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Journal articles on the topic 'Gas turbine flow efficiency'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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1

Kosowski, Krzysztof, and Marian Piwowarski. "Design Analysis of Micro Gas Turbines in Closed Cycles." Energies 13, no. 21 (2020): 5790. http://dx.doi.org/10.3390/en13215790.

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The problems faced by designers of micro-turbines are connected with a very small volume flow rate of working media which leads to small blade heights and a high rotor speed. In the case of gas turbines this limitation can be overcome by the application of a closed cycle with very low pressure at the compressor inlet (lower than atmospheric pressure). In this way we may apply a micro gas turbine unit of accepted efficiency to work in a similar range of temperatures and the same pressure ratios, but in the range of smaller pressure values and smaller mass flow rate. Thus, we can obtain a gas tu

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2

Yang, Xiaoyong, Zhenjia Yu, Xiaoli Yu, and Jie Wang. "ICONE19-43289 EFFECTS OF FLOW LOSSES ON EFFICIENCY OF HTGR GAS TURBINE CYCLE." Proceedings of the International Conference on Nuclear Engineering (ICONE) 2011.19 (2011): _ICONE1943. http://dx.doi.org/10.1299/jsmeicone.2011.19._icone1943_125.

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3

Valenti, Michael. "Keeping it Cool." Mechanical Engineering 123, no. 08 (2001): 48–52. http://dx.doi.org/10.1115/1.2001-aug-2.

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This article provides details of various aspects of air cooling technologies that can give gas turbines a boost. Air inlet cooling raises gas turbine efficiency, which is proportional to the mass flow of air fed into the turbine. The higher the mass flow, the greater the amount of electricity produced from the gas burned. Researchers at Mee Industries conduct laser scattering studies of their company’s fogging nozzles to determine if the nozzles project properly sized droplets for cooling. The goal for turbine air cooling systems is to reduce the temperature of inlet air from the dry bulb temp

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4

Wilson, Jay M., and Henry Baumgartner. "A New Turbine for Natural Gas Pipelines." Mechanical Engineering 121, no. 05 (1999): 72–74. http://dx.doi.org/10.1115/1.1999-may-7.

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The new Cooper-Bessemer power turbine is a high-efficiency, center frame-mounted, three-stage unit that can be driven by either the existing RB211-24 gas generator or the new improved version. The upgraded gas generator combined with the new power turbine offers an increase in nominal output from 28.4 MW (38,000 hp) to 31.8 MW (42,600 hp). The new coupled turbine, now being tested, is called the Coberra 6761. Besides improving core engine performance, the program's objectives included improved fuel efficiency and reliability, and easier site serviceability; extension of the modular concept fro

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5

Rodgers, C. "Impingement Starting and Power Boosting of Small Gas Turbines." Journal of Engineering for Gas Turbines and Power 107, no. 4 (1985): 821–27. http://dx.doi.org/10.1115/1.3239817.

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The technology of high-pressure air or hot-gas impingement from stationary shroud supplementary nozzles onto radial outflow compressors and radial inflow turbines to permit rapid gas turbine starting or power boosting is discussed. Data are presented on the equivalent turbine component performance for convergent/divergent shroud impingement nozzles, which reveal the sensitivity of nozzle velocity coefficient with Mach number and turbine efficiency with impingement nozzle admission arc. Compressor and turbine matching is addressed in the transient turbine start mode with the possibility of oper

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6

Крюков, Алексей, and Aleksei Kriukov. "Three dimensional gas-dynamic calculation of nozzle block of small flow-rate centripetal turbine." Vestnik of Astrakhan State Technical University. Series: Marine engineering and technologies 2019, no. 4 (2019): 89–95. http://dx.doi.org/10.24143/2073-1574-2019-4-89-95.

