By Thaddeus W. Fowler
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Extra info for Jet Engines and Propulsion Systems for Engineers
Example text
4> = gJAH/2U2 (turbines) $ = 2gJAH/U: (compressors) where AH = change in total enthalpy across the stage and U = wr or the linear velocity of rotation at radius r. Thus, the work coefficient is the ratio of work per unit mass flow divided by the wheel speed squared. 3 Mechanical Design Limits the Euler equation, which give the work input for a rotating blade row; gJAH = A(UCu) where Cu is the tangential component of the fluid velocity. In axial compressors and turbines it can be assumed that the radial shift in the streamline between the inlet and exit of a blade row is small, so mat the change in the blade rotational speed along a streamline is negligible.
In this chapter we are concerned with how the separate elements work together to provide the overall static structure of an engine. What are the major design issues which dictate the nature of the frames, casings and mounts? What are the loads for which we must design? First of all, the static components must maintain alignment between the rotors and stators of the turbomachinery. In many cases, this dictates a need for stiffness, rather than strength, in the frames and in the casings between the frames.
The low pressure turbine casing provides the support for the primary nozzle and, in this diagram, a turbine reverser. Note that the fan frame hub carries the 03 ball bearing at the front of the high pressure compressor, and the compressor rear frame carries the #4 roller bearing between the rear of the compressor and the front of the high pressure turbine. The turbine mid-frame carries two roller bearings, the #5 bearing at the rear of the high pressure turbine and the #6 bearing at the forward shaft of the low pressure turbine.
