scholarly journals Progress on Measurement Techniques for Industrial Gas Turbine Technology

1988 ◽  
Author(s):  
E. Valentini ◽  
P. Lacitignola ◽  
M. Casini
Keyword(s):  
Gas Turbine ◽  
Cooling System ◽  
Fluid Dynamic ◽  
Measurement Techniques ◽  
Experimental Program ◽  
Special Role ◽  
Load Testing ◽  
Ambient Conditions ◽  
Full Load ◽  
Industrial Gas Turbine

Instrumentation and measurements play a very special role in the advancement of gas turbine turbomachinery. In an industrial gas turbine experimental program, testing constantly flanks machine development and full-load testing of extensively instrumented units provides information on both overall and component performance. Rotordynamic testing is performed to determine, in ambient conditions, the optimum configuration for the rotor-bearing-casing assembly. Fluid-dynamic testing on models of the inlet duct, turbine casing and transition piece assembly and blade cooling system is carried out to minimize flow distortions or optimize cooling flows. Stress and modal analyses on turbine and compressor blades are performed, using 3D photoelasticity and holographic interferometry. In the full-load testing, the measurements include thermodynamic values, temperatures of the components, blade vibratory strains, blade tip clearances and axial displacements. Signals from rotating thermocouples and strain gages, installed on both turbine and compressor rotors, are transmitted using slip ring systems. HP blade temperature distribution is measured by means of the infrared pyrometer. Typical Campbell diagrams are derived from the blade strain gage measurements and are used for HCF verification. Radial and axial stator-to-rotor displacements are measured during transients.

Development of the PGT 25 High Efficiency Gas Turbine: Part 3 — Experimental Program and Testing

1984 ◽  
Author(s):  
P. Lacitignola ◽  
E. Valentini
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Engine Performance ◽  
Experimental Methods ◽  
Experimental Program ◽  
Load Testing ◽  
Testing Program ◽  
Full Load ◽  
Engine Testing ◽  
Turbine Design

This paper presents a review of the engineering testing program related to development of the PGT-25 gas turbine. The experimental methods employed and their capability of providing information for the tuning of the engine and its parts are discussed. Testing has continuously supported turbine design and development; integration of analytical and experimental procedures has proven to be efficient for successful final engine testing. Full load testing, using well developed instrumentation, has made it possible to know actual component behavior and engine performance in steady and transient states, over the entire speed and power range. The reliability of the machine has been assessed through the results of these tests.

scholarly journals Fluid Film Bearing Housing Design for a Hot Ambient Environment

1976 ◽  
Author(s):  
J. D. McHugh ◽  
W. O. Winer ◽  
G. D. Robson
Keyword(s):  
Gas Turbine ◽  
Journal Bearing ◽  
Test Facility ◽  
Experimental Program ◽  
Special Test ◽  
Housing Design ◽  
Full Size ◽  
Ambient Temperatures ◽  
Operating Field ◽  
Industrial Gas Turbine

Industrial gas turbine rotors sometimes require a journal bearing in a region of the machine surrounded by compressor discharge air. Ambient temperatures in this region may exceed 600 F (588 K), which poses a challenge to bearing designers. The present paper describes housing design approaches to meeting this challenge, an experimental program to evaluate them, and the application of results to operating field units. The experimental program was carried out in a special test facility on full-size housings for a 14-in. journal bearing in a hot, pressurized environment.

scholarly journals A Thermodynamic Transient Model for Performance Analysis of a Twin Shaft Industrial Gas Turbine

2017 ◽  
Author(s):  
Samuel Cruz-Manzo ◽  
Vili Panov ◽  
Yu Zhang ◽  
Anthony Latimer ◽  
Festus Agbonzikilo
Keyword(s):  
Gas Turbine ◽  
System Performance ◽  
Computational Tool ◽  
Ambient Conditions ◽  
Transient Model ◽  
Simulink Model ◽  
Artificial Neural Network Ann ◽  
Industrial Gas Turbine ◽  
Scientific Engineering ◽  
Steady State Performance

In this study, a Simulink model based on fundamental thermodynamic principles to predict the dynamic and steady state performance in a twin shaft Industrial Gas Turbine (IGT) has been developed. The components comprising the IGT have been implemented in the modelling architecture using a thermodynamic commercial toolbox (Thermolib, EUtech Scientific Engineering GmbH) and Simulink environment. Measured air pressure and air temperature discharged by compressor allowed the validation of the modelling architecture. The model assisted the development of a computational tool based on Artificial Neural Network (ANN) for compressor fault diagnostics in IGTs. It has been demonstrated that modelling plays an important role to predict and monitor gas turbine system performance at different operating and ambient conditions.

