Study of the Performance of Gas Turbine

Analyzing the Factors Affecting the Performance of Gas Turbines

by Mohith N. Kumar*, Dr. K. V. Sreenivas Rao,

- Published in Journal of Advances and Scholarly Researches in Allied Education, E-ISSN: 2230-7540

Volume 17, Issue No. 1, Apr 2020, Pages 9 - 16 (8)

Published by: Ignited Minds Journals


ABSTRACT

In this article we study about performance of gas turbine. The industrial gas turbines demonstrate output results that rely distinctly on atmospheric and operational conditions. Not only site height, air temperature, affects them. And relative temperature, but also the speed of the machinery being powered, the fuel and the load conditions. Applying gas turbines correctly needs analysis of certain variables. This guide describes certain features centered on the engine compressor output. Part of the combustor and generator, and other regulation methods. It introduces simple concepts which help to understand the energy flow between the components. Therefore. Methods are implemented which allow data to be used for trend and comparison purposes. The effect of component deterioration on the efficiency of individual components and overall engine output was addressed, along with approaches to reduce the influence of deterioration.

KEYWORD

gas turbine, performance, industrial, atmospheric conditions, operational conditions, site height, air temperature, relative temperature, speed, fuel, load conditions, engine compressor output, combustor, generator, regulation methods, energy flow, component deterioration, efficiency, engine output, approaches

INTRODUCTION

A gas turbine, also known as a combustion turbine, is a rotary engine that extracts energy from a flow of hot gas produced by the combustion of gas or fuel oil in an air compressor system. This has an upstream air compressor mechanically connected with radial or axial flow to a downstream generator, and a combustion chamber in addition. It produces energy when compressed air is combined with gasoline and ignited in the combustion chamber (combustor). Energy is extracted from the gas turbine in the form of shaft electricity, and this is used to drive electric generators and other machines. Gas turbines are being increasingly used to produce electricity for a number of applications around the globe. The performance of gas turbines is determined by the modulus output and turbine inlet temperature. Gas turbines have been in use for several years for many applications in aerospace and manufacturing. We are used effectively for driving both aircraft and industrial applications. Industrial Air Turbines include either a diesel-powered piston-type gas turbine or an air-powered piston, as well as an air turbine, which provides heat for both the air compressor as well as load (single shaft engine) with one shaft.. Nevertheless, the performance and output characteristics of a gas turbine derive from a dynamic interaction of various turboma-chines and a combustion device. The topics discussed will improve understanding of the principles expressed in gas turbine efficiency maps or, in other terms, clarify the principles of operation of a gas turbine in automotive purposes.