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The article describes the low-consumption turbines as reliable, productive, small-sized actuating mechanisms in various units and machines. Experience in production and use  of low-cost turbine stages contributes to improving the efficiency along with simplifying and re-ducing the cost of manufacturing of the blades and the stage in general. Improving the efficiency  of low-consumption turbines requires solving the problem of aerodynamic improvement of the flow part and the calculated determination of the optimal geometry and operating modes of the impeller flow. One of the innovat

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7

Vidian, Fajri, Putra Anugrah Peranginangin, and Muhamad Yulianto. "Cycle-Tempo Simulation of Ultra-Micro Gas Turbine Fueled by Producer Gas Resulting from Leaf Waste Gasification." Journal of Mechanical Engineering 24, no. 3 (2021): 14–20. http://dx.doi.org/10.15407/pmach2021.03.014.

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Leaf waste has the potential to be converted into energy because of its high availability both in the world and Indonesia. Gasification is a conversion technology that can be used to convert leaves into producer gas. This gas can be used for various applications, one of which is using it as fuel for gas turbines, including ultra-micro gas ones, which are among the most popular micro generators of electric power at the time. To minimize the risk of failure in the experiment and cost, simulation is used. To simulate the performance of gas turbines, the thermodynamic analysis tool called Cycle-Te

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8

Rice, I. G. "Split Stream Boilers for High-Temperature/High-Pressure Topping Steam Turbine Combined Cycles." Journal of Engineering for Gas Turbines and Power 119, no. 2 (1997): 385–94. http://dx.doi.org/10.1115/1.2815586.

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Research and development work on high-temperature and high-pressure (up to 1500°F TIT and 4500 psia) topping steam turbines and associated steam generators for steam power plants as well as combined cycle plants is being carried forward by DOE, EPRI, and independent companies. Aeroderivative gas turbines and heavy-duty gas turbines both will require exhaust gas supplementary firing to achieve high throttle temperatures. This paper presents an analysis and examples of a split stream boiler arrangement for high-temperature and high-pressure topping steam turbine combined cycles. A portion of the

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9

Godin, T., S. Harvey, and P. Stouffs. "High-Temperature Reactive Flow of Combustion Gases in an Expansion Turbine." Journal of Turbomachinery 119, no. 3 (1997): 554–61. http://dx.doi.org/10.1115/1.2841157.

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The analysis of the chemical behavior of the working fluid in gas turbines is usually restricted to the combustion chamber sections. However, the current trend toward higher Turbine Inlet Temperatures (TIT), in order to achieve improved thermal efficiency, will invalidate the assumption of frozen composition of the gases in the first stages of the expansion process. It will become necessary to consider the recombination reactions of the dissociated species, resulting in heat release during expansion. In order to quantify the influence of this reactivity on the performance of high TIT gas turbi

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10

Choi, Seok Min, Seungyeong Choi, and Hyung Hee Cho. "Effect of Various Coolant Mass Flow Rates on Sealing Effectiveness of Turbine Blade Rim Seal at First Stage Gas Turbine Experimental Facility." Energies 13, no. 16 (2020): 4105. http://dx.doi.org/10.3390/en13164105.

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The appropriate coolant mass flow of turbine blade rim seal has become an important issue as turbine blades are exposed to increasingly higher thermal load owing to increased turbine inlet temperature. If the coolant is deficient, hot gas ingresses to the rim seal, or if sufficient, the efficiency of turbine decreases. Therefore, we analyzed sealing effectiveness of rim seal derive appropriate coolant mass flow rate at various conditions. The experimental facility was modified from one designed for an aero-engine gas turbine. Rotational Reynolds number varied from 3 × 105 to 5 × 105 based on r

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11

Han, Je-Chin, and Srinath Ekkad. "Recent Development in Turbine Blade Film Cooling." International Journal of Rotating Machinery 7, no. 1 (2001): 21–40. http://dx.doi.org/10.1155/s1023621x01000033.

