The Design and Testing of Air-Cooled Blading for an Industrial Gas Turbine

1983 ◽  
Vol 105 (3) ◽  
pp. 466-473 ◽  
Author(s):  
J. M. Hannis ◽  
M. K. D. Smith
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Turbine Stage ◽  
High Pressure Turbine ◽  
Transient Conditions ◽  
Blade Cooling ◽  
Advance Information ◽  
Industrial Gas Turbine ◽  
Design And Testing ◽  
A Current

The design and testing of a cooled high-pressure turbine stage to provide advance information for the Ruston Tornado 6MW industrial gas turbine is described. The cooled stage was designed to replace an existing uncooled stage in a current Ruston gas turbine to allow development testing under actual engine conditions. The instrumentation techniques used on the development engine, including infrared pyrometry, are discussed and results of the tests covering nozzle vane and rotor blade cooling under steady-state and transient conditions and engine performance are presented and compared with the design predictions.

The Design and Test of Air-Cooled Blading for an Industrial Gas Turbine

1982 ◽  
Author(s):  
J. M. Hannis ◽  
M. K. D. Smith
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Turbine Stage ◽  
High Pressure Turbine ◽  
Transient Conditions ◽  
Blade Cooling ◽  
Advance Information ◽  
Industrial Gas Turbine ◽  
Design And Testing ◽  
A Current

The design and testing of a cooled high pressure turbine stage to provide advance information for the Ruston Tornado 6MW industrial gas turbine is described. The cooled stage was designed to replace an existing uncooled stage in a current Ruston gas turbine to allow development testing under actual engine conditions. The instrumentation techniques used on the development engine, including infrared pyrometry, are discussed and results of the tests covering nozzle vane and rotor blade cooling under steady state and transient conditions and engine performance are presented and compared with the design predictions.

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 Analysis, Design, and Testing of a Low Profile Deflection Pad™ Thrust Bearing in an Industrial Gas Turbine

1994 ◽  
Author(s):  
Dilip Jain ◽  
Fouad Zeidan ◽  
Michael Wittmeyer
Keyword(s):  
Gas Turbine ◽  
Thrust Bearing ◽  
Element Analysis ◽  
Low Profile ◽  
Wide Range ◽  
Analysis Design ◽  
Thrust Pad ◽  
Industrial Gas Turbine ◽  
Design And Testing ◽  
Thrust Load

This paper describes the analysis, design, and testing of a low profile thrust bearing in a DR 990 industrial gas turbine. High unit loads and speeds, and the need to maintain low frictional power loss presented many challenges. The thrust pad design utilizes a flexure pivot, which allow near optimum performance for a wide range of speeds and loads in comparison to a fixed geometry taper land design. The use of high conductivity material for the thrust pads and directed lubrication allowed operation at lower temperatures. Finite element analysis was used to model the pad structure and pivot support. This analysis was confirmed by measuring the pad tilt using an eddy current probe. The test was conducted in a controlled thrust rig allowing accurate application and measurement of the thrust load. Precision manufacturing of the spherical seat and the application of a proprietary coating allowed better aligning capability under load. The bearing was tested in an engine at a range of speeds and loading conditions. The results are presented and compared with the existing fixed geometry bearing design. The bearing is currently running in an engine in the field and has accumulated 2,400 hours of operation with no forced outages.

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.

Impact of Swirling Entropy Waves on a High Pressure Turbine

2021 ◽  
pp. 1-14
Author(s):  
Andrea Notaristefano ◽  
Paolo Gaetani
Keyword(s):  
Secondary Flows ◽  
Temperature Perturbation ◽  
Turbine Stage ◽  
High Pressure Turbine ◽  
Blade Cooling ◽  
Unsteady Aerodynamic ◽  
Experimental Campaign ◽  
Severe Reduction ◽  
Inlet Conditions ◽  
Noise Production