PERFORMANCE OF GAS TURBINE

The gas turbine engine is durable, has a low weight, and various fuels can be used. This makes gas turbine ideal for many applications in the aerospace and industrial fields. The economy of generating electricity using gas turbine engines depends in that order on the cost of fuel, operating efficiency, maintenance cost, and first cost. To order to reduce the fuel expense, the engine's performance will be maximized. To addition, a slight increase in output may be viewed as a large sum of money because fuel savings are applied over the engine's lifespan. At the other side, if the network frequency decreases, the operating expense and first expense per unit capacity will be the. Increasing net-specific work ensures an a smaller-size plant will yield the same electricity. The plant scale can be viewed as a repair and first expense factor. Therefore, in the plant optimization process maximum efficiency and maximum network accuracy are sought. In turn, low turbine inlet temperature (TIT) engine configuration and higher compressor pressure ratio reduces all repair and initial costs. This may however decrease efficiency as well as net specific work. Therefore, it may require a criterion for the inefficiency and net real function would be favored over reduction in the temperature inlet and compressor pressure ratio of turbines. It should be remembered that the metallurgical restrictions place a cap at TIT. Considerations of the turbo device also provided a reasonable specific pressure ratio for defined rotating rpm. Several improvements have been suggested on the basic gas turbine engine to boost its output within the TIT and compressor pressure range permitted. One example is the gas turbine engine which employs intercooling, recovery and heating. The motor can be made of two spools mounted on the low-pressure spool with free control generator. This free control turbine can be mounted in parallel or in series configurations. The percentage improvements in the output parameters of the modified cycle were tested over the basic cycle and it was observed that the modified engine cycles with Both thermal productivity and specific fuel efficiency systems better than normal unconventional components. An isothermal power replacement was researched into a regenerative gas turbine motor running on Brayton cycle system. Via a converging conduit, the temperature during the heat addition is maintained steady, resulting in an improvement in Mach number due to energy saving. The findings indicate that this engine offers the strongest efficiency and displays the highest cycle efficiencies when built according to the optimum power density setting. The limit on the Mach number exit from the isothermal combustor, however, is a major challenge and restricts performance improvement. In order to increase the output and unique strength of the engine, combustion was suggested to be pursued intentionally within the turbine. Ground-based gas turbine engines were tested for power production, with findings suggesting much greater efficiency improvements relative to traditional engines. The difficulties raised by such adjustment were checked to measure them against the gains. To choose the optimal design point the plant's statistical model will be as precise as possible. Some modeling errors may result in more overall cost to a system. It is particularly essential for complicated designs proposed to enhance the plant's efficiency. Different heat variations from component to component and often from inlet to outlet of the same component arise in these complicated engines. The impact of different Heat fluctuations are recognized as teaching statuses in function of temperature and air to fuel ratios, particularly when an ideal plant design level is calculated by a parametric analysis. A steady volume of natural heat has also been achieved for pure air (all products outside the as function of the temperature. In fact, the cooling flow needed for the two turbines not only adds complexity to the power plant but also affects output. The usage of cooling air creates both reliability and network unique output losses. However, in the analysis the cooling flow is usually neglected, and this creates variance in the optimum design stage. In order to operate at the maximum TIT and obtain practical optimum efficiency, the impact of turbine cooling flow should be regarded in the study According to the expertise of the author, not all such modifications were measured together using a complete and reliable engine model. Various changes in the gas turbine engine will be quantified using the engine's maximum practical configuration at various TIT and compressor pressure level. This attempts to measure the performance enhancements attributable to any practicable alteration of the engine's gas turbine at various TIT and compressor pressure ratios inside reasonable ranges utilizing the engine's maximum functional numerical model. It also assesses the impact on engine simulation accuracy of overlooking differences in specific heat and turbine cooling flow. That was specifically essential for determining the power plant's realistic optimum operating stage. It also assists the manufacturer in calculating the percentage increase because of improvements toward the added uncertainties and original and repair costs. The paper begins with the implementation of the complete numerical model of the engine. The model takes into consideration the performance and the decrease in pressure of specific components at the cooler, combustion device and heat exchanger. The performance of the heat exchanger and the intercooler is both accountable. The study involves actual heat and turbine cooling flow measurements at any stage.

PERFORMANCE TEST CODE ON GAS TURBINE

The aim of the code is to describe the test to evaluate the gas turbine's power production and thermal efficiency while running under the test conditions, and to modify such test results according to normal or defined operation and control conditions. Procedures are specified for performing the test, measuring the tests, and making the corrections. Such codes require the testing of gaseous or liquid fuel (or solid fuels which are converted before the entry of a gas turbine into a liquid or gas) gas turbine. It involves evaluating gas turbines with water or steam injection for pollution control and/or

be arranged for all relevant stakeholders as to how the study should be done and an ambiguity review should be carried out before the study. Overall test instability can vary due to variations in the characteristics of the source, used power, and powered machinery. The code establishes a limit for the uncertainty of each necessary unit of measure; the resulting uncertainty is then measured according to the procedures specified in the code and by ASME PTC 19.

