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Titanium alloys offer high specific strength and have long been used in the last stages of high pressure gas turbine engine compressors at temperatures up to about 450°C. Their application is limited to turbochargers of relatively low exhaust gas temperature. Since the specific stiffness is similar to that of IN713LC, the advantage of a titanium alloy would be the reduction in mass and inertia. The intermetallic titanium aluminide is currently receiving considerable attention. It has a specific strength similar to that of IN713LC, but the specific stiffness is much higher. It would therefore allow complex blade shapes to be formed in thin sections while retaining an adequate fatigue life. Compared with conventional metal alloys it is quite brittle as the low value of elongation to rupture shows. This material was originally developed for military applications, and many of the key properties remain uncertain and the details of manufacture are confidential. The available information suggests that in practice blades in this material have to be made slightly thicker than optimum for castability. Failures are easier to contain that those of metal alloys because the material tends to fragment into many small particles rather than a few large pieces, and so the weight of the turbine casing can be substantially reduced. CONCLUSIONS Turbocharger turbines can be effectively characterized by stage loading and flow coefficients. For a conventional radial inflow turbine with radial section blades, the maximum stage loading consistent with high efficiency is about 0.95. Higher stage loadings require forward swept blades, which require a mixed flow turbine geometry if radial sections are to be retained, The amount of forward sweep obtainable is limited by the blade lean angle, but in practice rotor inlet blade angles of 20–30° are feasible. By this means it is possible to increase the stage loading coefficient to about 1.15, or about 20% greater than that of a radial turbine. A design example shows that a high efficiency can be obtained at this level of loading, but a higher level of loading than this cannot be supported. An alternative route to high turbine power output is in developing better rotor materials. The intermetallic titanium aluminide shows promise but its durability in service has yet to be proved. REFERENCES CHEN H, BAINES N C 1994 The aerodynamic loading of radial and mixed flow turbines. Int Journ Mech Sci 36: 63-79. BAINES N C 1996 Flow development in radial turbine rotors. ASME Paper no. 96-GT-65. BAINES N C 1998 A meanline prediction method for radial turbine efficiency. In Turbochargers and Air management Systems, Inst Mech Engrs, pp. 45–56. TSUEI H H, OLIPHANT K N, JAPIKSE D 1998 The validation of rapid CFD modelling for turbomachinery. In CFD Technical Developments and Future Trends, Inst Mech Engrs. © Concepts ETI, Inc. 2002PDF Image | HIGH BOOST TURBOCHARGERS radial and mixed flow turbines
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