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.

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 Performance Test of the CW251B10 Gas Turbine Engine

1986 ◽  
Author(s):  
Ihor S. Diakunchak ◽  
David R. Nevin
Keyword(s):  
Gas Turbine ◽  
Performance Test ◽  
Engine Performance ◽  
Test Facility ◽  
Performance Tests ◽  
Test Results ◽  
Turbine Engine ◽  
Factory Test ◽  
Engine Component ◽  
Industrial Gas Turbine

A fully loaded factory test of the CW251B10 41MW class industrial gas turbine was carried out at the Westinghouse Canada test facility. This gas turbine, which is the latest of the W251 engine series, represents an advancement in industrial gas turbine technology. One of the main objectives of the factory test was the verification of the engine performance. The test results demonstrated that the CW251B10 engine achieved its performance goals. This paper describes some of the results of the performance tests and includes engine component performance details.

Cold Flow Turbine Rig Tests of the Original and Redesigned Compressor Turbines of an Industrial Gas Turbine Engine

1989 ◽  
Vol 111 (2) ◽  
pp. 146-152
Author(s):  
I. S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Advanced Technology ◽  
Test Facility ◽  
Test Results ◽  
Original Design ◽  
Turbine Engine ◽  
Cold Flow ◽  
Industrial Gas Turbine ◽  
Stage Efficiency

This paper describes the results of cold flow turbine rig tests carried out on the original and redesigned compressor turbines of an industrial gas turbine engine. Some details of the aerodynamic design of the latest variant, a brief description of the advanced technology design methods used in this design, and a description of the test facility are included. Bulk stage performance and detail rotor exit radial-circumferential traverse results are presented. These test results demonstrate that the design point stage efficiency of the redesigned compressor turbine is about six percentage points higher than that of the original design.

Inverse Generation of Gas Turbine Component Performance Maps From Experimental Test Data

2010 ◽  
Author(s):  
Changduk Kong ◽  
Semyeong Lim ◽  
Seonghwan Oh ◽  
Jihyun Kim
Keyword(s):  
Real Time ◽  
Gas Turbine ◽  
Condition Monitoring ◽  
Test Data ◽  
Performance Test ◽  
Monitoring Program ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Performance Data ◽  
Turbine Engine

The gas turbine engine performance is greatly relied on its component performance characteristics. Generally, acquisition of component maps is not easy for engine purchasers because it is an intellectual property of gas turbine engine supplier. In the previous work, the maps were inversely generated from engine performance deck data. However this method is limited to obtain the realistic maps from the calculated performance deck data. Present work proposes a novel method to generate more realistic component maps from experimental performance test data. In order to demonstrate the proposed method, firstly the NI data acquisition device with the proposed LabVIEW on-condition monitoring program monitors and collects real-time performance data such as temperature, pressure, thrust, and fuel flow etc. from a micro turbojet engine of the test setup which is specially manufactured for this study. Real-time data obtained from the test results are used for inverse generation of the component maps after processing by some numerical schemes. Realistic component maps can then be generated from those processed data using the proposed extended scaling method at each rotational speed. Verification can be made through comparison between performance analysis results using the performance simulation program including the generated compressor map and on-condition monitoring performance data.

Components Map Generation of Gas Turbine Engine Using Genetic Algorithms and Engine Performance Deck Data

2006 ◽  
Vol 129 (2) ◽  
pp. 312-317 ◽  
Author(s):  
Changduk Kong ◽  
Jayoung Ki
Keyword(s):  
Experimental Data ◽  
Genetic Algorithms ◽  
Gas Turbine ◽  
Test Data ◽  
Engine Performance ◽  
Scaling Method ◽  
Turbine Engine ◽  
Scaling Methods ◽  
Map Generation ◽  
Component Map

