Simulation Study on the Work Characteristics of Combined Diesel-Electric and Gas Turbine (CODLAG)

2018 ◽  
Author(s):  
Zhitao Wang ◽  
Jian Li ◽  
Tielei Li ◽  
Weitian Wang ◽  
Shuying Li
Keyword(s):  
Gas Turbine ◽  
Working Conditions ◽  
Electric Propulsion ◽  
Simulation Method ◽  
Propulsion System ◽  
Future Research ◽  
Work Condition ◽  
Loop Control ◽  
Integrated Simulation ◽  
Variable Condition

The combined diesel-electric and gas turbine (CODLAG) plant is a new type of ship power plant combining the advantages of electric propulsion system and mechanical propulsion system. The requires about ship power grid is lower than full electric propulsion mode, at the same time it can gain the quiet of electric propulsion in the low working conditions and increase the mobility of the ship in the high working conditions. Unlike traditional mechanical propulsion methods and forward-looking all-electric propulsion methods, the CODLAG plant has a coupling between mechanical propulsion and electric propulsion mode. The cooperative working characteristics of two different nature systems is still need further research. For the in-depth research of CODLAG device’s characters, this study built a simulation model of CODLAG device based on Matlab/Simulink and C/C++ platform. A kind of torque-shaft speed double closed-loop control strategy based on PID was used on the CODLAG device. And the typical work condition of CODLAG, including merging, merging off and variable work condition, was simulated in this study. Through the simulation, the dynamic response of main parameters at typical condition have been got. Then, characters of CODLAG device with CPP was simulated at variable condition. And the thrust response was compared with FPP’s. Through comparative analysis, the effectiveness of integrated simulation method specifying to CODLAG device was verified, and some useful conference was provided for the future research.

scholarly journals Integrated Systems Simulation for Assessing Fuel Thermal Management Capabilities for Hybrid-Electric Rotorcraft

2020 ◽  
Author(s):  
Ioannis Roumeliotis ◽  
Lorenzo Castro ◽  
Soheil Jafari ◽  
Vassilios Pachidis ◽  
Louis De Riberolles ◽  
...  
Keyword(s):  
Thermal Management ◽  
Electric Propulsion ◽  
Cooling Capacity ◽  
Propulsion System ◽  
Fuel Tank ◽  
Thermal Loads ◽  
Simulation Framework ◽  
Propulsion Systems ◽  
Integrated Simulation ◽  
Hybrid Electric

Abstract Future aircraft and rotorcraft propulsion systems should be able to meet ambitious targets and severe limitations set by governments and organizations. These targets cannot be achieved through marginal improvements in turbine technology or vehicle design. Hybrid-electric propulsion is being widely considered as a revolutionary concept to further improve the environmental impact of air travel. One of the most important challenges and barriers in the development phase of hybrid-electric propulsion systems is the Thermal Management System (TMS) design, sizing and optimization for addressing the increased thermal loads due to the electric power train. The aim of this paper is to establish an integrated simulation framework including the vehicle, the propulsion system and the fuel-oil system (FOS) for assessing the cooling capability of the FOS for the more electric era of rotorcrafts. The framework consists of a helicopter model, propulsion system models, both conventional and hybrid-electric, and a FOS model. The test case is a twin-engine medium (TEM) helicopter flying a representative Passenger Air Transport (PAT) mission. The conventional power plant heat loads are calculated and the cooling capacity of the FOS is quantified for different operating conditions. Having established the baseline, three different Power Management Strategies (PMS) are considered and the integrated simulation framework is utilized for evaluating FOS temperatures. The results highlight the limitations of existing rotorcraft FOS to cope with the high values of thermal loads associated with hybridization for the cases examined. Hence, new ideas and embodiments should be identified and assessed. The case of exploiting the fuel tank as a heat sink is investigated and the results indicate that recirculating fuel to the fuel tank can enhance the cooling capacity of conventional FOS.