PERFORMANCE ANALYSIS OF GAS TURBINE POWER PLANT

The performance of gas turbines is analytically limited by changes in temperature, especially in hot and rainy regions such as Sub-Sahara Africa. Particularly in the hot season, the changes in inlet air temperature are more apparent, and this triggers a major decrease in gas turbine power production. It happens because the power consumption is inversely proportional to the atmospheric temperature, and since the compressor draws high real volume of air. The gas turbine efficiency and power output changes depending on the ambient conditions. The resulting amount of these disparities has a significant impact on electricity generation, fuel consumption and plant revenues. The impact of temperature is prevailing; the production of work rises by around 10% per 56oC turbine temperature rise and decreases productivity by about 1.5%. The overall efficiency of the gas turbine cycle is largely dependent on the compressor pressure ratio. A gas turbine power plant 's output review is essentially oriented to evaluating the plant 's energy quality. The energy production of a plant has significant economic importance, as the high temperature heat supply reflects the electricity to be produced and the net energy performance reflects the gain for the produced oil. In general, gas turbine running at high turbine inlet temperatures would result in poorer output and decreased capacity. Better gas turbine performance means the low power production. According to the performance and efficiency of gas turbines is a clear feature of ambient air temperature. The gas turbine is 1 percent lower than ISO-rated, with 1.47MW of gross power consumption per 1 ° C change in the ambient temperature. Simultaneously, the actual heat intake rises by a rate between 1.5% and 4%. The atmospheric conditions ISO scores are: air temperature, 15oC, atmospheric density, 1bar (100.16kPa), and 60 per cent relative humidity. Output of a 23.7 MW gas turbine plant running at 30 ° C to 45 OC ambient temperature. If the gas turbine generator is provided with cold air at the inlet, the total power production is increased by 11 per cent. At 30oC ambient temperature, net power production rises by 11 per cent in ISO-rated settings, followed ISO to 30oC would contribute to a 10 percent decrease in net power output. The drop in power production can be much greater for gas turbine with smaller size. He also claimed that a 1oC change in air temperature resulted in a 1 percent decrease in the rated efficiency of the gas turbine. Estimated that the maximum power consumption can be improved by as much as 11.3 percent when the ambient temperature decreases from 34.2oC to ISO-rated level. He also found out that an improvement of 1oC in ambient air temperature contributed to power consumption and reduced performance by 0.74%. Regarding the crucial position that energy plays in the economic growth of a nation and its anticipated substantial future demand, it is a huge choice to save resources and allow productive usage. The findings of this analysis therefore determine the performance and reliability in one year (January to December 2016) of the Transcorp Ughelli Power station at Delta III GT9 (Hitachi H25 Gas Turbine Generator).

PERFORMANCE OF TURBOSHAFT GAS TURBINES

Turbo-shaft systems are distinguished by a single spool or, in some situations, two-spool gas turbine arrangement. Usually pressures range between 07:1 and 10:1 and with a TET of about 1250 K to 1450 K Turbine blade cooling makes. In certain medium and large turbocharged engines, the total pressure can be about 17:1 and the temperature of turbine entry is around 1500 K, in which case blade cooling is required. For specific strength, this 17:1 pressure ratio is about the optimum. The turboshaft engine is built in such a way that the helicopter rotor speed is independent of the gas generator's spinning. A schematic diagram of the turboshaft engine and its rising configuration with mounted output shaft and gear box. The usage of heat exchangers (both recuperators and inter-coolers) in an engine has enormous capacity for decreasing fuel consumption and thereby minimizing CO2 emissions.(technical specialist at MTU Aero Engines in Munich and member of the work team Intercooled Recuperative Aero-Engine (IRA)) once clarified that the recuperator utilizes some of the heat from the exhaust gas to thoracize the air. In fact, the demands of gas turbine users have, over the years, necessitated technical advancements in engine efficiency, and this is accomplished by extensive research. Technically, improving the thermal efficiency of industrial and aero gas turbines is paramount to the such as total pressure ratio (OPR) and TET. High-tech engine technologies such as cooling systems, system efficiencies, pressure fluctuations in ducts, and the implementation of different total thermodynamic processes, such as the usage of unusual technologies such as intercoolers and regenerators or recuperators. Therefore, gas turbines are indistinguishable from the performance and economic feasibility Through this we were aiming at turbo shaft gas turbines through civil aviation. A comparative evaluation of basic and updated engine cycle choices was conducted in the investigation. The aim of this work is to combine the technological importance of changed engine cycles such as zero-stage low pressure compressor (LPC) and intercooled / recovered (ICR) cycles in turbocharged helicopters.