Validation of Surface Temperature Measurements on a Combustor Liner Under Full-Load Conditions Using a Novel Thermal History Paint

2016 ◽  
Author(s):  
Robert Krewinkel ◽  
Jens Färber ◽  
Martin Lauer ◽  
Dirk Frank ◽  
Ulrich Orth ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal History ◽  
Measurement Techniques ◽  
Combustion Process ◽  
Lanthanide Ions ◽  
Maximum Temperature ◽  
Oxide Ceramic ◽  
Ambient Conditions ◽  
Hot Gas ◽  
Wide Range

The ever-increasing requirements on gas turbine efficiency, which are at least partially met by increasing firing temperatures, and the simultaneous demand for reduced emissions, necessitate much more accurate calculations of the combustion process and combustor wall temperatures. Thermocouples give locally very accurate measurements of these temperatures, but there is a practical limit to the amount of measurement points. Thermal paints are another established measurement technique, but are toxic and at the same time require dedicated, short-duration tests. Thermal History Paints (THPs) provide an innovative alternative to the aforementioned techniques, but so far only a limited number of tests has been conducted under real engine conditions. THPs are similar in their chemical and physical make-up to conventional thermographic phosphors which have been successfully used in gas turbine applications for on-line temperature detection before. A typical THP comprises of oxide ceramic pigments and a water based binder. The ceramic is synthesized to be amorphous and when heated it crystallizes, permanently changing the microstructure. The ceramic is doped with lanthanide ions to make it phosphorescent. The lanthanide ions act as atomic level sensors and as the structure of the material changes, so do the phosphorescent properties of the material. By measuring the phosphorescence the maximum temperature of exposure can be determined through calibration, enabling post operation measurements at ambient conditions. This paper describes a test in which THP was applied to an impingement-cooled front panel from a combustor of an industrial gas turbine. Since this component sees a wide range of temperatures, it is ideally suited for the testing of the measurement techniques under real engine conditions. The panel was instrumented with a thermocouple and thermal paint was applied to the cold side of the impingement plate. THP was applied to the hot-gas side of this plate for validation against the other measurement techniques and to evaluate its resilience against the reacting hot gas environment. The durability and temperature results of the three different measurement techniques are discussed. The results demonstrate the benefits of THPs as a new temperature profiling technique. It is shown that the THP exhibited greater durability compared to the conventional thermal paint. Furthermore, the new technology provided detailed measurements down to millimeters indicating local temperature variations and global variations over the complete component.

Modeling a Non-Premixed Industrial Gas Turbine Combustor by a Transported PDF Approach With ILDM Chemistry

2007 ◽  
Author(s):  
Sebastian Harder ◽  
Franz Joos
Keyword(s):  
Gas Turbine ◽  
Particle System ◽  
Measurement Techniques ◽  
Combustion Process ◽  
Generic Model ◽  
Numerical Comparison ◽  
Gas Turbine Combustor ◽  
Turbulent Diffusion Flame ◽  
Pdf Methods ◽  
Industrial Gas Turbine

The combustion process in a typical can combustor of an industrial gas turbine is determined by the nature of turbulent flow, the chemical reaction and the interaction with each other. Turbulent non-premixed combustion can be divided into different flame regimes in terms of time- and length scales. A typical non-premixed turbulent diffusion flame in a gas turbine combustor covers all regimes. PDF methods are suitable to describe the entire combustion regime without any limitation to a certain regime. In this paper a hybrid pdf/RANS method is presented. The pdf model is based on the transported composition pdf equation, coupled with a commercial three dimensional CFD solver. A stochastic particle system in a Lagrangian framework is used to solve the pdf equation. The chemistry is described by an ILDM approach. The numerical results have been validated with measurements. The test rig consists of an non-premixed gas turbine can combustor with a typical primary and secondary zone. A main air swirler stabilizes the natural gas/air mixture in the primary zone, followed by a burnout and a mixing zone. The setup is investigated using conventional measurement techniques. Field measurements of compositions and mixture fraction as well as temperature are compared with the pdf/RANS calculations. The benefit of this approach is a realistic prediction of all relevant species. The complete one point statistics of the numerical calculations are used to identify the different combustion regimes from the combustor to the exit. The numerical comparison of pdf-, edm- and flamelet-model shows that the pdf approach can be used to describe a realistic gas turbine combustor. In the past, pdf-methods were applied only on simple generic model flames. The purpose of the presented paper is to demonstrate the application of a transported-pdf approach to a realistic gas turbine combustor.

