Page 62 - Fluid Mechanics and Thermodynamics of Turbomachinery
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Basic Thermodynamics, Fluid Mechanics: Definitions of Efficiency  43
                          theoretical kinetic energy per unit mass obtained by an isentropic expansion to the
                          same back pressure, i.e.
                                    1 2  1 2
                                N D . c //. c / D .h 01  h 2 //.h 01  h 2s /.             (2.40)
                                    2 2  2 2s
                          Nozzle efficiency is sometimes expressed in terms of various loss or other coeffi-
                          cients. An enthalpy loss coefficient for the nozzle can be defined as

                                             1 2
                                N D .h 2  h 2s //. c /,                                   (2.41)
                                             2 2
                          and, also, a velocity coefficient for the nozzle,
                              K N D c 2 /c 2s .                                           (2.42)

                          It is easy to show that these definitions are related to one another by
                                                2
                                N D 1/.1 C   N / D K .                                    (2.43)
                                                N
                            EXAMPLE 2.2. Gas enters the nozzles of a turbine stage at a stagnation pressure
                          and temperature of 4.0 bar and 1200 K and leaves with a velocity of 572 m/s and
                          at a static pressure of 2.36 bar. Determine the nozzle efficiency assuming the gas
                          has the average properties over the temperature range of the expansion of C p D
                          1.160 kJ/kg K and 
 D 1.33.
                            Solution. From eqns. (2.40) and (2.35) the nozzle efficiency becomes

                                   1   T 2 /T 01    1  T 2 /T 01
                                N D           D                  .
                                   1   T 2s /T 01  1  .p 2 /p 01 / .
 1//
                          Assuming adiabatic flow .T 02 D T 01 /:
                                        1 2             1      2
                              T 2 D T 02  c /C p D 1200   ð 572 /1160 D 1059 K,
                                        2 2             2
                          and thus
                                     1   1059/1200     0.1175
                                N D                  D        D 0.9576.
                                   1   .2.36/4/ 0.33/1.33  0.12271


                          Diffusers

                            A diffuser is a component of a fluid flow system designed to reduce the flow
                          velocity and thereby increase the fluid pressure. All turbomachines and many other
                          flow systems incorporate a diffuser (e.g. closed circuit wind tunnels, the duct
                          between the compressor and burner of a gas turbine engine, the duct at exit from a
                          gas turbine connected to the jet pipe, the duct following the impeller of a centrifugal
                          compressor, etc.). Turbomachinery flows are, in general, subsonic (M< 1) and the
                          diffuser can be represented as a channel diverging in the direction of flow (see
                          Figure 2.13).
                            The basic diffuser is a geometrically simple device with a rather long history of
                          investigation by many researchers. The long timespan of the research is an indicator
                          that the fluid mechanical processes within it are complex, the research rather more
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