1948
DOI: 10.1243/pime_proc_1948_159_019_02
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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 n… Show more

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Cited by 26 publications
(7 citation statements)
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“…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.…”
Section: Application Of Optimization Procedures To Stationary Gas Turbinementioning
confidence: 99%
“…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.…”
Section: Application Of Optimization Procedures To Stationary Gas Turbinementioning
confidence: 99%
“…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.…”
Section: Rotating Machinerymentioning
confidence: 99%
“…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).…”
Section: Itt1mentioning
confidence: 99%