Planning and Development for a New Generation of Gas Turbine Propelled Ships in the U.S. Navy

In the early 1970s, gas turbine technology had reached the stage where it became feasible to consider marinization of state-of-the-art aircraft engines. Approximately concurrently with these technological advances, the U.S. Navy had the need to project replacements for many of its conventionally propelled surface ships of World War II vintage. Characteristics of good fuel economy coupled with potentially viable reliability and maintenance characteristics conditioned the development of main and auxiliary gas turbine prime movers for ships. Ship design, therefore, was strongly influenced by previously unavailable power plant characteristics. New ships are building and others actively being designed to draw upon these technological advantages, and a broad base of support is being established to ensure the continued long range mobility of the U.S. Navy’s ships.

Control for 600-Bhp Dump Truck Gas Turbine Engine With Recuperator

A fuel control system for a prototype gas turbine with recuperator is described. The electronic fuel control was designed with the aid of a hybrid simulator. Its performance is verified on the bench test for a 600-bhp gas turbine engine with recuperator. Prediction of vehicle behavior and transmission requirements were made for a heavy-duty, 32-ton dump truck equipped wtih the 600-bhp gas turbine engine.

The Use of Desk Top Computers in the Teaching of Aircraft Gas Turbines

The fairly recent advent of programmable desk top computers with branching and looping capability has allowed the simple and rapid handling of otherwise very complicated engineering problems. The teaching of aircraft gas turbines is particularly enhanced by the use of such computers because remarkably accurate performance calculations, design calculations or flow field calculations can be made on such machines. The rapid calculation capability of the computer frees the student to concern himself with the implications of the results, rather than with the minutia of the calculations. Four specific example programs and results are given: (a) Design calculations for a turbojet; (b) Design calculations for a fan jet, in which the bypass ratio is optimized to give minimum specific fuel consumption; (c) Performance calculations for both a conventional turbojet and a variable area turbojet; (d) Flow field calculations for a highly loaded actuator disk.

Regenerator Development for the British Leyland 2S/350/R Gas Turbine Engine

This paper describes the application of the ceramic regenerator to the British Leyland truck gas turbine. Aspects of mounting, driving and sealing the heat exchanger disk are covered with particular reference to the single disk version of the 2S/350/R engine.

Inspection, Maintenance and Field Repair of Heavy Duty Industrial Gas Turbines

The expenditures for inspection and maintenance of gas turbines are an important part of the total owning and operating costs. Maintenance outage time should be kept to a minimum. A proper design with adequate ports facilitates visual and boroscope inspection of critical areas. Maintenance outage time can be considerably reduced by special equipment which allows inspection and replacement of bearings and combustor inner parts and balancing of rotors without major disassembly of the unit. The advantages of an indoor installation with overhead crane with respect to maintenance are also discussed in this paper.

Application of a Two-Dimensional Supersonic Passage Analysis to the Design of Compressor Rotors

A description of a two-dimensional supersonic cascade passage analysis and its application to the design of a high hub-to-tip ratio supersonic compressor rotor is presented. The analysis, applicable to the case in which the inviscid flow is everywhere supersonic, includes an entrance region calculation which accounts for blade leading edge bluntness effects, and a passage and wake region calculation. The inviscid part of the analysis is solved using a rotational method of characteristics. The effect of the blade boundary layer displacement thickness is taken into consideration. Comparison of the results of the analysis with supersonic cascade data is made, showing good agreement in overall performance prediction, in blade surface static pressure distributions, and in achievement of the desired shock wave patterns. A comparison of the results of the analysis is made also with the performance of a blade section of a high hub-to-tip ratio supersonic compressor and acceptable agreement obtained.

Construction and Initial Operating Experience on Two Prototype Gas Turbine Power Plants

In this paper, the authors describe construction and initial operating experience on two prototype gas turbine power plants located thousands of miles apart: Isefjordvaerket’s 140-MW plant at Kyndby, Denmark, built by Brown Boveri-Sulzer Turbomachinery (BST) and Northern States Power’s 200-MW plant at Blue Lake, Minnesota, built by Turbodyne Corporation (TBD). The paper provides a unique opportunity of comparing two approaches to a similar plant construction concept.

A 125-Mw Unfired Combined Cycle Electric Generating Unit From Concept to Operation

This paper discusses the development of a 125-Mw combined cycle generating unit from the original developmental concepts to the initial operation. The initial justification, the evolution of the plant through design, and the actual construction are discussed. The actual construction site and the equipment utilized are described. A discussion of the cooling system and the licensing efforts that were required are also discussed. This paper also shows how this type of plant will provide a versatile, economical, mid-range peaking plant.

NEPCOMP: The Navy Engine Performance Program

A general purpose computer program is described which permits rapid design point and off-design performance analyses of air breathing engines. The modular approach used in building the over-all program allows analysis of many engine configurations including multi-stream, multi-nozzle, augmented engines, shaft engines and ramjets. The program may be operated with or without component maps. The result is a computational tool that can be used to perform independent analyses of an engine manufacturer’s product as well as provide engine performance data for use in engine-airframe design and integration studies.

A Comparison of Analog, Digital and Hybrid Computing Techniques for Simulation of Gas Turbine Performance

Simulation of gas turbine dynamic performance can be accomplished using analog, digital or hybrid computing techniques. The paper discusses computing techniques for each type of computer and reviews their advantages and disadvantages. It is concluded that the three types of simulation are complementary to each other and that all three computers have their place: the analog is essential for real time simulation of complex engines, the digital is most suitable for detailed studies and the hybrid combines the ease of integration of the analog with the logic and stored program capability of the digital.