Heavy Duty Gas Turbine Simulation: Global Performances Estimation and Secondary Air System Modifications

2006 ◽  
Author(s):  
Carlo Carcasci ◽  
Bruno Facchini ◽  
Stefano Gori ◽  
Luca Bozzi ◽  
Stefano Traverso
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Cooling System ◽  
Energy System ◽  
Operating Conditions ◽  
Coupled Analysis ◽  
Ambient Conditions ◽  
Air System ◽  
Secondary Air ◽  
And Performance

This paper reviews a modular-structured program ESMS (Energy System Modular Simulation) for the simulation of air-cooled gas turbines cycles, including the calculation of the secondary air system. The program has been tested for the Ansaldo Energia gas turbine V94.3A, which is one of the more advanced models in the family Vx4.3A with a rated power of 270 MW. V94.3A cooling system has been modeled with SASAC (Secondary Air System Ansaldo Code), the Ansaldo code used to predict the structure of the flow through the internal air system. The objective of the work was to investigate the tuning of the analytical program on the basis of the data from design and performance codes in use at Ansaldo Energy Gas Turbine Department. The results, both at base load over different ambient conditions and in critical off-design operating points (full-speed-no-load and minimum-load), have been compared with APC (Ansaldo Performance Code) and confirmed by field data. The coupled analysis of cycle and cooling network shows interesting evaluations for components life estimation and reliability during off-design operating conditions.

Experimental Investigation on Effusion Liner Geometries for Aero-Engine Combustors: Evaluation of Global Acoustic Parameters

2012 ◽  
Author(s):  
A. Andreini ◽  
B. Facchini ◽  
L. Ferrari ◽  
G. Lenzi ◽  
F. Simonetti ◽  
...  
Keyword(s):  
Cooling System ◽  
Fluid Dynamic ◽  
Pressure Fluctuations ◽  
Main Concern ◽  
Dynamic Features ◽  
Ambient Conditions ◽  
Test Rig ◽  
Acoustic Parameters ◽  
Field Range ◽  
Aero Engines

In new generation aero-engines based on the innovative lean combustion technology, thermoacoustic instabilities are one of the most important issues and their prevention and reduction are challenging goals. To achieve these targets, the use of multi-perforated liners, that have to primarily provide an efficient liner cooling, is very attractive because they are efficient passive dampers of pressure fluctuations, especially with bias flow. The design of multi-perforated liners for both thermal and acoustic purposes can be accomplished by selecting liner parameters, such as hole diameter, pattern and inclination, main and bias Mach numbers, fulfilling both requirements; this procedure requires to assess the effect of both geometrical and fluid-dynamic features. Thus, a specific research project is ongoing on the acoustic and thermal experimental characterization of selected multi-perforated liner geometries. In this paper, the complete experimental campaign on the acoustic behavior of the aforementioned liners has been carried out in the planar wave field range, that is of main concern in aero-engines. For this purpose, an innovative modular test rig has been designed to characterize test cases at ambient conditions, changing bias and main flows up to operating engine conditions. Liner geometries account for 3 different hole diameters, 5 different patterns and 2 hole inclinations, ranging within typical cooling system values; tests were performed with the two-source multi-microphone technique to evaluate global acoustic parameters independently from test rig boundary conditions. The acoustic performances of liners are discussed in terms of the energy dissipation coefficient.

