The T64 is a turboshaft/turboprop aircraft engine under development by the Small Aircraft Engine Department of the author’s company for the U. S. Navy Bureau of Weapons. A summary is given of the basic design criteria for the engine as well as a brief description of the engine configuration and highlights of engine development experience. A summary of the engine configuration is given in Table 1.
Since 1956, when the last report on closed-cycle gas-turbine development was presented in the U. S., six solid-fuel-fired plants, rated from 2 to 13.5-mw, have come into operation. Additional oil and gas-fired installations, both for stationary power plants and ship propulsion, have been built and operated or will soon start operation. Unfortunately, none of these are in the U. S.
This paper covers the reasons why the standby plant was required, the selection of plant site and economic considerations governing the selection of equipment. The installation is described in some detail including building design, arrangement of equipment, significant design features and method of operation.
The G.6 gas turbine, of 7500-shp output, forms part of the combined steam-turbine and gas-turbine propulsion machinery currently being installed in two classes of British naval ships. The design specification included some requirements of a novel nature; details are given of the mechanical construction of the gas turbine, and of its test-bed performance. The possibilities of further development are outlined.
The paper presents a detailed thermodynamic analysis of a combined gas-turbine “CO” boiler installation. Regenerator flue gas with 9 per cent CO is burned to CO2 using gas-turbine exhaust which contains 17 per cent O2. In addition, the first costs of a steam-turbine drive is compared to that of the gas-turbine installation. The summary is a comparison of the anticipated efficiency with those being experienced.
The Maritime gas-cooled-reactor concept is a closed-cycle nuclear propulsion system in the 20,000-shp range. The power cycle consists of a beryllium-oxide, helium-cooled reactor, directly coupled to a closed-cycle axial-flow, split turbine. The high-pressure turbine drives the directly connected helium compressors. The low-pressure turbine drives the propeller shaft through a suitable speed reducer. Problems relating to the design development of principal plant components and systems, and the current status of turbomachinery and reactor technology are discussed.
Steadily rising shipbuilding costs, approaching block obsolescence of the bulk of our active fleet, and the rapid advance of weapons technology are the major problems facing the U. S. Navy today. The ability of the gas turbine to make important contributions to combatting each of these problems has resulted in a rapid rise in its use. Specific current programs and applications are discussed.
Segregates present in highly alloyed materials, particularly in modified 12 per cent Cr steels, can have very adverse effects on the physical and mechanical properties. It has been shown that such inhomogeneities can act as inherent notches or stress risers which contribute to or cause premature failures. The fact that such segregation cannot be detected by nondestructive magnetic-particle or sonic tests dictates the use of alternate inspection and process methods to qualify highly stressed parts, such as turbine wheels, for actual service. Turbine wheels, especially those of high-alloy content, produced in accordance with inspection procedures and process methods described herein can be assured to give reliable and satisfactory service.
In 1958, The Orlando Utilities Commission installed two gas turbines for peaking and standby service. These units were then the largest simple-cycle gas turbines in the United States and among the largest anywhere, Fig. 1. The operating and maintenance experience with these units should be of interest to other users and potential users of large simple-cycle gas turbines.
Reliability and improvements in industrial gas turbines are closely related to the materials study programs which are conducted in support of the turbine design. The studies at the author’s company are described with presentation of blade and disk material data. Field experience as related to materials evaluations are described, with particular emphasis on returning parts to service. Materials now available when fully evaluated, through the program described, will permit metal temperatures 100 degrees F higher than currently used.
The Coal-Burning Closed-Cycle Gas Turbine