Effect of gas-turbine green discoloring and drying processingmethods on herbal quality of tetraploid Lonicerae Japonicae Flos

2012 ◽  
Keyword(s):  
Gas Turbine ◽  
Herbal Quality

scholarly journals Gas Turbine Train Development in France

1975 ◽  
Author(s):  
M. R. Garde
Keyword(s):  
Diesel Engine ◽  
Gas Turbine ◽  
High Speed ◽  
Rolling Stock ◽  
Lightweight Construction ◽  
The Future ◽  
Railway Traction ◽  
Aircraft Type ◽  
Very High

This paper presents a discussion on aircraft type gas-turbine train development. For railway traction purposes, the turbo-engines used on aircraft would improve the quality of the services provided in the electrified lines. The gas turbine should insure high speed and satisfactory acceleration. It would enable relatively lightweight construction to be carried out and run at a higher speed than trains on non-electrified lines. The gas turbine will not completely replace the diesel engine, but it will enable rolling stock to be constructed for which the diesel is unsuitable, especially in the case of high-speed, lightweight trainsets and, in the future, very high-powered units.

Build Direction Effects on Additively Manufactured Channels

2015 ◽  
Author(s):  
Jacob C. Snyder ◽  
Curtis K. Stimpson ◽  
Karen A. Thole ◽  
Dominic Mongillo
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Pressure Loss ◽  
Small Scale ◽  
Turbine Cooling ◽  
Gas Turbine Cooling ◽  
Gas Turbine Heat Transfer ◽  
Manufacturing Techniques ◽  
Traditional Manufacturing

With the advances of Direct Metal Laser Sintering (DMLS), also generically referred to as additive manufacturing, novel geometric features of internal channels for gas turbine cooling can be achieved beyond those features using traditional manufacturing techniques. There are many variables, however, in the DMLS process that affect the final quality of the part. Of most interest to gas turbine heat transfer designers are the roughness levels and tolerance levels that can be held for the internal channels. This study investigates the effect of DMLS build direction and channel shape on the pressure loss and heat transfer measurements of small scale channels. Results indicate that differences in pressure loss occur between the test cases with differing channel shapes and build directions, while little change is measured in heat transfer performance.

Adaptive Myriad Filter for Improved Gas Turbine Condition Monitoring Using Transient Data

2005 ◽  
Vol 127 (2) ◽  
pp. 329-339 ◽  
Author(s):  
Vellore P. Surender ◽  
Ranjan Ganguli
Keyword(s):  
Noise Reduction ◽  
Gas Turbine ◽  
Health Monitoring ◽  
Moving Average ◽  
Acceleration Process ◽  
Outlet Temperature ◽  
Outlier Removal ◽  
Moving Average Filter ◽  
Average Filter

The removal of noise and outliers from measurement signals is a major problem in jet engine health monitoring. In this study, we look at the myriad filter as a substitute for the moving average filter that is widely used in the gas turbine industry. The three ideal test signals used in this study are the step signal that simulates a single fault in the gas turbine, while ramp and quadratic signals simulate long term deterioration. Results show that the myriad filter performs better in noise reduction and outlier removal when compared to the moving average filter. Further, an adaptive weighted myriad filter algorithm that adapts to the quality of incoming data is studied. The filters are demonstrated on simulated clean and deteriorated engine data obtained from an acceleration process from idle to maximum thrust condition. This data was obtained from published literature and was simulated using a transient performance prediction code. The deteriorated engine had single component faults in the low pressure turbine and intermediate pressure compressor. The signals are obtained from T2 (IPC total outlet temperature) and T6 (LPT total outlet temperature) engine sensors with their nonrepeatability values that were used as noise levels. The weighted myriad filter shows even greater noise reduction and outlier removal when compared to the sample myriad and a FIR filter in the gas turbine diagnosis. Adaptive filters such as those considered in this study are also useful for online health monitoring, as they can adapt to changes in quality of incoming data.

