Fabrication of ATTAP Ceramic Turbine Components

The development and fabrication of sintered alpha SiC injection molded axial rotors and slip cast vortexes by Carborundum for the Advanced Turbine Technology Applications Project (ATTAP) are discussed. Key injection molding process variables and their levels were identified through modeling and experimental design. Post-HIPing improved the density, strength, and uniformity of injection molded components. The fabrication and strength of slip cast components were enhanced through dispersion and powder beneficiation studies. The component process optimization approaches and current status are presented for each.

Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by Optimization Procedure

This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including scramjet engine) to achive the maximum performance. The optimization of such criteria as thermal efficiency, specific output and total performance for gas turbine engines, and overall efficiency, non-dimensional thrust and specific impulse for aero-engines have been performed by the optimization procedure with multiplier method. The comparisons of results with analytical solutions establishes the validity of the optimization procedure.

Adaptation of a Small Commercial Fan Jet Trainer for Military Applications

The JTI5D-4 engine is a successful small fan jet with a history of reliable service in fast, economical executive jet aircraft. This paper describes the unique design features which were necessary to convert it to the military combat trainer role, together with the associated development program. It includes details of a special test facility constructed to simulate aerobatic flight conditions, and discusses some aspects of field experience in a single engine trainer application.

Gas Turbine Powered Blue Riband Winner

The high speed yacht “Gentry Eagle” has set a new record for Atlantic Ocean crossing plus two other speed records. The British built, United States owner 110 ft. craft is powered by two diesels and a centerline 4,000 hp marine gas turbine. The paper will describe all the power plants and the propulsion system for each. Gas turbine mounting, control, inlet and exhaust treatment, and operating scenario will be covered. Craft details will be included. History of the vessel including performance and speed run details will be noted.

New Generation of the Small Turboshaft and Turboprop Engines in the U.S.S.R.

The main requirements for a new generation of small turboshaft and turboprop engines in the USSR are considered. The main performance of the new small engines developed in the USSR are given and their features are emphasized.

EJ200: The Engine for the New European Fighter Aircraft

This paper describes the concept and design of the EJ200 engine to meet the air staff targets for the European Fighter Aircraft. The international collaborative arrangements to support the programme are shown and the lessons learnt from previous collaboration illustrated. The excellent progress made in the programme during the first year since the signing of the development contract is described to illustrate confidence in the ability to meet the design targets within the programme timescales.

Stealth Aircraft-History, Technology and Outlook

The development of low observables or Stealth technology is reviewed. Brief descriptions are given of the major Stealth aircraft programs now under way, including the Lockheed F-117A, the Northrop B-2, the US Air Force’s Advanced Tactical Fighter and the US Navy’s A-12. Mention is made of LO work in other nations and potential counters to Stealth are summarised.

Gas Turbine Engine Test Cell Modeling

A numerical simulation of the aerothermal characteristics of a gas turbine engine test cell is presented. The three-dimensional system is modeled using the PHOENICS computational fluid dynamics code. Results predict the velocity field, temperatures, pressures, kinetic energy of turbulence, and dissipation rates of turbulent kinetic energy. Numerical results from two versions, a cartesian coordinate model and a body fitted coordinate model, are compared to experimental data. The comparison shows good quantitative and very good qualitative agreement, suggesting that numerical modeling would be useful in the preliminary design of gas turbine test facilities.

RAMSCRAM: A Flexible RAMJET/SCRAMJET Engine Simulation Program

With the resurgence of interest in high supersonic and hypersonic flight there is a need to simulate airbreathing engines which may be used in this flight regime. To meet this requirement the RAMSCRAM code was developed. The code calculates one-dimensional flow properties at each component interface and the overall performance of the engine. It uses equilibrium thermodynamics which accounts for dissociation and allows for any fuel or combination of fuels. The program can simulate ramjet, scramjet, rocket, and ducted rocket engines.

Gas Turbine With Intermediate Heat Exchanger for Flight Application

High power/weight ratio and low SFC are the most important requirements for an airborne engine. This may be achieved by a gas turbine engine with an intermediate heat exchanger, combined with a double-decked compressor-turbine design. In this engine, the specific fuel consumption is minimal at 70% of maximum power output for best fuel economy in helicopter engines. The additional weight, due to its design, is compensated by fuel saved in less than one hour flight for a 926 kW cruise power engine.