Life Cycle Analysis for a Powertrain in a Concept for Electric Power Generation in a Hybrid Electric Aircraft

2020 ◽  
Author(s):  
Michael Schneider ◽  
Jens Dickhoff ◽  
Karsten Kusterer ◽  
Wilfried Visser
Keyword(s):  
Life Cycle ◽  
Gas Turbine ◽  
Electric Propulsion ◽  
Aircraft Engine ◽  
Propulsion System ◽  
Civil Aviation ◽  
Propulsion Systems ◽  
Hybrid Propulsion ◽  
Hybrid Electric ◽  
The Impact

Abstract In the recent decades, civil aviation was growing 4.7% per annum. In order to reduce emissions promoting the global warming process, alternative propulsion systems are needed. Full-electric propulsion systems in aviation might have the potential for emission-free flights using renewable energy. However, several research efforts indicate electric propulsion only seems feasible for small aircraft. Especially due to the low energy density of batteries compared to fossil fuels. For this reason, hybrid propulsion systems came into focus, combining the benefits of all-electric and conventional propulsion system concepts. It is also considered as bridging technology, system test and basis for component development — and therewith paves the way towards CO2 free aviation. In the ‘HyFly’ project (supported by the German Luftfahrtforschungsprogramm LuFo V-3), the potential of a hybrid electric concept for a short/mid-range 19 PAX aircraft is assessed — not only on system but also on single component basis. In a recent study, the propulsion architecture and the operating mode of the gas turbine and the electric components have been defined [1]. In this paper, the advantages of the hybrid propulsion architecture and a qualitative assessment of component life are presented. Methods for life time prediction for the aircraft engine, the electric motor, the reluctance generator and the battery are discussed. The impact of turbine inlet temperature on life consumption is analyzed. The life cycle of the aircraft engine and the electric components including gradual component deterioration and consequent performance degradation is simulated by using an in-house gas turbine simulation tool (GTPsim). Therefore, various effects on electric propulsion system can be predicted for the entire drivetrain system in less than one hour.

scholarly journals Installation of a Gas-Turbine/Electric Propulsion System in a 65 Foot Patrol Boat

1995 ◽  
Author(s):  
J. B. Brown ◽  
Nicholas F. Martino ◽  
William S. Stavenger ◽  
C. M. Lee
Keyword(s):  
Gas Turbine ◽  
Electric Propulsion ◽  
Propulsion System ◽  
Foot Patrol ◽  
Electric Propulsion System ◽  
Electrical Propulsion

This paper presents a descriptive summary of the significant features of a gas-turbine/electrical propulsion system as installed in a 65 foot patrol boat for test purposes.

A hybrid propulsion system for a high-endurance UAV: configuration selection, aerodynamic study, and gas turbine bench tests

2014 ◽  
Vol 02 (01) ◽  
pp. 16-35 ◽  
Author(s):  
R. Capata ◽  
L. Marino ◽  
E. Sciubba
Keyword(s):  
Gas Turbine ◽  
Electric Propulsion ◽  
High Performance ◽  
Limited Range ◽  
Propulsion System ◽  
Major Drawback ◽  
Hybrid Propulsion ◽  
Electric Generator ◽  
Wide Range ◽  
Configuration Selection

In recent years, renewed interest in the development of unmanned aerial vehicles (UAVs) has led to a wide range of interesting applications in reconnaissance and surveillance. In these missions, the noise produced by propeller-driven UAVs is a major drawback, which can be partially solved by installing an electric motor to drive the propeller. While the evolution of high performance brushless motors makes electric propulsion particularly appealing, at least for small and medium UAVs, all electric propulsion systems developed to date are penalized by the limited range and endurance that can be provided by a reasonably sized battery pack. In this paper we propose a hybrid propulsion system based on a recently developed ultramicro gas–turbine (UMGT), which can be used to power an electric generator, providing a significant range and (or) mission time extension. The UMGT is undergoing operational testing in our laboratory, to identify the most suitable configuration and to improve performance: a new compact regenerative combustion chamber was developed and several tests are being carried out to reduce its weight and size so as to increase, all other things being equal, the vehicle payload. This paper aims to propose a high endurance UAV, by a preliminary configuration selection and aerodynamic study of its performance.