“SMART ENGINE”: A Gas Turbine Fault Diagnostics and Life Management Tool

2006 ◽  
Author(s):  
Suresh Sampath ◽  
Luca Marinai ◽  
Riti Singh ◽  
Ankush Gulati
Keyword(s):  
Life Cycle ◽  
Performance Management ◽  
Gas Turbine ◽  
Field Experience ◽  
Management Tool ◽  
Life Cycle Costs ◽  
Fault Diagnostics ◽  
Turbine Performance ◽  
Salient Features

Given the maturity of the gas turbine user industry, and the quality of the original equipment manufactured, the field experience of these machines has been broadly very good. Nonetheless, there can be difficulties in managing availability and reliability, and the costs of unscheduled shut downs can be extremely large. Advanced gas turbine performance management offers opportunities in improving availability, reliability and productivity, driving down life cycle costs as well as adding to safety and compliance. This paper describes in detail the development of an engine fault diagnostics tool by the authors. The authors focus on structure, functionality as well as possible benefits of its use. The first part describes the structure and various methodologies adopted in the development of the system and the second part of the work describes the system and its salient features. The primary goal at this point of time was to test the utility, functionality and robustness of the presented tool, interesting and relevant results are obtained. Due to space limitations we restrict ourselves to discussing the system and not go into the details of actual simulation runs.

scholarly journals POSSIBILITIES OF APPLICATION OF THE METHODOLOGY FOR DETERMINING RATINGS OF A GAS TURBINE ENGINE TO IMPROVETHE QUALITY OF EQUIPMENT DIAGNOSTIC

2018 ◽  
pp. 83-87
Author(s):  
A. I. Mikhaylenko
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Oil Field ◽  
Design Parameters ◽  
Flow Section ◽  
Turbine Engine ◽  
Current State ◽  
Entire Flow ◽  
Methodological Approaches

The article deals with theoretical and methodological approaches and practical approaches to improve the quality of gas turbine engine diagnostics. The author presents the main results of development of the calculating method for additional ratings in the entire flow section of the gas turbine engine GTE-6,3/MS which is used by LLC «RN-Uvatneftegaz» at the Tyamkinskoye oil field of Uvat district of Tyumen region. The conclusion is drawn that an expanded series of design parameters of a gas turbine engine makes it possible to improve the quality, reliability and depth of diagnostics of both the current state of equipment and after major overhaul.

scholarly journals Surface layer quality in compressor titanium blades at multiaxes deep grinding

2017 ◽  
Vol 2 (12) ◽  
pp. 15-19
Author(s):  
В. Полетаев ◽  
V. Poletaev ◽  
Е. Цветков ◽  
E. Tsvetko
Keyword(s):  
Titanium Alloy ◽  
Surface Layer ◽  
Residual Stresses ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Blade Surface ◽  
A Value ◽  
Surface Layer Quality

The investigation results of technological conditions impact at multiaxes deep grinding upon quality of titanium alloy blade surface layer in the compressors of gas turbine engines (GTE) are presented. The grinding mode impact upon a surface and a value of residual stresses in a surface layer of blades is defined and also conditions for defect occurrence as burns on blade surfaces under machining are detected.

scholarly journals Surface Roughness Prediction and Minimization in 5-Axis Milling Operations of Gas Turbine Blades

2021 ◽  
Author(s):  
Arameh Eyvazian ◽  
Farayi Musharavati ◽  
Afrasyab Khan ◽  
Mohsen Soori ◽  
Tamer A. Sebaey ◽  
...  
Keyword(s):  
Surface Roughness ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Machining Process ◽  
Machining Parameters ◽  
Gas Turbine Blades ◽  
Virtual Machining ◽  
Machined Parts ◽  
Machining System

