Transcription of Axial-Flow Compressors
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Axial-Flow Compressors
Introduction The Compressors in most gas turbine applications, especially units over 5MW, use axial fl ow Compressors . An axial fl ow compressor is one in which the fl ow enters the compressor in an axial direction (parallel with the axis of rotation), and exits from the gas turbine, also in an axial direction. The axial-fl ow compressor compresses its working fl uid by fi rst accelerating the fl uid and then diffusing it to obtain a pressure increase. The fl uid is accelerated by a row of rotating airfoils (blades) called the rotor, and then diffused in a row of stationary blades (the stator). The diffusion in the stator converts the velocity increase gained in the rotor to a pressure increase. A compressor consists of several stages: 1) A combination of a rotor followed by a stator make-up a stage in a compressor; 2) An additional row of stationary blades are frequently used at the compressor inlet and are known as Inlet Guide Vanes (IGV) to ensue that air enters the fi rst-stage rotors at the desired fl ow angle, these vanes are also pitch variable thus can be adjusted to the varying fl ow requirements of the engine; and 3) In addition to the stators, another diffuser at the exit of the compressor consisting of another set of vanes further diffuses the fl uid and cont
High-aspect ratio blades are often pretwisted so that at full operational speed the centrifugal forces acting on the blades will untwist the blades to the designed aerodynamic angle. The pretwist angle at the tip for blades with AR ratios of about four is between two and four degrees. The air inlet angle α 1
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