A 750-Kw Gas Turbine Generator Set for USS Oklahoma City (CGL-5)

A description of a 750-kw emergency and standby electric-generator set as installed in the USS Oklahoma City. Operating experience is summarized. The 1100-hp gas turbine in this set is the largest installed in a U. S. Naval combat ship.

The Volvo-Turbo Experimental Gas Turbine

This paper gives a brief description of the Volvo experimental turbine, its working cycle, its basic components and their relative arrangement as well as some of the basic thinking behind the selection of the same. The paper also gives a short description of the new concept of a dual-geared power turbine, the combined reduction gear and high-speed hydrodynamic retarder, as well as some other new features incorporated.

Design Features for a 22-Mw Decentralized Gas-Turbine Plant

Today many utilities are confronted with the problem of increasing their generating capacity to shave system peaks. By the nature of being a complete power cycle, the gas turbine appears as an attractive prime mover in this type application. This paper describes a 22-mw decentralized gas-turbine generating station designed specifically for peaking service. The philosophy of the design of the equipment and its arrangement in the plant is included along with a description of its control and operation.

Binary Cycle Gas Fired Turbine for Gas Compression Service

Three years ago a survey was made of the various prime movers available to the pipeline industry for gas compression. This survey included gas turbines and two and four-cycle reciprocating gas engines. The purpose of this study was to determine which of the existing equipments would be most economical and whether or not there was a need for the development of additional equipment. As a result of this economic study, it appeared there was a definite requirement in the industry for a high-speed, low-cost, gas turbine-centrifugal compressor unit for both field and main-line-station gas compression. As a result of the studies two gas-turbine-driven centrifugal compressor units were placed in operation early in 1960 at Cypress Station near Houston, waste-heat recovery systems being installed in the summer of 1961. Performance tests were satisfactory and subsequently six small gas-engine-driven compressor units have been installed at two main-line compressor stations.

El Paso Uprates Two Gas Turbines

El Paso discusses the philosophy of uprating older gas turbines by taking advantage of the continuous progress being made in turbine design. This paper describes El Paso’s uprating of two General Electric gas turbines and includes the feasibility study, modificaton required and operating experience.

Gas Turbines in Hydrofoil Seacraft

This paper describes the use of gas-turbine propulsion systems in hydrofail seacraft. Background information on the early hydrofoil developments is presented, as well as discussions of the factors affecting choice of power plants, economics of operation, and the practical considerations involved with respect to marine environments, installation requirements, and engine characteristics. Descriptions of turbine-powered hydrofoil craft are also included.

Design and Test of a Small Turbine-Compressor Set for a Nuclear Application

This paper describes the design of a turbine-compressor set in the 400–500 kw power range for use in the ML-1 mobile nuclear power plant. The specification and design problems are discussed in terms of mechanical design and aerodynamic performance. The open-cycle test facility is also described and the results of open-cycle testing are surveyed.

Development of a Control System for a Dual-Shaft Gas Turbine for Rapid Load Acceptance and Rejection

The application required large electrical load changes with very limited variations in frequency and voltage. With a dual-shaft gas turbine, nominal rating 8000 kilowatts, instantaneous loads up to 90 per cent rated were successfully accepted and rejected with frequency maintained within a one and one half per cent band. Voltage variation did not exceed four per cent. Frequency and voltage recovery were well within two seconds. The foregoing was accomplished by incorporating a control system which permitted operation of the turbine at other than normal operating conditions when auxiliary control valves were preset in anticipation of the load variation. The auxiliary control valves were air-inlet throttling valves, an inter-turbine bleed valve, and an additional fuel valve. The basic machine consisted of a 15-stage axial compressor, a two-stage, high-pressure turbine, and a two-stage power turbine. The unique requirements necessitated off-design operation and considerable extrapolation from known test data. However, it was possible to program the control-system components so that a conventional pneumatic control system was capable of maintaining speed within the prescribed band even though the applied load varied from that anticipated by as much as 12.5 per cent.

Production of Integrally-Cast Airfoil Components for Small Gas-Turbine Engines

This paper presents a review of the progress made by the investment casting foundries in producing integrally-cast airfoil components for small gas-turbine engines. The casting process, from pattern production to the final inspection operations, is discussed in detail. Suggested dimensional tolerances, based on the present state of the art, are included. Finally, the properties and casting characteristics of various alloys commonly used for internal components are presented.

American Airlines Experience With Turbojet/Turbofan Engines

The turbojet engine JT3C-6 and JT3C-7 entered commercial service on American Airlines Boeing 707/720 Aircraft after a considerable period of experience resulting from military J57 operation. Although the commercial operation uncovered problem areas, the causes were defined and the engine reliability and serviceability responded to various improvement programs. The time between overhauls (TBO) increased from 800 to 2100 hr at a rate unparalled in commercial engine operation. The turbofan is now going through a period of commercial “growing pains.” Problems have resulted from higher thrust, use of new materials, higher temperatures within and outside the engine, complexities of a fan air-thrust reverser, and so on. The airframe and engine manufacturers have defined these problems and together with the commercial operators are engaged in programs to insure performance and reliability compatible with the tremendous success of the first generation JT3C-6 and JT3C-7 turbojets.