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INTRODUCTION There is a continuing upward trend in boost pressure in order to achieve higher BMEP and reduce emissions levels. The boost pressure that can be achieved in a simple turbocharger is usually considered to be limited by the compressor, but it may also be limited by the turbine. A single stage centrifugal compressor is capable of working efficiently at high pressure ratios, but this is usually only achieved at the expense of range. For applications where a wide range is not required, the limiting factor may then be the ability of the turbine to provide sufficient power to drive the compressor while maintaining an adequate service life and competitive manufacturing cost. Where high compressor pressure ratio and wide range are required simultaneously, the common solution is the series, or two stage, turbocharger. Most often this is implemented by coupling two single stage turbochargers. This has the advantage of requiring no new components, but the installation volume can be significant, as can the parasitic pressure losses in the ducting between the turbochargers. In a few limited cases integrated two stage turbochargers have been developed, but these have not completely overcome the problems of two, single stage machines. An alternative solution where high boost pressure is required together with wide range is a two stage compressor driven by a single stage turbine. This can be made considerably more compact than a series turbocharger arrangement. The limitation that the two compressor stages must rotate at the same speed is not as serious as is sometimes supposed. Any turbocharger is optimally matched to an engine at one condition only and a series turbocharger is only slightly better than a single turbocharger at other conditions. The solution to the matching problem that is increasingly being adopted today is variable turbine geometry. Optimal operation of a series turbocharger requires that both turbines be variable geometry, which is considerably more expensive than any turbocharging scheme that uses only a single turbine. The power required to drive the compression system increases with boost pressure. When high boost pressure is used, the focus of attention falls on the power that the turbine can effectively deliver. In this paper we examine the limits of conventional radial inflow turbines and show how these limits can readily be predicted. Where higher output power is necessary, modifications to the conventional turbine geometry can extend the maximum power and delay the point at which a two stage turbine is required. POWER REQUIREMENTS The performance of a radial-inflow turbine can simply be described in terms of two nondimensional parameters: the stage loading coefficient ψ = ∆h0/U2 and the flow coefficient φ = Cm/U. Chen and Baines (1) showed that these parameters could be used to correlate the turbine efficiency very effectively. Figure 1 shows the measured efficiencies of a large number of radial turbines of various sizes and configurations, Clearly the maximum efficiency is obtained for stage loading coefficients in the range 0.9–1.0 and flow coefficients between about 0.2 and 0.3. These data establish a link between the specific work output of the turbine ∆h0 and the rotor blade tip speed U. By making some simple assumptions about the stage loading coefficient,PDF Image | HIGH BOOST TURBOCHARGERS radial and mixed flow turbines
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