燃气涡轮工程手册 Gas Turbine Engineering Handbook 2(24)

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Boyce.M.P.，Schiller，R.N.， andDesai，A.R.， ""Study of Casing TreatmentEffects in Axial-flowCompressors，"" ASME Paper No. 74-GT-...
Boyce， M.P.， ""Secondary Flows in Axial-flow Compressors with Treated Blades，""AGARD-CCP-214 pp. 5-1 to5-13， 1.74.
Carter，A.D.S.， ""The Low-Speed Performance of Related Aerofoils inCascade，""Rep.R.55， BritishNGTE，September， 1.4..
Giamati，C.C.， andFinger，H.B.， ""Design Velocity Distribution in MeridionalPlane，"" NASA SP36， Chapter VIII(1.65)， p. 255.
Graham， R.W. andGuentert，E.C.，""Compressor Stall and BladeVibration，""NASA SP36， (1.65) ChapterXI， p. 311.
Hatch...E.，Giamati，C.C.， and.ackson，R...， ""Application of Radial Equili-brium Condition to Axial-Flow Turbomachine Design Including Considera-tion of Change of Enthropy with Radius Downstream of BladeRow，"" NACA RM E54A20 (1.54).
Herrig，L...，Emery，..C.， andErwin，..R.， ""Systematic Two-Dimensional Cascade Tests of NACA 65 Series Compressor Blades at LowSpeed，"" NACA R.M. E 55Hll (1.55).
.18 Gas Turbine Engineering Handbook
Holmquist，L.O.， andRannie，W.D.， ""An Approximate Method of Calculating Three-Dimensional Flow in Axial Turbomachines"" (Paper) Meeting Inst.Aero.Sci.， New.ork， .anuary 24-2， 1.55.
Horlock，..H.， ""Axial FlowCompressors，"" Robert E. .rieger PublishingCompany， 1.73.
.oller，U.，Monig，R.，.osters，B.，Schreiber，H-A，1...， ""Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines. Part I: DesignandOptimization，"" ASME ..-GT-.5.
Lieblein，S.，Schwenk，F.C.， andBroderick，R.L.， ""Diffusion Factor for Estim-ating Losses and Limiting Blade Loading in Axial-Flow Compressor BladeElements，"" NACA RM .53001 (1.53).
Mellor，G.， ""The Aerodynamic Performance of Axial Compressor Cascades withApplication to MachineDesign，""(Sc. D.Thesis)， M.I.T. Gas TurbineLab，
M.I.T. Rep. No. 3 (1.57).
Stewart，W.L.，  ""Investigation of Compressible Flow Mixing Losses ObtainedDownstream of a BladeRow，"" NACA RM E54120 (1.54).
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Radial-Inflow Turbines

The radial-inflow turbine has been in use for many years. It first appeared as a practical power-producing unit in the hydraulic turbine field. Basically acentrifugal compressor with reversed flow and oppositerotation， the radial-inflowturbinewasthefirstusedinjetengineflightinthelate 1930s. Itwas considered the natural combination for a centrifugal compressor used in the same engine. Designers thought it easier to match the thrust from the two rotors and that the turbine would have a higher efficiency than the com-pressor for the same rotor because of the accelerating nature of the flow.
The performance of the radial-inflow turbine is now being investigated with more interest by the transportation and chemical industries: in trans-portation， this turbine is used in turbochargers for both spark ignition anddiesel engines; in aviation， the radial-inflow turbine is used as an expander inenvironmental control systems; and in the petrochemicalindustry， it is usedin expander designs， gas liquefaction expanders， and other cryogenic sys-tems. Radial-inflow turbines are also used in various small gas turbines to power helicopters and as standby generating units.
The radial-inflow turbine's greatest advantage is that the work produced by a single stage is equivalent to that of two or more stages in an axial turbine. This phenomenon occurs because a radial-inflow turbine usually has a higher tip speed than an axial turbine. Since the power output is a function ofthe square ofthe tip speed (PαU2) for a given flowrate， the work is greater than in a single-stage axial-flow turbine.
The radial-inflow turbine has another advantage: its cost is much lower than that of a single or multistage axial-flow turbine. The radial-inflow turbine has a lower turbine efficiency than the axial-flow turbine; how-ever， lower initial costs may be an incentive to choosing a radial-inflow turbine.
　
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