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Gas turbines are extensively used for aircraft propulsion, land-based power generation, and industrial applications. Thermal efficiency and power output of gas turbines increase with increasing turbine rotor inlet temperature (RIT). The current RIT level in advanced gas turbines is far above the .melting point of the blade material. Therefore, along with high temperature material development, a sophisticated cooling scheme must be developed for continuous safe operation of gas turbines with high performance. Gas turbine blades are cooled internally and externally. This paper focuses on externa

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12

Rusanov, Andrii V., Viktor L. Shvetsov, Anna I. Kosianova, et al. "The Gas-Dynamic Efficiency Increase of the K-300 Series Steam Turbine Control Compartment." Journal of Mechanical Engineering 23, no. 4 (2020): 6–13. http://dx.doi.org/10.15407/pmach2020.04.006.

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The paper proposes ways to increase the efficiency of nozzle control for steam power turbines of the K-300 series, that, along with the K-200 series turbines, form the basis of thermal energy in Ukraine. The object of study is considered to be the control compartment (CC) of the high-pressure cylinder (HPC) of the K-325-23.5 steam turbine. In the paper, the calculation and design of the control compartment of the steam turbine was performed using the complex methodology developed in IPMach NAS of Ukraine, that includes methods of different levels of complexity, from one-dimensional to models f

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13

Schädler, Rainer, Anestis I. Kalfas, Reza S. Abhari, Gregor Schmid, Tilmann auf dem Kampe, and Sanjay B. Prabhu. "Novel high-pressure turbine purge control features for increased stage efficiency." Journal of the Global Power and Propulsion Society 1 (July 21, 2017): 68MK5V. http://dx.doi.org/10.22261/68mk5v.

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AbstractRim seals throttle flow and have shown to impact the aerodynamic performance of gas turbines. The results of an experimental investigation of a rim seal exit geometry variation and its impact on the high-pressure turbine flow field are presented. A one-and-a-half stage, unshrouded and highly loaded axial turbine configuration with 3-dimensionally shaped blades and non-axisymmetric end wall contouring has been tested in an axial turbine facility. The exit of the rotor upstream rim seal was equipped with novel geometrical features which are termed as purge control features (PCFs) and a b

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14

Grigoriev, A. V., A. A. Kosmatov, О. A. Rudakov, and A. V. Solovieva. "Theory of gas turbine engine optimal gas generator." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 2 (2019): 52–61. http://dx.doi.org/10.18287/2541-7533-2019-18-2-52-61.

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The article substantiates the necessity of designing an optimal gas generator of a gas turbine engine. The generator is to provide coordinated joint operation of its units: compressor, combustion chamber and compressor turbine with the purpose of reducing the period of development of new products, improving their fuel efficiency, providing operability of the blades of a high-temperature cooled compressor turbine and meeting all operational requirements related to the operation of the optimal combustion chamber including a wide range of stable combustion modes, high-altitude start at subzero ai

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15

Diakunchak, I. S. "Cold Flow Turbine Rig Tests of the Original and Redesigned Compressor Turbines of an Industrial Gas Turbine Engine." Journal of Turbomachinery 111, no. 2 (1989): 146–52. http://dx.doi.org/10.1115/1.3262249.

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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

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16

Mai, Thanh Dam, and Jaiyoung Ryu. "Effects of Leading-Edge Modification in Damaged Rotor Blades on Aerodynamic Characteristics of High-Pressure Gas Turbine." Mathematics 8, no. 12 (2020): 2191. http://dx.doi.org/10.3390/math8122191.

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The flow and heat-transfer attributes of gas turbines significantly affect the output power and overall efficiency of combined-cycle power plants. However, the high-temperature and high-pressure environment can damage the turbine blade surface, potentially resulting in failure of the power plant. Because of the elevated cost of replacing turbine blades, damaged blades are usually repaired through modification of their profile around the damage location. This study compared the effects of modifying various damage locations along the leading edge of a rotor blade on the performance of the gas tu

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17

Rogalev, Andrey, Vladimir Kindra, Alexey Zonov, Nikolay Rogalev, and Levon Agamirov. "Evaluation of Bleed Flow Precooling Influence on the Efficiency of the E-MATIANT Cycle." Mechanics and Mechanical Engineering 22, no. 2 (2020): 593–602. http://dx.doi.org/10.2478/mme-2018-0047.