PERFORMANCE OF FUEL COMPOSITION ON GAS TURBINE

An industrial gas turbine can operate on a broad range of power generation fuels. The required performance capacity, operability and engine emissions will differ greatly based on the fuel content and related conditions, precisely the hydrogen – carbon ratio. This research explores how specific fuels can influence the performance characteristics of Solar Turbines Incorporated industrial engines and illustrates the advantages of utilizing higher hydrogen-based fuels like higher capacity, higher productivity and lower carbon emissions. The research further addresses important operability problems for combustion that need to be addressed such as auto-ignition, recall, blowout, and combustion instabilities that are more noticeable while greatly changing the hydrogen – carbon ratio. Our aim is to provide a straightforward and succinct guide to mortify the reader analyzing characteristics of fuels with various properties and how natural gas is superior in terms of carbon dioxide, strength, and performance to other fossil fuels with lower hydrogen carbon ratios. Through the years of being allowed to utilize oils made up of a large range of stakeholders, pollution, combustion device operability, and the reliability of hot section materials. Those are discussed in the paper along with a property analysis of gaseous, liquid, and solid hydrocarbon fuel, a description of relevant uses, and a number of other musings. Many general findings may be made while evaluating the properties of the used hydrocarbon product, in particular the ratio of hydrogen to carbon (H / C).

General Observations to Remember

• Once the H / C hydrogen ratio reduces, the power of the shaft and thermal performance are increased. • In combustion materials a higher H / C yields more H2O and fewer CO2. • Liquids with low H / C provide higher average energies than traditional petroleum and natural-gas liquids. Lower-H / C oils include a wider variety of heavy hydrocarbons and particulates, resulting in much tougher fuel handling and injection procedures. • High-H2 and CO synthetic gases usually include volatile gases, thereby raising their heating benefit relative to natural gas and other hydrocarbon-based fuels. • The nature of fuel not only influences the fuel's energy content but also influences its physical and chemical properties, which significantly impact the operability of the combustion device. The important feature of combustion process is the mixing of a broad variety of chemicals with oxygen in the soil to produce a powerful energy supply in solid, fluid or gassed conditions. Hydrocarbon fuels used in traditional methods under human regulation continue their path for efficient release of electricity, and contribute to a heat finality and preferably a fully oxidized carbon and hydrogen synthesis of water and carbon dioxide. The differences in the fuel property that occur for the current wide spectrum of fuels result in improvements in the exergy released by the device. The system's kinetic strength is mere exergy, whereas a volume of electricity or a liquid pressurized fluid involves a combination of exergy and anergy. Exergy as "usable energy." Exergy is the portion of energy that can be transformed into some other type of useful energy because it cannot be transformed to anergy.

generated efficiently, economically and/or environmentally feasible. But certain metals "continue to cling to oxygen," in the process of heat and light, releasing energy. Recent experiments have been performed to hold nano- or micron-sized metal particles in fuel droplets to maximize combustion energies resulting in higher energy density, shorten the ignition delay period and increase catalytic impact fuel oxidation. Consequently, the application of metallic to hydrocarbon oils contributes to fewer CO2, NOx and other species. Although it's very fascinating to research what brandies in our environment alone, we concentrate on the operation of industrial gas turbines with the structural impacts of hydraulic fuels, varying from pure hydrogen to pure oil, etc. This collection of fuels often involves rising industrial gases arising from a number of processes for the gasification of hydrocarbons.

H/C Effects on Industrial Gas Turbine Output.

Through simulation, the results of increasing fuel content can be seen on the engine's production strength and performance while preserving usual operational constraints Usually, turbine inlet temperature (TRIT) in the turbine just after the combustion engine, including the speed and working temperature. Our first case study discusses the typical fuel used by industrial gas turbines such as natural gas, diesel (DF-2) and kerosene. For simulation purposes a common formulation of fuel has been chosen for each blend. A commonly asked query from a consumer may be "Why does the generator, when working on the same TRIT, generate less strength while running diesel fuel relative to natural gas? "Our case study addresses this problem with a single shaft or cold end drive and two shaft or hot end drive (HED) versions of our Solar Turbine engines capable of burning both gaseous and liquid fuels, better known as the" dual fuel "combustion systems of Solar Turbine.

GAS TURBINE PERFORMANCE DEGRADATION

Output of GT can be momentarily or permanently diminished. During operation and engine repair, the former may be partly recuperated whilst the latter needs replacement. Temporary causes of depreciation include fouling, oxidation, rust, and blade tip removal, while distortion of the airfoil and untwisting and frame distortions contribute to irreversible decay (meaning persistent decay even after significant overhaul). Damage may also be graded as recoverable (with washing) non-recoverable (cannot be restored during the operation nor can be recuperated after the recovery) and permanent (neither cleaning nor recovery or the evolution time span for the deterioration. Short-term / rapid degradation happens at the early age of the GT engine when it begins operation or, at any point during the activity of the engine, can result from a single event like object injury. Although long-term oxidation is more slowly created by absorption and accumulation of different toxins and/or elevated ambient temperatures. Such physical defects trigger adjustments to one or more of the performance parameters that characterize the efficiency of a different molecules-path component. Generally, the output metrics include compressor flow power, isentropic efficiency compressor, turbine flow ability, and isentropic efficiency generator. Changes in the output parameters result in consequent adjustments in the measurement parameters (temperature, friction, shaft speed and fuel flow), which are the fault signs or symptoms of engine safety testing.

