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Gas Turbine Design Axial Flow Compressors

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Gas Turbine Design Axial Flow Compressors ( gas-turbine-design-axial-flow-compressors )

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total loss by superposition of entropy generation terms as opposed to the traditional superposition of loss terms (see Appendix D). However, at the low levels of losses experienced in a well-designed transonic compressor, the difference between the total loss calculated by superposition of pressure losses as opposed to that calculated by entropy generation is found to be negligible. In addition, because loss mechanisms do not behave completely linearly, either method provides a satisfactory approximation of the total loss. If the loss and deviation are known in addition to the blade geometry and inlet conditions, the streamline curvature simulation can obtain exit flow thermodynamic and fluid mechanic properties. Unfortunately, there is no strictly theoretical means of obtaining loss or deviation. However, simple analyses may be employed to provide useful insights, and combined with empirical information can provide a satisfactory basis for cascade design (Hill & Peterson, 1967). As stated previously, 2-D cascades and 2-D cascade theory are commonly used to model flow in transonic compressors. Note that 2-D linear cascade data and theory must be modified in order to prepare them for use in modeling an actual 3-D compressor flowfield. Some adjustments in converting from a 2-D to a 3-D flowfield include: 1) New definition of loss to account for change in radius 2) Conversion from 2-D to 3-D loss 3) Converting 2-D Axial Velocity Density Ratio to analogous 3-D Meridional Velocity Density Ratio 4) Introduction of new losses such as those due to mid-span dampers, casing and hub boundary layers, vortices between the casing and the rotor tip, and additional secondary losses which are not present in strictly 2-D flowfields. The definition of the above terms and their application to loss modeling will be explained in subsequent sections. 9

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