scholarly journals The Use of Mathematical Modeling in the Analysis of Gas Turbine Compressor Unit Test Data

1981 ◽  
Author(s):  
L. J. Williams
Keyword(s):  
Mathematical Modeling ◽  
Gas Turbine ◽  
Test Data ◽  
Performance Test ◽  
Test Results ◽  
Compressor Unit ◽  
Turbine Performance ◽  
Modelling Procedure ◽  
Gas Turbine Compressor ◽  
Actual Test

A clear need exists for methods of establishing the validity of gas turbine performance test results and diagnosing the causes of performance problems. Published methods depend on the results of simulating faults in complex mathematical models of the engines and are only capable of diagnosing combinations of faults previously simulated. A very simple mathematical modelling procedure is described which allows the analyst to test his own hypothesis of engine faults and so identify instrumentation errors and discover conditions not previously considered. Application of modelling to actual test data is demonstrated.

scholarly journals Fully Loaded Factory Test of the CW251B12 Gas Turbine Engine

1990 ◽  
Author(s):  
Ihor S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Test Data ◽  
Performance Test ◽  
Engine Performance ◽  
Test Facility ◽  
Test Results ◽  
Turbine Engine ◽  
Engine Model ◽  
Factory Test ◽  
Industrial Gas Turbine

The fully loaded factory test of the CW251B12 45 MW class industrial gas turbine is described in this paper. This gas turbine is the latest uprating of the W251 series of engines. The main objectives of the factory test were the verification of the performance and the mechanical integrity of the new engine model. A brief description of the main features of the engine, the application of the first unit, the test facility, and the engine instrumentation used in the test is included. Details of the engine performance test results, telemetry test data results, and the hot end component metal temperature measurements are provided.

Fully Loaded Factory Test of the CW251B12 Gas Turbine Engine

1991 ◽  
Vol 113 (4) ◽  
pp. 482-487 ◽  
Author(s):  
I. S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Test Data ◽  
Performance Test ◽  
Engine Performance ◽  
Test Facility ◽  
Test Results ◽  
Turbine Engine ◽  
Engine Model ◽  
Factory Test ◽  
Industrial Gas Turbine

The fully loaded factory test of the CW251B12 45 MW class industrial gas turbine is described in this paper. This gas turbine is the latest uprating of the W251 series of engines. The main objectives of the factory test were the verification of the performance and the mechanical integrity of the new engine model. A brief description of the main features of the engine, the application of the first unit, the test facility, and the engine instrumentation used in the test is included. Details of the engine performance test results, telemetry test data results, and the hot end component metal temperature measurements are provided.

Model Based Performance Correction Methodology — A Case Study

2014 ◽  
Author(s):  
Koldo Zuniga ◽  
Thomas P. Schmitt ◽  
Herve Clement ◽  
Joao Balaco
Keyword(s):  
Control System ◽  
Control Systems ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Performance Test ◽  
Test Results ◽  
Model Based ◽  
Test Conditions ◽  
Partial Load

Correction curves are of great importance in the performance evaluation of heavy duty gas turbines (HDGT). They provide the means by which to translate performance test results from test conditions to the rated conditions. The correction factors are usually calculated using the original equipment manufacturer (OEM) gas turbine thermal model (a.k.a. cycle deck), varying one parameter at a time throughout a given range of interest. For some parameters bi-variate effects are considered when the associated secondary performance effect of another variable is significant. Although this traditional approach has been widely accepted by the industry, has offered a simple and transparent means of correcting test results, and has provided a reasonably accurate correction methodology for gas turbines with conventional control systems, it neglects the associated interdependence of each correction parameter from the remaining parameters. Also, its inherently static nature is not well suited for today’s modern gas turbine control systems employing integral gas turbine aero-thermal models in the control system that continuously adapt the turbine’s operating parameters to the “as running” aero-thermal component performance characteristics. Accordingly, the most accurate means by which to correct the measured performance from test conditions to the guarantee conditions is by use of Model-Based Performance Corrections, in agreement with the current PTC-22 and ISO 2314, although not commonly used or accepted within the industry. The implementation of Model-based Corrections is presented for the Case Study of a GE 9FA gas turbine upgrade project, with an advanced model-based control system that accommodated a multitude of operating boundaries. Unique plant operating restrictions, coupled with its focus on partial load heat rate, presented a perfect scenario to employ Model-Based Performance Corrections.

Operating Experience of the First Solar® Taurus 70S Mechanical Drive Installation

1997 ◽  
Author(s):  
A. James Hoshizaki
Keyword(s):  
Gas Turbine ◽  
Performance Test ◽  
Operating Experience ◽  
Field Performance ◽  
Field Evaluation ◽  
Pipeline System ◽  
Test Results ◽  
Compressor Station ◽  
Test Program ◽  
Natural Gas Pipeline

In October 1995, NOVA Gas Transmission Ltd. (NGTL) commissioned the first mechanical drive application of Solar Turbines’ Taurus™ 70S gas turbine. The unit was installed as a part of a turbine/compressor package at a compressor station on NGTL’s natural gas pipeline system. As this first installation was a part of a development test program by Solar Turbines, field evaluation was conducted subsequent to the original commissioning and related testing. This paper presents NGTL’s experiences in commissioning, startup and operation. Field performance test results for the gas turbine are presented and focus on output power, thermal efficiency and exhaust emissions. Some of the findings and observations from the field evaluation tests performed by Solar are also discussed. In addition, a description of the facility in which the turbine/compressor package is installed is provided.