Fouling

Filtration is adherence to numerous pollutants (such as grit, ashes, gravel, smoke, oil droplets, water mists, hydrocarbons and synthetic chemicals) to the gas-path portion surface. This contributes to surface roughness changes and airfoil shapes change. The end result is declining results. Compressor fouling causes the flow capacity to decrease and isentropic efficiency. Nevertheless, the degree of the percentage variance of these parameters is not understood, for example, the failure of the compressor which lead to a 5% loss of flow efficiency and a 2,5% loss of the isentropic performance regarding the site test results, a 5 per cent flow capacity compressor fouling and a 1.8 per cent reduction in isentropic efficiency. For another analysis the increase for flow capability due to compressor fouling was recorded to be 1.25 times the related shift in efficiency. At other side, the findings of model simulation showed that the flow capability variance by 3.1% decreased the isentropic output by 0.906%. Both researches nevertheless concluded that fouling affects the flow power rather than output. Compressor fouling accounts for 70 to 85 per cent of a GT overall output loss. A 5 percent flow capacity and a 1.8 percent reduction in isentropic efficiency due to compressor fouling could result in power output loss of 7 percent and heat rate increases of 2.5 percent. Whereas, Report is that, due to compressor fouling, a 10 percent reduction in power output could result in a 5 percent mass flow rate and an efficiency reduction of 2,5 per cent. That finding was decided in to the end, under adverse conditions, compressor fouling may result fuel usage. A 2.5% rise in fuel usage as the flow efficiency decreases by 5%. Fouling of the compressor will also reduce the clearance of blade tips and margins and raise turbine intake temperature (TET).

Erosion

Erosion is the incremental removal of substance from the surface of components of the gas route induced by absorption of pollutants such as sand, gravel, soil, smoke, pollution particles and liquid droplets. Dust is the most common of such sources since it appears on most of the GT application regions. The particulates which trigger erosion typically have a diameter of 20 μm or more. Erosion will strike all components of the gas-path although the degree of impact for turbines is higher than for compressors. It may result in a loss of about 5 percent overall performance. As with fouling, erosion-prone output degradation may be characterized by flow power and adjustments in productivity isentropic. Owing to an improvement in blade exterior dirtiness and tip clearance, and improvements in airfoil shape, performance declines during both compressor and turbine erosions. Whereas with compressor erosion, flow capacity decreases and increases with turbine erosion. According to, the flow capacity-efficiency-change ratio is 2:1. Thanks to the availability of a more efficient air filtration device, the risk of degradation is less for industrial GT than aircraft engines.

Corrosion

Corrosion is an inevitable degradation of materials owing to oxidation reactions or chemical encounters with inlet air pollutants (potassium and sodium chloride, mineral acids as well as other chemically reactive elements like sodium, potassium, lead and vanadium) and combustion gases (sulfur oxides, for example). It can be marked as warm and cold. Corrosion associated with airborne pollutant in conjunction with water is called cold or wet corrosion and especially affects the generator airfoils. Hot corrosion occurs due to combustion gasses that involve other chemicals and/or molten salts, which damage the turbines in particular. Corrosion attributable to contamination from hot gas is more extreme and is heavily affected by the gas temperature. Sand is the big corrosion element of both compressor and turbine components. It-piston flow power, isentropic piston performance, and isentropic turbine output and improves turbine flow ability. A good coating will avoid corrosion effects. Gas-path components become impaired as a result of inserting foreign items into the engine (such as birds or other animals, debris, rocks, mud, ice and runway gravel) or internal artifacts (broken out engine pieces such as blade bits or large carbon particles from fuel nozzles). Harm to foreign objects (FOD) is one of the most popular problems, typically in aircraft engines. Deterioration from foreign bodies differs from an unrecoverable damage to a catastrophic failure, as in the case of blade off or ingestion of large objects in the engine. It shows a rapid change in measurements of the gas path. Furthermore, unpredictable material loss or aerodynamic vibrational due to FOD distortion of the blade may induce motor vibration. Because of its effect on the roughness and distortion of the blade sheet, FOD highly influences the components isentropic performance than flow capacity. The extent of the failure depends upon the FOD / DOD form and design. Whether the harm induces a material failure on the surface of the edge, the flow potential decreases, or if the foreign object blocks the gas direction, the reverse is experienced.