Abstract The harsh environment exiting modern gas turbine combustion chamber is characterized by vorticity and temperature perturbations, the latter commonly referred as entropy waves. The interaction of these unsteadiness with the first turbine stage causes non-negligible effects on the aerodynamic performance, blade cooling and noise production. The first of these drawbacks is addressed in this paper by means of an experimental campaign: entropy waves and swirl profile are injected upstream of an axial turbine stage through a novel combustor simulator. Two injection positions and different inlet conditions are considered. Steady and unsteady experimental measurements are carried out through the stage to address the combustor-turbine interaction characterizing the injected disturbance, the nozzle and rotor outlet aerothermal field. The experimental outcomes show a severe reduction of the temperature perturbation already at stator outlet. The generated swirl profile influences significantly the aerodynamic, as it interacts with the stator and rotor secondary flows and wakes. Furthermore, the clocking position changes the region most affected by the disturbance, showing a potential modifying the injection position to minimize the entropy wave and swirl profile impact on the stage. Finally, this work shows that in order to proficiently study entropy waves, the unsteady aerodynamic flow field stator downstream has to be addressed.

Application of an Optical Pyrometer to Newly Developed Industrial Gas Turbine

2012 ◽  
Author(s):  
Tomoki Taniguchi ◽  
Ryozo Tanaka ◽  
Yuji Shinoda ◽  
Masanori Ryu ◽  
Norbert Moritz ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Evaluation Process ◽  
Optical Pyrometer ◽  
Blade Surface ◽  
High Pressure Turbine ◽  
Low Pressure Turbine ◽  
Lower Temperature ◽  
Measurement And Evaluation ◽  
Industrial Gas Turbine ◽  
Engine Condition

Kawasaki Heavy Industries, Ltd (KHI) have developed a new industrial gas turbine, L30A. The turbine section composed of two-stage high pressure turbine and three-stage low pressure turbine. In the development period, a commercial pyrometer system was employed to measure blade temperatures under real engine condition. The pyrometer was equipped with an updated detector module and could measure lower temperature compared to the conventional one. Thus it could be used to measure all stages of blades with one pyrometer. The validity of the result was demonstrated by comparing the result with data obtained with other conventional techniques. With the pyrometer system the temperature distribution on the blade surface was easily available and cooling capabilities of blades were evaluated without taking much time. This paper describes the detail of measurement and evaluation process.

Impact of Swirling Entropy Waves on a High Pressure Turbine

2021 ◽  
Author(s):  
Andrea Notaristefano ◽  
Paolo Gaetani
Keyword(s):  
Secondary Flows ◽  
Temperature Perturbation ◽  
Turbine Stage ◽  
High Pressure Turbine ◽  
Blade Cooling ◽  
Unsteady Aerodynamic ◽  
Experimental Campaign ◽  
Severe Reduction ◽  
Inlet Conditions ◽  
Noise Production

Abstract The harsh environment exiting modern gas turbine combustion chamber is characterized by vorticity and temperature perturbations, the latter commonly referred as entropy waves. The interaction of these unsteadiness with the first turbine stage causes non-negligible effects on the aerodynamic performance, blade cooling and noise production. The first of these drawbacks is addressed in this paper by means of an experimental campaign: entropy waves and swirl profile are injected upstream of an axial turbine stage through a novel combustor simulator. Two injection positions and different inlet conditions are considered. Steady and unsteady experimental measurements are carried out through the stage to address the combustor-turbine interaction characterizing the injected disturbance, the nozzle and rotor outlet aerothermal field. The experimental outcomes show a severe reduction of the temperature perturbation already at stator outlet. The generated swirl profile influences significantly the aerodynamic, as it interacts with the stator and rotor secondary flows and wakes. Furthermore, the clocking position changes the region most affected by the disturbance, showing a potential modifying the injection position to minimize the entropy wave and swirl profile impact on the stage. Finally, this work shows that in order to proficiently study entropy waves, the unsteady aerodynamic flow field stator downstream has to be addressed.