The Procurement of a 1–2MW Gas Turbine Alternator for the Royal Navy

2000 ◽  
Author(s):  
James A. Fielder
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Electric Propulsion ◽  
Propulsion System ◽  
Royal Navy ◽  
Procurement Process ◽  
Electric Propulsion System ◽  
High Level

This paper provides a high level overview of why the Royal Navy is seeking to procure a 1–2MW Gas Turbine Alternator as part of a full electric propulsion system. It describes the Royal Navy requirements of marine gas turbines and highlights the reasons for the adoption of Integrated Full Electric Propulsion. The paper also describes the major technical and commercial requirements of the 1–2MW gas turbine alternator and the procurement process that was used to select the prime contractor.

scholarly journals An LNG Carrier Adjustable Speed Gas Turbine Electric Propulsion System

1981 ◽  
Author(s):  
M. R. Hauschildt ◽  
L. P. Gripp ◽  
W. Peters
Keyword(s):  
Gas Turbine ◽  
Electric Propulsion ◽  
Operating Characteristic ◽  
Waste Heat ◽  
Propulsion System ◽  
Diesel Fuels ◽  
Adjustable Speed ◽  
Liquid Natural Gas ◽  
Electric Loads ◽  
Fuel Costs

This paper describes the design of a 43,000 shp (32,065 KW), 110 propeller rpm, Liquid Natural Gas (LNG) Carrier, gas turbine AC electric, adjustable speed propulsion system, burning LNG and/or diesel fuels. Excess boil-off energy is dissipated through a load bank resistor system. Boil-off compressor, ship service electric loads and auxiliary steam services are supplied by waste heat boilers. A relative economic and operating characteristic comparison of steam vs gas turbine electric LNG propulsion plants is presented for various assumed fuel costs. The ship application is a single shaft, 125,000 cubic meter LNG Carrier of about 96,000 tons (97,541 tones) displacement.

scholarly journals High Impact Shock Test of a General Electric LM2500 Propulsion Gas Turbine Module

1973 ◽  
Author(s):  
W. R. Bobo
Keyword(s):  
Gas Turbine ◽  
Electric Propulsion ◽  
High Impact ◽  
Propulsion System ◽  
Test Results ◽  
General Electric ◽  
Shock Test ◽  
Shock Testing ◽  
System Components ◽  
Impact Shock

This paper discusses the high impact shock testing of a General Electric Propulsion Gas Turbine Module to the requirements of Military Specification MIL-S-901C. This shock qualification is just one of a comprehensive program of tests to be, performed to fully qualify the LM2500 Gas Turbine and the DD-963 Propulsion System components specifically for the Spruance (DD-963) Class Destroyers. The description of the gas turbine and the preparation for, and the conduct of the shock test, and a review of the shock test results are presented.

Dynamic Simulation and Control Strategy for Three-Shaft Marine Electric Propulsion Gas Turbine

2010 ◽  
Author(s):  
Chenyu Wei ◽  
Shusheng Zang
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Control Strategy ◽  
Electric Propulsion ◽  
Dynamic Performance ◽  
Propulsion System ◽  
System Quality ◽  
Matching Problems ◽  
Electric Propulsion System ◽  
And Control

Three-shaft gas turbine was applied to marine electric propulsion system. The dynamic performance and control strategy of the three-shaft marine electric propulsion gas turbine arrested investigator’s attention, because they are very different from that of single-shaft gas turbine due to the complicated rotor structure. In this study, a model of nonlinear differential equation set is built to calculate the dynamic performance of three-shaft gas turbine and a simulation model of three-shaft marine electric propulsion gas turbine is constructed using the platform of MATLAB/SIMULINK. An adaptive software is developed for three-shaft gas turbine simulation. The new matching problems and changing rules among parameters are investigated in the case of load rejection of marine electric propulsion system. Multi-closed loop control system, instead of traditional control system, is introduced in order to improve the system quality and safety.

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