Increase in Blade Tip Clearance

Blade tip clearance relates to an improvement in clearance between the tips of the traveling blades and the tips of the covering or stationary blades and the spinning core attributable to the reduction of particulate absorption content, thermal and centrifugal growth and erosion. This may also be influenced by rotation of the rotor assembly due to excess velocity during the starting process, or by thermal and centrifugal expansion between the commutator assembly and the turbine components. This triggers a decline of non-recoverable results. The growth in approvals will increase the leakage and consequently a deterioration in performance. Due to this fault the output degradation can be expressed by reductions in efficiency and flow capacity. For example, it has been reported that an increase of 0.8 percent in tip clearance could lead to a reduction of up to 3 percent and 2 percent in flow capacity and isentropic efficiency. A 1 percent rise in blade tip clearance will result in power consumption and total performance loss of more than 1 per cent. As recorded, a rise of 1 to 3.5 per cent in blade tip clearance will also trigger a decrease of up to 15 per cent in the stage pressure ration. The forms of pollutants and their impact on the physical and thermodynamic properties of GTgas-path components.

investigated a topic more directly connected to this case study60. It evaluated mainly combined gas turbines injected with cycle and steam, but also their effect on the electricity industry. The report started with an assessment of the power generation and equipment industries structure. The study then focused on the process of developing innovation and the contributing factors throughout the introduction of new technologies. The contemporary section of the developed gas turbine system study set the stage in which advanced turbines would emerge for the industry structure. This summary included a analysis of US regulatory policy, electrical utilities growth, and the essence of the turbine manufacturing industry. It then identified the guiding factors of turbine engineering and its sustainability. Innovation pushing factors is perceived to be legislative reforms to policy, such as PURPA and the Fuel Usage Act. This contributed to the technical demands of non-utility generators that had not existed before. Also, initial drivers in the report were the shortcomings of existing turbine equipment and the enhancements in modern turbine technologies. Three types of sustaining powers were: fiscal, technological, and systemic. Gas turbines have been attractive economically because of their low cost of production, O&M, and fuel. Obviously, combustion turbines increasing its market share due to their high efficiency and low impact on the environment. Structural, gas turbines benefited from the slow growth in demand that led to the availability for extremely rapid, modular growth with short lead times. The study encapsulated the process of innovation development as a reinforcing cycle of progress leading to demand, which resulted in further advances. The finding was that policy legislative reforms form the catalyst to the innovation process. Moreover, it concluded that many of the technical advances in gas turbines would have occurred without the regulatory spark, but that then gas and combined cycle turbines "would not have been the revolutionary technologies that transformed the electricity sector," suggesting that gas turbines could have been a driver of electrical reorganization.

CONCLUSION

In this article we addressed gas turbine efficiency, gas turbine power plant output, turboshaft gas turbine efficiency, gas turbine design performance structure performance, gas turbine design deterioration and gas turbine device advancement. Important advance in GT (gas turbine) research performance. In addition, the validity of the built expensive systems to test the power plant output based on appropriate criteria and specialized configuration has revealed many uncertainties. Using the optimization strategies has demonstrated robustness, suitability for parallel computation, and efficiency; thus, no adjustment is needed for a particular problem. Current and historical recognition is a prerequisite for the critical successful parameters which need to be used in the production of GT power plants output. The present research uses an externally fired gas turbine process to investigate small scale cogeneration of power and heat from a strong biomass material. Gas turbine cycles are measured using either an open working fluid circuit utilizing air as running fluid or a closed working circuit utilizing, He, He / CO2 or N2 as heat transfer fluid.

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Mohith N. Kumar*

Mechanical Engineer, QuEST Global Engineering services PVT LTD mohithnkumar98@gmail.com