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AbstractThis study aims to present a method for precooling bleed flow by water injection in the E-MATIANT cycle and to estimate its impact on the overall efficiency. The design parameters of the cycle are set up on the basis of the component technologies of today's state-of-the-art gas turbines with a turbine inlet temperature between 1100 and 1700°C. Several schemes of the E-MATIANT cycle are considered: with one, two and three combustion chambers. The optimal pressure ratio ranges for the considered turbine inlet temperatures are identified and a comparison with existing evaluations is made.

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18

Dabbashi, Siddig, Tarak Assaleh, and Asia Gabassa. "EVALUATION OF DEGRADATION EFFECT ON INTERCOOLED GAS TURBINE PERFORMANCE OPERATED IN FLEXIBLE MODE." Scientific Journal of Applied Sciences of Sabratha University 2, no. 1 (2019): 52–70. http://dx.doi.org/10.47891/sabujas.v2i1.52-70.

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This paper investigates the effect of type and level of degradation in industrial gas turbine components on its performance under flexible operation due to working as a back-up to renewable energy sources (RES). This investigation was carried out for a 2-shaft 100MW aero-derivative gas turbine with intercooler. Due to the influence of unpredictable nature of power produced by RES, power plants are now operating in a flexible manner, which will require the operator to either stop operation during high feed-in from renewables or reducing the power output from the power plant to a certain percent

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19

Schobeiri, M. T., and K. Pappu. "Optimization of Trailing Edge Ejection Mixing Losses: A Theoretical and Experimental Study." Journal of Fluids Engineering 121, no. 1 (1999): 118–25. http://dx.doi.org/10.1115/1.2821991.

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The aerodynamic effects of trailing edge ejection on mixing losses downstream of cooled gas turbine blades were experimentally investigated and compared with an already existing one-dimensional theory by Schobeiri (1989). The significant parameters determining the mixing losses and, therefore, the efficiency of cooled blades, are the ejection velocity ratio, the cooling mass flow ratio, the temperature ratio, the slot thickness ratio, and the ejection flow angle. To cover a broad range of representative turbine blade geometry and flow deflections, a General Electric power generation gas turbin

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20

Mrzljak, Vedran, Nikola Anđelić, Ivan Lorencin, and Zlatan Car. "Analysis of Gas Turbine Operation before and after Major Maintenance." Journal of Maritime & Transportation Science 57, no. 1 (2019): 57–70. http://dx.doi.org/10.18048/2019.57.04.

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This paper presents an analysis of the gas turbine real process (with all losses included) before and after a major maintenance. The analysis of both gas turbine operating regimes is based on data measured during its exploitation. Contrary to authors’ expectations, the major maintenance process did not result either in any decrease in losses or increase in efficiencies for the majority of the gas turbine components. However, the major maintenance influenced positively the gas turbine combustion chambers (reduction in losses and increase in the combustion chambers efficiency). After the major m

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21

Filinov, Evgeny, Andrey Tkachenko, Hewa Hussein Omar, and Viktor Rybakov. "Increase the Efficiency of a Gas Turbine Unit for Gas Turbine Locomotives by Means of Steam Injection into the Flow Section." MATEC Web of Conferences 220 (2018): 03010. http://dx.doi.org/10.1051/matecconf/201822003010.

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In the modern world of railways, electrification is given great importance. Currently, more than 50% of all freight traffic carried out by electric traction. However, today, about half of the railways are not electrified, so it is necessary to use thermal engines to drive the locomotive. One of the possible variant is use gas turbine unit. The power of the gas turbine unit is given to the electric generator, and the electric motors drive the locomotive. In the present paper, as a power plant of a gas turbine locomotive, considered gas turbine unit with a twin -shaft gas generator of two scheme

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22

Han, Je-Chin. "Recent Studies in Turbine Blade Cooling." International Journal of Rotating Machinery 10, no. 6 (2004): 443–57. http://dx.doi.org/10.1155/s1023621x04000442.