Vibration Measurement Techniques on an Industrial Gas Turbine Rotor Train

1998 ◽  
Author(s):  
Stefan S. Florjancic ◽  
Wes Franklin ◽  
Noel Lively
Keyword(s):  
Gas Turbine ◽  
Support System ◽  
Data Reduction ◽  
Dynamic Properties ◽  
Measurement Techniques ◽  
Turbine Rotor ◽  
Vibration Measurement ◽  
Analytical Models ◽  
System Parameters ◽  
Industrial Gas Turbine

The rotordynamic behavior of an industrial gas turbine rotor train was assessed on site, and the sensitivity to unbalance was quantified. An outline of the measurement procedure is given. Differential data reduction with test unbalances was undertaken to minimize the influence of measurement uncertainty. A test unbalance was installed for one run and then shifted by 180° for the consecutive run. With differential data, the effective dynamic properties of the rotor - support - system can be estimated more accurately. A rotordynamic model was used to identify the support system parameters based on measured data. For the analysis, the anisotropic, elliptical vibration orbits were decomposed into two counter-rotating circular orbits, and the support system parameters identified match the originally predicted values well. The methods of differential data reduction, rotor train mode shape presentation, elliptical orbit decomposition, and the link of measurement to analytical models with parameter definition are described. Examples from on-site measurements are included for illustration.

Development of an Improved Desiccant-Based Evaporative Cooling System for Gas Turbines

2008 ◽  
Author(s):  
Amir Abbas Zadpoor ◽  
Ali Asadi Nikooyan
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Cooling System ◽  
Evaporative Cooling ◽  
Climatic Conditions ◽  
Cooling Systems ◽  
Actual Performance ◽  
Evaporative Cooling System ◽  
Industrial Gas Turbine ◽  
Gas Turbine Cycle

The evaporative inlet cooling systems used for inlet cooling of gas turbines during hot summers do not work well in humid areas. However, desiccant wheels can be used to dehumidify the air before passing it trough the evaporative cooler. Since the desiccant wheels work adiabatically, the resulting air is hotter than the air introduced to the wheel and an evaporative cooling system is used to cool down the dehumidified air. Combined direct and indirect evaporative coolers have been already used to investigate the effects of dehumidification on the effectiveness of the evaporation cooling systems. It is shown that a single desiccant wheel does not offer much higher effectiveness compared to the multiple-stage evaporative systems. In this paper, an improved version of the desiccant inlet cooling system is presented. Additional dehumidification and indirect evaporative cooling stages are added to increase the effectiveness of the inlet cooling. A typical gas turbine cycle along with an industrial gas turbine with actual performance curves are used to simulate the thermal cycle in presence of the different inlet cooling systems. The simulations are carried out for three different climatic conditions. The improved and original desiccant-based systems are compared and it is shown that the added stages substantially improve the effectiveness of the desiccant-based inlet cooling.

Validation of Surface Temperature Measurements on a Combustor Liner Under Full-Load Conditions Using a Novel Thermal History Paint

2016 ◽  
Vol 139 (4) ◽  
Author(s):  
Robert Krewinkel ◽  
Jens Färber ◽  
Ulrich Orth ◽  
Dirk Frank ◽  
Martin Lauer ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal History ◽  
New Technology ◽  
Measurement Techniques ◽  
Combustion Process ◽  
Lanthanide Ions ◽  
Maximum Temperature ◽  
Oxide Ceramic ◽  
Ambient Conditions ◽  
Hot Gas

The ever-increasing requirements on gas turbine efficiency and the simultaneous demand for reduced emissions, necessitate much more accurate calculations of the combustion process and combustor wall temperatures. Thermal history paints (THPs) is an innovative alternative to the established measurement techniques, but so far only a limited number of tests have been conducted under real engine conditions. A typical THP comprises oxide ceramic pigments and a water-based binder. The ceramic is synthesized to be amorphous and when heated it crystallizes, permanently changing the microstructure. The ceramic is doped with lanthanide ions to make it phosphorescent and as the structure of the material changes, so do the phosphorescent properties of the material. By measuring the phosphorescence, the maximum temperature of exposure can be determined, enabling postoperation measurements at ambient conditions. This paper describes a test in which THP was applied to an impingement-cooled front panel from a combustor of an industrial gas turbine. The panel was instrumented with a thermocouple (TC), and thermal paint was applied to the cold side of the impingement plate. The THP was applied to the hot-gas side of this plate for validation against the other measurement techniques and to evaluate its resilience against the reacting hot gas environment. The durability and temperature results of the three different measurement techniques are discussed. It is shown that the THP exhibited greater durability compared to the conventional thermal paint. Furthermore, the new technology provided detailed measurements indicating local temperature variations and global variations over the complete component.

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