scholarly journals Retrofitting a 100,000 HP Simple Cycle Gas Turbine Compressor Station With Regenerators

1983 ◽  
Author(s):  
Arjo Klyn ◽  
Hans Wylens
Keyword(s):  
Gas Turbine ◽  
Transport System ◽  
Gas Turbines ◽  
Gas Transport ◽  
Peak Load ◽  
Simple Cycle ◽  
Compressor Station ◽  
Compressor Unit ◽  
Gas Turbine Compressor ◽  
Base Load

In its gas transport system N.V. Nederlandse Gasunie found a shift from peak load to base load at stations which were not originally designed for that duty. A study was made of the application of recuperators on GE frame 5 gas turbines, based on experience with a prototype installation four years ago. The paper describes the Breda-regenerator in general and the experience of one of the two prototypes which was installed on a Gasunie frame 5 two shaft 24 mW gas turbine compressor unit in 1978. In June 1981 Gasunie decided to equip two more identical gas turbine compressor units at their 100,000 HP compressor station at Zweekhorst with Breda-regenerators. The paper covers all aspects of retrofitting the simple cycle gas turbine installations with regenerators at the Zweekhorst station.

The Design and Calibration of a Heat-Fluxmeter for Gas Turbine Studies

1994 ◽  
Author(s):  
Paul C. Ivey
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Test Data ◽  
Performance Test ◽  
Instrument Design ◽  
Sample Heat ◽  
Aero Engine ◽  
Nose Cone ◽  
Idealised Model ◽  
Design Construction

This paper details the design, construction and calibration of a heat-fluxmeter to measure at one end of an idealised model of an aero-engine drive shaft. The constraints on instrument design of manufacture and calibration, together with the matching of instrument and measurement characteristics are discussed. Sample heat-transfer results based upon fluxmeter measurements are presented. A model for the heat-transfer to the nose-cone of an aero-engine for anti-icing applications, derived from these results, is shown to compare favourably with analysis of engine icing performance test data.

scholarly journals A Practical Guide for Gas Turbine Performance Field and Test Data Analysis

1992 ◽  
Author(s):  
Francoise M. Krampf
Keyword(s):  
Data Analysis ◽  
Gas Turbine ◽  
Test Data ◽  
Performance Data ◽  
Test Cell ◽  
Simple Cycle ◽  
Simple Method ◽  
Practical Guide ◽  
Turbine Performance

This paper provides a simple method for correcting and analyzing the performance data from a simple cycle, two shaft gas turbine. This data may have been collected in a test cell, in the field or by a user who desires to closely monitor the performance of an engine.

Analysis of Changes in the Performance Characteristics of Steam Turbines

1971 ◽  
Vol 93 (2) ◽  
pp. 225-237 ◽  
Author(s):  
K. C. Cotton ◽  
P. Schofield
Keyword(s):  
Steam Turbine ◽  
Test Data ◽  
Performance Test ◽  
Performance Characteristics ◽  
Steam Turbines ◽  
Case Histories ◽  
Turbine Performance ◽  
Internal Condition ◽  
Proper Analysis

The proper analysis of routine steam turbine performance test data can afford valuable information on the internal condition of a steam turbine. This paper outlines the theory behind the analysis of test data together with several case histories illustrating the use of the analysis to pinpoint various steam turbine problems.

Improving Gas Turbine Performance Through Reassembling Degraded Components: An Experimental and Computational Study

2020 ◽  
Author(s):  
Shuocheng Xia ◽  
Zhongran Chi ◽  
Shusheng Zang ◽  
Hui Wang
Keyword(s):  
Gas Turbine ◽  
Test Data ◽  
Thermal Efficiency ◽  
Gas Turbines ◽  
Computational Study ◽  
Low Cost ◽  
Gas Turbine Engine ◽  
Performance Degradation ◽  
Turbine Engine ◽  
Turbine Performance

Abstract Performance degradation of gas turbine is a common phenomenon during operation. Maintenance of the degraded gas turbines and improving their performance at a low cost are important in engineering. In this paper, the maintenance method based on reassembling degraded components of existing gas turbines was studied. This research was based on a type of 2MW gas turbine engine. Blue ray scanning was carried out to rebuild the 3D flow-path geometries of the compressor and turbine of a degraded engine. Then CFD simulations were carried out to compare the characteristic maps of new and degraded components. Secondly, performance tests of six engines were carried out. A correction method was developed to get the specific component characteristics using test data, which can also analyze and quantify the degradations. Also, a gas turbine performance prediction program was used to find the promising component-exchange plan within 5 given gas turbines to improve total thermal efficiency. Finally, additional test was carried out to verify the performance of the reassembled gas turbine. Through the developed method including 3D scanning, CFD simulation, and correction of component characteristics with engine test data, the component performance degradation of a specific gas turbine can be obtained in quantity. The gas turbine performance predictions based on the acquired characteristic maps showed good agreement with test data. With the help of the method developed in this work, a new gas turbine engine was obtained through exchanging the components of degraded engines, which is at a very low cost and in a short time. The improvement in total thermal efficiency was about 0.3 percentage, which was verified by engine tests.

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