Performance Simulation of a Power Generating Gas Turbine in Off-design point Conditions

International Journal of Advanced Scientific and Technical Research 12/2012; 2(6):560-566.


We present an off-design point analysis of a power generating gas turbine based on a reference location in Isle of Man. The off design simulation is carried out at, up to, an altitude of 2km for ambient temperatures range of 1 to 19°C. A parametric analysis for the altitude simulations shows that power output and cycle efficiency reduced with an increasing ambient temperature while fuel consumption increased. The altitude simulation also shows that power output and mass flow rate reduce as altitudes increase, while the cycle efficiency reduces with increasing altitude. Degradation simulation was attempted by using a reduced fraction of the clean engine data and results show that power output was lower even at a higher shaft speed
for a constant turbine entry temperature.

Download full-text


Available from: Akinola Adeniyi, Oct 02, 2015
321 Reads
  • Journal of Propulsion and Power 11/1994; 10(6):890-896. DOI:10.2514/3.23828 · 0.87 Impact Factor
  • [Show abstract] [Hide abstract]
    ABSTRACT: A scaling method for characteristics of gas turbine components using experimental data or partially given data from engine manufacturers was newly proposed. In case of currently used traditional scaling methods, the predicted performance around the on-design point may be well agreed with the real engine performance, but the simulated performance at off-design points far away from the on-design point may not be well agreed with the real engine performance generally. It would be caused that component scaling factors, which were obtained at on-design point, is also used at all other operating points and component maps are derived from different known engine components. Therefore to minimize the analyzed performance error in the this study, firstly component maps are constructed by identifying performances given by engine manufacturers at some operating conditions, then the simulated performance using the identified maps is compared with performances using currently used scaling methods. In comparison, the analyzed performance using the currently used traditional scaling method was well agreed with the real engine performance at the on-design point but had maximum 12% error at off design points within the flight envelope of a calculation example turboprop engine. However the performance result using the newly proposed scaling method had maximum 6% reasonable error even at all flight envelope.
    Journal of Engineering for Gas Turbines and Power 10/2003; 125(4). DOI:10.1115/1.1610014 · 0.80 Impact Factor
  • [Show abstract] [Hide abstract]
    ABSTRACT: Gas turbine diagnostics has a history almost as long as gas turbine development itself. Early engine fault diagnosis was carried out based on manufacturer information supplied in a technical manual combined with maintenance experience. In the late 1960s, when L. A. Urban introduced gas path analysis, gas turbine diagnostics made a big breakthrough. Since then different methods have been developed and used in both aerospace and industrial applications. To date, a substantial number of papers have been published in this area. This paper intends to give a comprehensive review of performance-analysis-based methods available thus far for gas turbine fault diagnosis in the open literature.
    Proceedings of the Institution of Mechanical Engineers Part A Journal of Power and Energy 08/2002; 216(5):363-377. DOI:10.1243/095765002320877856 · 0.65 Impact Factor