Abstract To enhance the quality of machined parts, virtual machining systems are presented in this study. In the turbine blades, the minimization of the surface roughness of the blades can decrease the Reynolds number to decrease the loss of energy in power generation. Due to difficulties of polishing process in minimizing the surface roughness of machined blades, the optimized machining parameters for minimizing the surface roughness is an effective solution for the problem. In this study, a virtual machining system is developed to predict and minimize the surface roughness in 5-Axis machining operations of gas turbine blades. To minimize the surface roughness, the machining parameters were optimized by the Genetic algorithm. To validate the developed system, the turbine blades were machined using a 5-Axis CNC machine tool and the machined blades were measured using the CMM machine to obtain the surface roughness of machined parts. So, a 41.29% reduction in the measured surface roughness and a 42.09% reduction in the predicted surface roughness are obtained using the optimized machining parameters. The developed virtual machining system can be applied in the machining process of turbine blades to enhance the surface quality of machined blades and thus improve the efficiency of gas turbines.

The Design and Operation of the Parsons Experimental Gas Turbine

1949 ◽  
Vol 160 (1) ◽  
pp. 454-471 ◽  
Author(s):  
A. T. Bowden ◽  
J. L. Jefferson
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
Axial Flow ◽  
Residual Oil ◽  
Flow Compressor ◽  
Oil Fuel ◽  
Industrial Gas Turbine ◽  
Turbine Blading ◽  
Principal Design

The paper describes the principal design features of the Parsons 500 h.p. experimental industrial gas turbine, and records the operating results obtained in running the plant since December 1945. A section is devoted to some of the preliminary investigations on the compressor, combustion, and heat exchanger components, undertaken prior to the building of the unit. Some of the early work on the axial-flow compressor is, it is considered, of particular interest. One of the most important questions remaining to be answered in gas-turbine operation, is the quality of the oil fuel which can be regularly and reliably burned. Details are included in the paper of operating results using a residual oil fuel. Considerable trouble was experienced as a result of the building up of deposits in the turbine blading; these deposits are analysed and compared with the parent oil-fuel analysis, and photographs of spindle and cylinder blading show the nature of the build-up.

Efficient structural analysis of gas turbine blades

2018 ◽  
Vol 90 (9) ◽  
pp. 1305-1316
Author(s):  
Timo Rogge ◽  
Ricarda Berger ◽  
Linus Pohle ◽  
Raimund Rolfes ◽  
Jörg Wallaschek
Keyword(s):  
Structural Analysis ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Turbine Blades ◽  
Element Model ◽  
Gas Turbine Blade ◽  
Quality Of Results ◽  
Content Type ◽  
Gas Turbine Blades

Purpose The purpose of this study a fast procedure for the structural analysis of gas turbine blades in aircraft engines. In this connection, investigations on the behavior of gas turbine blades concentrate on the analysis and evaluation of starting dynamics and fatigue strength. Besides, the influence of structural mistuning on the vibration characteristics of the single blade is analyzed and discussed. Design/methodology/approach A basic computation cycle is generated from a flight profile to describe the operating history of the gas turbine blade properly. Within an approximation approach for high-frequency vibrations, maximum vibration amplitudes are computed by superposition of stationary frequency responses by means of weighting functions. In addition, a two-way coupling approach determines the influence of structural mistuning on the vibration of a single blade. Fatigue strength of gas turbine blades is analyzed with a semi-analytical approach. The progressive damage analysis is based on MINER’s damage accumulation assuming a quasi-stable behavior of the structure. Findings The application to a gas turbine blade shows the computational capabilities of the approach presented. Structural characteristics are obtained by robust and stable computations using a detailed finite element model considering different load conditions. A high quality of results is realized while reducing the numerical costs significantly. Research limitations/implications The method used for analyzing the starting dynamics is based on the assumption of a quasi-static state. For structures with a sufficiently high stiffness, such as the gas turbine blades in the present work, this procedure is justified. The fatigue damage approach relies on the existence of a quasi-stable cyclic stress condition, which in general occurs for isotropic materials, as is the case for gas turbine blades. Practical implications Owing to the use of efficient analysis methods, a fast evaluation of the gas turbine blade within a stochastic analysis is feasible. Originality/value The fast numerical methods and the use of the full finite element model enable performing a structural analysis of any blade structure with a high quality of results.

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