow and diffuser data.

The results obtained are unusual and indicate that previous assessments of diffuser performance at high Mach numbers have been confused by incorrect consideration of the effect of the diffuser entry pipe conjunction and incorrect specification of the effective mean entry Mach number. It is concluded that further experimental results are needed for developing compressible flows in constant area ducts in order that the present preliminary results may be made more precise. The momentum equation analysis in terms of suitable mean values is presented briefly.

Previous diffuser results for low subsonic entry Mach numbers are considered briefly in comparison. Serious errors are shown to be present in these early results. Typically the errors originate in the definition of loss coefficient and static pressure efficiency and the use of the mass derived mean concept. In some cases the quoted static pressure efficiencies imply a decrease in entropy for the diffuser flow at low area ratios.

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References

Ward-Smith

A. J.

‘Subsonic adiabatic flow in a duct of constant cross-sectional area’, Jl R. aeronaut. Soc. 1964 (February).

Livesey

J. L.

Hugh

‘ “Suitable mean values” in one-dimensional gas dynamics’, Jl mech. Engng Sci. 1966 8 (No. 4), 374.

Cockrell

D. J.

Markland

‘A review of incompressible diffuser flow’, Aircraft Engng 1963 (October).

‘Measurements of the pressure recovery characteristics of a number of circular diffusers’, Rolls-Royce Experimental Department Report, reference Chr/W.J.A. 1/BH, 14th January 1949.