Paper 16: Case for the Single-Shaft Vehicular Gas Turbine Engine

1968 ◽  
Vol 183 (14) ◽  
pp. 156-176 ◽  
Author(s):  
A. F. McLean
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Fuel Economy ◽  
Lower Cost ◽  
Turbine Engine ◽  
Advantages And Disadvantages ◽  
Initial Cost ◽  
Variable Transmission ◽  
Infinitely Variable Transmission

This paper reviews gas turbine cycles most favoured for vehicular use. It suggests the single-shaft turbine engine as a possible contender for a lower cost approach, where fuel economy requirements are not met by complexity of cycle but by operation at higher turbine inlet temperatures. The question, ‘Where does the engine end and the transmission begin?’ is discussed, and an example of an infinitely variable transmission is explored as a means for overcoming the performance deficiencies of the single-shaft machine. The paper examines the advantages and disadvantages of this type of turbine engine with respect to acceleration and torque characteristics, fuel consumption, engine braking, initial cost, and design for simplicity and high temperature.

Challenges for Implementing a Distributed-Control System for Turbine Engines

2010 ◽  
Author(s):  
Andrew W. Berner
Keyword(s):  
Control System ◽  
High Temperature ◽  
Gas Turbine ◽  
Distributed Control ◽  
Power Distribution ◽  
Distributed Control System ◽  
Turbine Engine ◽  
Advantages And Disadvantages ◽  
Technical Challenges ◽  
Near Term

For several years, the potential benefits of implementing a distributed-control system on an airborne gas-turbine engine have been discussed and analyzed. However, after many years of trade studies and lab demonstrations, it appears that the airborne gas-turbine community is no closer to implementing this type of distributed architecture. The NASA-sponsored Distributed Engine Control Working Group is attempting to unify the efforts of engine manufacturers, their system integrators, and sub-tier suppliers. In order to collectively move forward, it is necessary to understand the issues that have impeded the progress of this approach. In so doing, the industry can focus on the near-term work required to develop programs that would create the necessary infrastructure to make airborne turbine-engine-based distributed-control systems a reality. This paper will present some proposed distributed-control architectures, advantages and disadvantages of some of these approaches, and will discuss the major technical challenges that have, to date, prevented these architectures from becoming viable. Some of the architectural approaches range from a fully distributed system (one distributed-control module per actuator loop) to a “hybridized” system that has a data concentrator and a reduced FADEC. The technical challenges that will be discussed include: high-temperature electronics, robust serial-communication bus in a high-temperature environment, power distribution, and certification.

TIMETAL 551

Alloy Digest ◽  
2006 ◽  
Vol 55 (5) ◽  
Keyword(s):  
Shear Strength ◽  
High Temperature ◽  
Physical Properties ◽  
Gas Turbine ◽  
Heat Treating ◽  
Nominal Composition ◽  
Turbine Engine ◽  
Temperature Performance ◽  
Beta Alloy ◽  
Alpha Beta

Abstract Timetal 551 is an improved-strength version of Timetal 550 alloy that retains good forging characteristics. The alpha-beta alloy has a nominal composition of Ti-4Al-4Mo-4Sn-0.5 Si, and it is used in gas turbine engine parts. This datasheet provides information on composition, physical properties, elasticity, tensile properties, and shear strength as well as creep. It also includes information on high temperature performance as well as forming and heat treating. Filing Code: TI-138. Producer or source: Timet.

Future Vehicular Recuperator Technology Projections

1994 ◽  
Author(s):  
Robert A. Wilson ◽  
Daniel B. Kupratis ◽  
Satyanarayana Kodali
Keyword(s):  
Gas Turbine ◽  
Fuel Economy ◽  
Department Of Defense ◽  
Gas Turbines ◽  
High Performance ◽  
Development Program ◽  
Turn Of The Century ◽  
Turbine Engine ◽  
Technology Roadmap ◽  
Vehicle Propulsion

The Department of Defense and NASA have funded a major gas turbine development program, Integrated High Performance Turbine Engine Technology (IHPTET), to double the power density and fuel economy of gas turbines by the turn of the century. Seven major US gas turbine developers participated in this program. While the focus of IHPTET activity has been aircraft propulsion, the same underlying technology can be applied to water craft and terrestrial vehicle propulsion applications, such as the future main battle tank. For these applications, the gas turbines must be equipped with recuperators. Currently, there is no technology roadmap or set of goals to guide industry and government in the development of a next generation recuperator for such applications.

