The Part-Load Performance of Various Gas-Turbine Engine Schemes

Abstract

The literature on the gas turbine already contains much information concerning the performance of the “constant-pressure” cycle both in its simple form and in its more complicated forms involving intercooled compression, reheated expansion, and heat exchange. Such information enables the design performance of a particular engine to be estimated, but there appears to be very little published work to help the designer to foretell what changes in performance are to be expected when particular engines operate at non-design conditions. What work there is seems to have been restricted to very simple engines, and is often further limited by the assumption of unalterable component performance characteristics. In this lecture we attempt to include in a general comparison of part-load performance characteristics not only the simpler designs but also some of the more complex turbine engines which will be needed for land and marine applications. At the same time, by considering, in appropriate cases, the influence of changes in the assumed component performance features on the part-load operation of an engine, a broadening of the basis of comparison is made possible. As a result of the work we shall describe we feel that, although as yet so little of the possible field of investigation has been surveyed, it is nevertheless possible to indicate the main guiding principles by which the comparative part-load performance of different gas turbine schemes may be assessed.

Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by Optimization Procedure

“…A number of components are theoretically possible if, in addition to the positioning of the compressor and turbines, distinction is drawn between the inclusion and omission of a regenerator and intercooler. A conventional three-group notation is adopted (Mallinson et al, 1948). The first group gives the number of turbocompressor rotors.…”

The Constant Volume Gas Turbine Cycle According to Karavodine

“…Normal performance calculations for radial compressors require factors it, (D and fl. Their interrelationship has been analysed using constant or 0 'u N at AT N2 (Mallinson [16]). The approach cpreferred here is to estimate a general compressor map as an averaged version of those of several identical centrifugal compressors and fit it to an analytical form of elliptic equations ( fig.…”

Approximately Calculating Optimum Pressure Ratios for Various Gas Turbine Cycles

“…neglected, the pressure loss coefficient, b, in equation (6) become equal to 1. Equation (6) is not clear as equation (3); i.e., the relationship between the optimum pressure ratio for maximum thermal efficiency r cm. , 7 and n c , nT , T, and b in equation (6).…”