Prognosis for Safe Water-Disposal-Well Operations and Practices That Are Based on Reservoir Flow Modeling and Real-Time Performance Analysis

2018 ◽  
Vol 21 (03) ◽  
pp. 576-592 ◽  
Author(s):  
Maulin Pankaj Gogri ◽  
Joseph M. Rohleder ◽  
C. Shah Kabir ◽  
Matthew J. Pranter ◽  
Zulfiquar A. Reza
Keyword(s):  
Performance Analysis ◽  
Real Time ◽  
Flow Modeling ◽  
Safe Water ◽  
Time Performance ◽  
Reservoir Flow ◽  
Water Disposal

Real-Time Performance Analysis of FOI-PD Controller for Twin Rotor MIMO System

2018 ◽  
Vol 36 (6) ◽  
pp. 547-567
Author(s):  
Debdoot Sain ◽  
Subrat Kumar Swain ◽  
Ayan Saha ◽  
Sudhansu Kumar Mishra ◽  
Sarbani Chakraborty
Keyword(s):  
Performance Analysis ◽  
Real Time ◽  
Mimo System ◽  
Pd Controller ◽  
Time Performance ◽  
Twin Rotor Mimo System ◽  
Twin Rotor

Development of Condition Monitoring Test Cell Using Micro Gas Turbine Engine

2009 ◽  
Author(s):  
Seonghee Kho ◽  
Jayoung Ki ◽  
Miyoung Park ◽  
Changduk Kong ◽  
Kyungjae Lee
Keyword(s):  
Performance Analysis ◽  
Real Time ◽  
Gas Turbine ◽  
Condition Monitoring ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Test Cell ◽  
Turbine Engine ◽  
Time Performance ◽  
Engine Condition

This study is aim to be programmed the simulation which is available for real-time performance analysis so that is to be developed gas turbine engine’s condition monitoring system with analyzing difference between performance analysis results and measuring data from test cell. In addition, test cell created by this study have been developed to use following applications: to use for learning principals and mechanism of gas turbine engine in school, and to use performance test and its further research for variable operating conditions in associated institutes. The maximum thrust of the micro turbojet engine is 137 N (14 kgf) at 126,000 rpm of rotor rotational speed if the Jet A1 kerosene fuel is used. The air flow rate is measured by the inflow air speed of duct, and the fuel flow is measured by a volumetric fuel flowmeter. Temperatures and pressures are measured at the atmosphere, the compressor inlet and outlet and the turbine outlet. The thrust stand was designed and manufactured to measure accurately the thrust by the load cell. All measuring sensors are connected to a DAQ (Data Acquisition) device, and the logging data are used as function parameters of the program, LabVIEW. The LabVIEW is used to develop the engine condition monitoring program. The proposed program can perform both the reference engine model performance analysis at an input condition and the real-time performance analysis with real-time variables. By comparing two analysis results the engine condition can be monitored. Both engine performance analysis data and monitoring results are displayed by the GUI (Graphic User Interface) platform.

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