Effects of Anti-Icing System Operation on Gas Turbine Performance and Monitoring

2001 ◽  
Author(s):  
K. Mathioudakis ◽  
A. Tsalavoutas
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Performance Model ◽  
False Alarms ◽  
System Operation ◽  
Diagnostic Ability ◽  
Engine Model ◽  
On Line ◽  
Industrial Gas Turbine ◽  
Engine Condition

The effect of operation of compressor bleed anti-icing on the performance of an industrial gas turbine is analysed. The effect of putting this system in operation is first qualitatively discussed, while the changes on various performance parameters are derived by using a computer engine performance model. The main point of the paper is the study of the effect of anti-icing system operation on parameters used for engine condition monitoring. It is shown that operation of the anti-icing system causes an apparent modification of such parameters, which may reduce the diagnostic ability of an on-line monitoring system and produce false alarms. It is shown that by incorporating the effect of anti-icing system operation into a diagnostic engine model, such problems can be avoided and the diagnostic ability of the system is not influenced by anti-icing activation. The analysis presented is substantiated through experimental data from a twin shaft gas turbine operating in the field.

Integrated Turbine Design Using Evolutionary Strategies to Minimize Fuel Burn

2019 ◽  
Author(s):  
Roy J. Hartfield ◽  
Noel Cervantes
Keyword(s):  
Engine Performance ◽  
Evolutionary Strategies ◽  
Simulation Tool ◽  
Turbine Stage ◽  
Optimization Scheme ◽  
High Pressure Turbine ◽  
Fuel Burn ◽  
Blade Optimization ◽  
Blade Section ◽  
Turbine Design

Abstract This paper describes the use of an Evolutionary Strategies optimization scheme to optimize the rotor blade section of a high-pressure turbine stage for minimum fuel burn. The goal is to determine if the blade optimization can result in an overall engine performance upgrade by minimizing the fuel required. To ascertain the overall effect of turbine improvement on fuel burn specifically, the remainder of the engine is modeled using the Numerical Propulsion System Simulation tool. The result is a 0.082% improvement in fuel burn. The paper details the resulting configuration and identifies some strategies which are emerging for improving turbine design.

Application of Adaptive GPA to an Industrial Gas Turbine Using Field Data

2019 ◽  
Author(s):  
Ericcson Ramadhan ◽  
Yi-Guang Li ◽  
Deplian Maherdianta
Keyword(s):  
Performance Management ◽  
Gas Turbine ◽  
Performance Status ◽  
Engine Performance ◽  
Health Condition ◽  
Diagnostic Process ◽  
Component Level ◽  
Turbine Component ◽  
The Difference ◽  
Industrial Gas Turbine

Abstract The gas turbine inspection activities provided by the manufacturers and user maintenance scheme may be different from each other. To accommodate the difference, performing engine diagnostic as a condition-based monitoring technique is necessary to support Asset Performance Management (APM) adopted by the gas turbine users to improve the scheme. This paper provides an application of a novel Adaptive Gas Path Analysis (Adaptive GPA) to diagnose performance and health condition of a GE industrial gas turbine MS5001PA operated by PT Pupuk Kaltim (PKT). In the application, an engine thermodynamic model is constructed, adapted, and validated on the actual engine performance based on its gas path measurements. To estimate the health condition from the degraded engine data, two steps are applied in the Adaptive GPA diagnostic process. The first step is the estimation of degraded engine performance status and the second step is the prediction of engine health status at the gas turbine component level. Adaptive GPA results show that satisfactory predictions of the engine degradation have been achieved. In other words, the compressor has been predicted 5.56% degradation in flow capacity and 4.26% degradation in efficiency respectively, which is an indication of compressor fouling. Combining the diagnostic results, manufacturer’s recommendations, and user maintenance strategy, it is relatively safe and allowable to increase the maintenance inspection interval from 12,000 to 16,000 hours. Therefore, the adaptive GPA is proven to be beneficial to support condition-based maintenance decisions.

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