The Design of Turbomachinery for the Gas Turbine (Direct Cycle) High Temperature Gas Cooled Reactor Power Plant

The Gas Turbine HTGR, or “Direct Cycle” High-Temperature Gas-Cooled, Reactor power plant, uses a closed-cycle gas turbine directly in the primary coolant circuit of a helium-cooled high-temperature nuclear reactor. Previous papers have described configuration studies leading to the selection of reactor and power conversion loop layout, and the considerations affecting the design of the components of the power conversion loop. This paper discusses briefly the effects of the helium working fluid and the reactor cooling loop environment on the design requirements of the direct-cycle turbomachinery and describes the mechanical arrangement of a typical turbomachine for this application. The aerodynamic design is outlined, and the mechanical design is described in some detail, with particular emphasis on the bearings and seals for the turbomachine.

An Optimizing Design Point Program for Selection of a Gas Turbine Cycle

As vehicles evolve through the concept phase, a wide variety of engines are usually considered. For long-life vehicles such as heavy armored tracked vehicles, gas turbines have been favored because of their weight and volume characteristics at high hp levels (1500 to 2000 hp). Many existing gas turbine engines, however, are undesirable for vehicular use because their original design philosophy was aircraft oriented. In a ground vehicle, mass flow and expense are only two areas in which these engines differ greatly. Because the designer generally is not given the freedom to design an engine from scratch, he must evaluate modifications of the basic Brayton cycle. In this study, various cycles are evaluated by using a design point program in order to optimize design parameters and to recommend a cycle for heavy vehicular use.

COGOG Propulsion Installations in Guided Missile and Standard Class Frigates of the Royal Netherlands Navy: A Review of the Development From the Specific Design Philosophies to the Actual Technical, Personnel and Maintenance/Logistic Management in Service

This paper gives a brief survey of the overall design philosophies of the Olympus/Tyne twin shaft propulsion plants in the unmanned engine rooms of the Guided Missiles and Standard class frigates of the Royal Netherlands Navy, including the installation’s major auxiliaries, electronic control system, solid state surveillance and data recording equipment Complimentary to this paper is the paper by J. B. Kerpestein of Royal Schelde entitled, “Propulsion Gearing Transmission Systems for Guided Missile and Standard Frigates of the Royal Netherlands Navy” (ASME Paper No. 77-GT-67). The author further outlines briefly current ship operating experience and the reorganization undertaken by the RNN to satisfy the requirements for personnel training and technical and logistic support of the gas turbines.

Development of the Centrifugal Compressor for the Nissan Vehicular Gas Turbine

This paper outlines the development process of the centrifugal compressor of the Nissan vehicular gas turbine YTP12 The compressor should provide a solid performance as a component of a vehicular prime mover. As we have managed to achieve the design performance by modifying the components of the compressor within the limited sphere permitted by the dimensions of a given engine, this paper will cover the key processes of improvement, as well as some additional information which may be applicable to future compressor designs.

Computation of the Temperature Distribution in Cooled Radial Inflow Turbine Guide Vanes

A two-dimensional finite-difference numerical technique is presented to determine the temperature distribution of an internally-cooled blade of radial turbine guide vanes. A simple convection cooling is assumed inside the guide vane. Such an arrangement results in relatively small cooling effectiveness at the leading edge and at the trailing edge. Heat transfer augmentation in these critical areas may be achieved by using impingement jets and film cooling. A computer program is written in Fortran IV for IBM 370/165 computer.

Cooling Considerations for Design of a Radial Inflow Turbine

A numerical study to determine the temperature distribution in the rotor of a radial inflow turbine is presented. Internal cooling passages are modeled in the present formulation in order to carry out solid and coolant temperature computations simultaneously resulting in a considerable computer time savings. The stresses due to centrifugal and thermal loadings are determined in an actual rotor and the effect of cooling design on its mechanical integrity is discussed.

Some Measured and Calculated Effects of Forward Velocity on Propeller Noise

The results of a program investigating the sources of noise in unshrouded propellers under forward flight conditions and a comparison with theory are reported. Tests were conducted using an instrumented three-bladed propeller installed on a turbine-powered, twin-engine, general aviation airplane. Measurements included far-field noise on the ground and on the aircraft wing tip, propeller blade surface pressures, atmospheric turbulence, and aircraft operating conditions. The primary result of the full-scale flight tests was to confirm that foward-flight propeller noise levels are lower than those experienced under static conditions and that the most significant reductions occur at the mid-frequencies which dominate perceived and A-weighted noise levels. Analytical techniques have been used to predict the observed experimental trends and to provide further insight into the noise generating mechanisms. Correlation with experimental data is shown to be good at low frequencies under static conditions and at all frequencies in forward flight. It is tentatively concluded that propeller noise generation in flight may result from steady loads (including blade thickness effects). Under static conditions, the principal noise source appears to be the intersection of the propeller with persistent turbulent eddies passing through the propeller disk.

The Effect of a Transversely Injected Stream on the Flow Through Turbine Cascades: Part I — Flow Effects

A study has been made of the flow-through turbine cascade when a transverse flow is injected into the main flow immediately in front of the cascade. A separation bubble was observed on the end-wall immediately behind the injection slot. At the suction surface end of this bubble a vortex moved into the main flow and continued downstream through, and beyond, the cascade. The effects of the separation bubble and of the vortex were observed in measurements of pressure around the blade surfaces, in boundary layer transverses on the end-wall, and in total head and directional transverses across the cascade exit.

The Shaft Coupled Lift/Cruise Fan Propulsion System for Navy Multimission V/STOL Aircraft

The Navy has promoted requirements for aircraft capable of operating from ships smaller than the CV class of large aircraft carriers. The subsonic roles within these requirements may be met by a multimission V/STOL aircraft powered by an integrated lift cruise fan propulsion system using advanced turboshaft engines and shafting for power distribution. General system requirements, unique features and characteristics, and special design considerations relating to V/STOL, such as propulsive lift control, engine sizing and engine out ratings, are presented.

A Study of Commuter Aircraft Design

Commuter airlines have generally demonstrated excellent growth in recent years. This growth has been accomplished mainly with aircraft that have evolved from larger general aviation aircraft or specially designed utility aircraft. None reflect a configuration optimized for the current type of passenger service early in the vehicle definition phase. This paper investigates the impact of configuration considerations, mission requirements, and performance constraints on conceptual commuter aircraft designs. Emphasis is placed on direct comparisons between turbofan and turboprop powered aircraft in the 10–30 passenger class. The analysis is accomplished using a computerized aircraft synthesis model that simulates the aircraft design and mission. The resulting conceptual aircraft are similar in size and performance regardless of engine type but the turboprop offers more mission flexibility.