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Gas turbines are used extensively for aircraft propulsion, land-based power generation, and industrial applications. Developments in turbine cooling technology play a critical role in increasing the thermal efficiency and power output of advanced gas turbines. Gas turbine blades are cooled internally by passing the coolant through several rib-enhanced serpentine passages to remove heat conducted from the outside surface. External cooling of turbine blades by film cooling is achieved by injecting relatively cooler air from the internal coolant passages out of the blade surface in order to form

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23

Sudadiyo, Sri, and Jupiter Sitorus Pane. "DESAIN AWAL TURBIN UAP TIPE AKSIAL UNTUK KONSEP RGTT30 BERPENDINGIN HELIUM." JURNAL TEKNOLOGI REAKTOR NUKLIR TRI DASA MEGA 18, no. 2 (2016): 65. http://dx.doi.org/10.17146/tdm.2016.18.2.2319.

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ABSTRAK DESAIN AWAL TURBIN UAP TIPE AKSIAL UNTUK KONSEP RGTT30 BERPENDINGIN HELIUM. Konsep reaktor daya nuklir yang dikembangkan merupakan jenis reaktor berpendingin gas dengan temperatur tinggi (RGTT). Gas yang digunakan untuk mendinginkan teras RGTT adalah helium. Konsep RGTT ini dapat menghasilkan daya termal 30 MWth sehingga dinamakan RGTT30. Temperatur helium mampu mencapai 700 °C ketika keluar dari teras RGTT30 dan digunakan untuk memanaskan air di dalam steam generator hingga mencapai temperatur 435 °C. Steam generator dihubungkan dengan turbin uap yang dikopel dengan generator listrik

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24

Kurz, Rainer. "Parameter Optimization on Combined Gas Turbine-Fuel Cell Power Plants." Journal of Fuel Cell Science and Technology 2, no. 4 (2005): 268–73. http://dx.doi.org/10.1115/1.2041669.

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A thermodynamic model for a gas turbine-fuel cell hybrid is created and described in the paper. The effects of gas turbine design parameters such as compressor pressure ratio, compressor efficiency, turbine efficiency, and mass flow are considered. The model allows to simulate the effects of fuel cell design parameters such as operating temperature, pressure, fuel utilization, and current density on the cycle efficiency. This paper discusses, based on a parametric study, optimum design parameters for a hybrid gas turbine. Because it is desirable to use existing gas turbine designs for the hybr

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25

Roy Yap, Mun, and Ting Wang. "Simulation of Producer Gas Fired Power Plants with Inlet Fog Cooling and Steam Injection." Journal of Engineering for Gas Turbines and Power 129, no. 3 (2006): 637–47. http://dx.doi.org/10.1115/1.2718571.

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Biomass can be converted to energy via direct combustion or thermochemical conversion to liquid or gas fuels. This study focuses on burning producer gases derived from gasifying biomass wastes to produce power. Since the producer gases are usually of low calorific values (LCV), power plant performance under various operating conditions has not yet been proven. In this study, system performance calculations are conducted for 5MWe power plants. The power plants considered include simple gas turbine systems, steam turbine systems, combined cycle systems, and steam injection gas turbine systems us

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Norris, G., and R. G. Dominy. "Diffusion rate influences on inter-turbine diffusers." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 211, no. 3 (1997): 235–42. http://dx.doi.org/10.1243/0957650971537141.