Epoxy-free high-temperature fiber optic pressure sensors for gas turbine engine applications

2004 ◽  
Author(s):  
Juncheng Xu ◽  
Gary Pickrell ◽  
Bing Yu ◽  
Ming Han ◽  
Yizheng Zhu ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Fiber Optic ◽  
Pressure Sensors ◽  
Gas Turbine Engine ◽  
Turbine Engine

LV100 AIPS Technology—For Future Army Propulsion

1992 ◽  
Author(s):  
Walter Brockett ◽  
Angelo Koschier
Keyword(s):  
Control Systems ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Cooling System ◽  
Gas Turbine Engine ◽  
Air Filtration ◽  
Turbine Engine ◽  
Overall Design ◽  
Armored Vehicle ◽  
And Control

The overall design of and Advanced Integrated Propulsion System (AIPS), powered by an LV100 gas turbine engine, is presented along with major test accomplishments. AIPS was a demonstrator program that included design, fabrication, and test of an advanced rear drive powerpack for application in a future heavy armored vehicle (54.4 tonnes gross weight). The AIPS design achieved significant improvements in volume, performance, fuel consumption, reliability/durability, weight and signature reduction. Major components of AIPS included the recuperated LV100 turbine engine, a hydrokinetic transmission, final drives, self-cleaning air filtration (SCAF), cooling system, signature reduction systems, electrical and hydraulic components, and control systems with diagnostics/prognostics and maintainability features.

scholarly journals Investigation of Micro Gas Turbine Systems for High Speed Long Loiter Tactical Unmanned Air Systems

Aerospace ◽  
2019 ◽  
Vol 6 (5) ◽  
pp. 55 ◽  
Author(s):  
James Large ◽  
Apostolos Pesyridis
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
High Speed ◽  
Engine Performance ◽  
Operating Conditions ◽  
Turbine Engine ◽  
Micro Gas Turbine ◽  
Fan Speed ◽  
Relative Design ◽  
Design Simplicity

In this study, the on-going research into the improvement of micro-gas turbine propulsion system performance and the suitability for its application as propulsion systems for small tactical UAVs (<600 kg) is investigated. The study is focused around the concept of converting existing micro turbojet engines into turbofans with the use of a continuously variable gearbox, thus maintaining a single spool configuration and relative design simplicity. This is an effort to reduce the initial engine development cost, whilst improving the propulsive performance. The BMT 120 KS micro turbojet engine is selected for the performance evaluation of the conversion process using the gas turbine performance software GasTurb13. The preliminary design of a matched low-pressure compressor (LPC) for the proposed engine is then performed using meanline calculation methods. According to the analysis that is carried out, an improvement in the converted micro gas turbine engine performance, in terms of thrust and specific fuel consumption is achieved. Furthermore, with the introduction of a CVT gearbox, the fan speed operation may be adjusted independently of the core, allowing an increased thrust generation or better fuel consumption. This therefore enables a wider gamut of operating conditions and enhances the performance and scope of the tactical UAV.

The Allison 570/571 Gas Turbine for Patrol Boat Power

1986 ◽  
Author(s):  
John E. Roberts
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Power Density ◽  
Design Features ◽  
Excellent Performance ◽  
Turbine Engine ◽  
Consumption Rates ◽  
Hull Forms ◽  
Main Components ◽  
Density Ratios

This paper discusses the use of 570/571-KF engine in patrol boat propulsion applications. The text is composed of two basic sections — 1. The Engine, and 2. The Applications: The engine section includes a brief review of the background and development of this free turbine engine, as well as a description of the main components and design features. The performance characteristics and fuel consumption rates are discussed relative to patrol missions. In the applications section a comparison is made of the current 570 installations (both civil and military), along with a survey of the planned applications. Finally a review of proposed uses of these engines in other naval vessels is included to show the adaptability of this size engine in FPB and PB missions, and demonstrate the feasibility of retrofitting other turbine or diesel powered patrol boats with 570/571-KF engines. The conclusion is drawn that for patrol boats with conventional or modified hull forms, the Allison 570/571 engines are well suited due to their excellent performance and power density ratios.

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