In order to estimate the gas turbine engine performance precisely, the component maps containing their own performance characteristics should be used. Because the components map is an engine manufacturer’s propriety obtained from many experimental tests with high cost, they are not provided to the customer generally. Some scaling methods for gas turbine component maps using experimental data or data partially given by engine manufacturers had been proposed in a previous study. Among them the map generation method using experimental data and genetic algorithms had showed the possibility of composing the component maps from some random test data. However not only does this method need more experimental data to obtain more realistic component maps but it also requires some more calculation time to treat the additional random test data by the component map generation program. Moreover some unnecessary test data may introduced to generate inaccuracy in component maps. The map generation method called the system identification method using partially given data from the engine manufacturer (Kong and Ki, 2003, ASME J. Eng. Gas Turbines Power, 125, 958–979) can improve the traditional scaling methods by multiplying the scaling factors at design point to off-design point data of the original performance maps, but some reference map data at off-design points should be needed. In this study a component map generation method, which may identify the component map conversely from some calculation results of a performance deck provided by the engine manufacturer using the genetic algorithms, was newly proposed to overcome the previous difficulties. As a demonstration example for this study, the PW206C turbo shaft engine for the tilt rotor type smart unmanned aerial vehicle which has been developed by Korea Aerospace Research Institute was used. In order to verify the proposed method, steady-state performance analysis results using the newly generated component maps were compared with them performed by the Estimated Engine Performance Program deck provided by the engine manufacturer. The performance results using the identified maps were also compared with them using the traditional scaling method. In this investigation, it was found that the newly proposed map generation method would be more effective than the traditional scaling method and the methods explained above.

Performance Deterioration in Industrial Gas Turbines

1992 ◽  
Vol 114 (2) ◽  
pp. 161-168 ◽  
Author(s):  
I. S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

scholarly journals Application of High Bypass Turbofan Computer Simulation to Flight and Test Data Processing

1982 ◽  
Author(s):  
J. F. Chapier ◽  
L. Levine
Keyword(s):  
Computer Simulation ◽  
Computer Program ◽  
Simulation Model ◽  
Gas Turbine ◽  
Data Reduction ◽  
Engine Performance ◽  
Computer Simulation Model ◽  
Test Results ◽  
Static Test ◽  
Turbine Engine

This paper describes the computer program used to compare gas turbine engine flight and static test results with a predicted standard engine computer simulation model. The program is conceived not only for a final presentation of engine performance, but also as a research tool to further analyze the validity of measurements and the assumptions used in data reduction.

Performance Deterioration in Industrial Gas Turbines

1991 ◽  
Author(s):  
Ihor S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

Components Map Generation of Gas Turbine Engine Using Genetic Algorithms and Engine Performance Deck Data

2006 ◽  
Author(s):  
Changduk Kong ◽  
Jayoung Ki ◽  
Changho Lee
Keyword(s):  
Experimental Data ◽  
Genetic Algorithms ◽  
Gas Turbine ◽  
Test Data ◽  
Engine Performance ◽  
Scaling Method ◽  
Turbine Engine ◽  
Scaling Methods ◽  
Map Generation ◽  
Component Map

In order to estimate the gas turbine engine performance precisely, the component maps containing their own performance characteristics should be needed. Because the components map is an engine manufacturer’s propriety obtained from many experimental tests with high cost, they are not provided to the customer generally. Some scaling methods for gas turbine component maps using experimental data or data partially given by engine manufacturers had been proposed in previous study. Among them the map generation method using experimental data and genetic algorithms (Kong et al., 2004) had showed a possibility composing the component maps from some random test data. However not only this method needs more experimental data to obtain the more realistic component maps but also it requires some more calculation time to treat the additional random test data by component map generation program. Moreover some unnecessary test data may introduce to generate inaccuracy in component maps. And the map generation method called as the system identification method using partially given data from engine manufacturer (Kong et al., 2003) can improve the traditional scaling methods by multiplying the scaling factors at design point to off-design point data of the original performance maps, but some reference map data at off-design points should be needed. In this study a component map generation method which may identify component map conversely from some calculation results of a performance deck provided by engine manufacturer using the Genetic Algorithms was newly proposed to overcome the previous difficulties. As a demonstration example for this study, the PW206C turbo shaft engine for the tilt rotor type Smart UAV (Unmanned Aerial Vehicle) which has been developed by KARI (Korea Aerospace Research Institute) was used. In order to verify the proposed method, steady-state performance analysis results using the newly generated component maps were compared with them performed by EEPP (Estimated Engine Performance Program) deck provided by engine manufacturer. And also the performance results using the identified maps were compared with them using the traditional scaling method. In this investigation, it was found that the newly proposed map generation method would be more effective than the traditional scaling method and the methods explained at the above.

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