scholarly journals Development of a procedure for the synthesis of a micro gas turbine engine neural controller with account for fuel consumption constraints

2018 ◽  
Vol 17 (3) ◽  
pp. 93
Author(s):  
A. V. Kuznetsov ◽  
G. M. Makaryants
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbine Engine ◽  
Neural Controller ◽  
Turbine Engine ◽  
Micro Gas Turbine ◽  
Consumption Constraints

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.

scholarly journals Micro Gas Turbine Engine: A Review

10.5772/54444 ◽  
2013 ◽  
Author(s):  
Marco Antnio Rosa do Nascimento ◽  
Lucilene de ◽  
Eraldo Cruz dos Santos ◽  
Eli Eber Batista Gomes ◽  
Fagner Luis Goulart ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Micro Gas Turbine

Off-Design Characteristics of Low-Fuel Consumption Gas Turbine Engine for Long-Range UAV

2013 ◽  
Author(s):  
Roberto Andriani ◽  
Umberto Ghezzi ◽  
Antonella Ingenito ◽  
Fausto Gamma ◽  
Antonio Agresta
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Long Range ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Design Characteristics

Performance and Emission Characteristics of a Small Scale Gas Turbine Engine Fueled With Propanol/Jet A Blends

2011 ◽  
Author(s):  
Carlos J. Mendez ◽  
Ramkumar N. Parthasarathy ◽  
Subramanyam R. Gollahalli
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbine Engine ◽  
Single Stage ◽  
Specific Fuel Consumption ◽  
Small Scale ◽  
Emission Characteristics ◽  
Turbine Engine ◽  
Performance And Emission ◽  
Emission Index

Alcohols serve as an alternate energy resource to the conventional petroleum-based fuels. The objective of this study was to document the performance and emission characteristics of blends of n-propanol and Jet A fuel in a small-scale gas turbine engine. The experiments were conducted in a 30kW gas turbine engine with a single-stage centrifugal flow compressor, annular combustion chamber and a single-stage axial flow turbine. In addition to neat propanol and Jet A fuel, three blends, with 25%, 50% and 75% of propanol by volume, were used as the fuels. The thrust, thrust-specific fuel consumption, and the concentrations of CO and NOx in the exhaust were measured and compared with those measured with Jet A fuel. The engine was operated at the same throttle settings with all the fuels. The operational range of engine rotational speed was shifted downwards with the addition of propanol due to its lower heating value. The thrust specific fuel consumption increased with the addition of propanol, while the CO emission index increased and NOx emission index decreased.

2704 The Fluid Simulation of Combustor for Micro Gas Turbine Engine

2007 ◽  
Vol 2007.20 (0) ◽  
pp. 391-392
Author(s):  
Yuki YAMADA ◽  
Junnosuke YOKOO ◽  
Naoki TAKANO ◽  
Toshiyuki TORIYAMA ◽  
Akira FURUTANI ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Fluid Simulation ◽  
Turbine Engine ◽  
Micro Gas Turbine
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