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Inter-turbine diffusers are becoming of increasing importance to the aero gas turbine designer to diffuse the flow between the HP (high-pressure) or IP (intermediate-pressure) turbine and the LP (low-pressure) turbine. Diffusing the flow upstream of the LP turbine and raising the mean passage radius increases stage efficiency. These inter-turbine diffusers, which have high curvature, S-shaped geometry and low-energy wakes created by the upstream turbine, together give rise to secondary flows, making the flow fully three-dimensional. Using both experimental measurements and CFD (computational f

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27

Vlasic, E. P., S. Girgis, and S. H. Moustapha. "The Design and Performance of a High Work Research Turbine." Journal of Turbomachinery 118, no. 4 (1996): 792–99. http://dx.doi.org/10.1115/1.2840936.

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This paper describes the design and performance of a high work single-stage research turbine with a pressure ratio of 5.0, a stage loading of 2.2, and cooled stator and rotor. Tests were carried out in a cold flow rig and as part of a gas generator facility. The performance of the turbine was assessed, through measurements of reaction, rotor exit conditions and efficiency, with and without airfoil cooling. The measured cooled efficiency in the cold rig was 79.9 percent, which, after correcting for temperature and measuring plane location, matched reasonably well the efficiency of 81.5 percent

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28

Molyakov, V. D., B. A. Kunikeev, and N. I. Troitskiy. "Analysis of Physical Processes in the Flow Parts of Gas Turbines with Different Blade Chords." Proceedings of Higher Educational Institutions. Маchine Building, no. 7 (736) (July 2021): 40–53. http://dx.doi.org/10.18698/0536-1044-2021-7-40-53.

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Theoretical and experimental studies of the current flowing in the lattices of the turbine stage impeller with a change in the elongation of its blades at constant constraining diameters of the flow part (constant blade lengths) are carried out. Four single-stage turbines with different chords of rotor blades and their relative elongations have been investigated. To explain the nature of the integral characteristics of the turbine stage with a change in the relative elongation of the rotor blades, detailed studies of the spatial flow structure in the gap between wheels and behind the impeller

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Yari, M., and K. Sarabchi. "Modelling and optimization of part-flow evaporative gas turbine cycles." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 7 (2005): 533–48. http://dx.doi.org/10.1243/095765005x31315.

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The evaporative gas turbine cycle is a new high-efficiency power cycle that has reached the pilot plant testing stage. This article presents the construction of a mathematical model for thermodynamic simulation of part-flow evaporative gas turbine cycle including steam injection. The maximum deviation of predicted performance results by this model from available data in literature was 1 per cent. Then, changes in configuration of this cycle have been investigated. Configuration changes concern using feed water heater and injection of saturated vapour instead of superheated vapour to the humid

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Wilcock, R. C., J. B. Young, and J. H. Horlock. "The Effect of Turbine Blade Cooling on the Cycle Efficiency of Gas Turbine Power Cycles." Journal of Engineering for Gas Turbines and Power 127, no. 1 (2005): 109–20. http://dx.doi.org/10.1115/1.1805549.

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A thermodynamic cycle analysis computer code for the performance prediction of cooled gas turbines has been used to calculate the efficiency of plants with varying combustor outlet temperature, compressor pressure ratio, and turbomachinery polytropic efficiency. It is shown that the polytropic efficiency exerts a major influence on the optimum operating point of cooled gas turbines: for moderate turbomachinery efficiency the search for enhanced combustor outlet temperature is shown to be logical, but for high turbomachinery efficiency this is not necessarily so. The sensitivity of the cycle ef

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Hänni, Dominic, Rainer Schädler, Reza Abhari, et al. "Purge flow effects on rotor hub endwall heat transfer with extended endwall contouring into the disk cavity." Journal of the Global Power and Propulsion Society 3 (May 13, 2019): 555–68. http://dx.doi.org/10.33737/jgpps/109838.

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Efficiency improvements for gas turbines are strongly coupled with increasing turbine inlet temperatures. This imposes new challenges for designers for efficient and adequate cooling of turbine components. Modern gas turbines inject bleed air from the compressor into the stator/rotor rim seal cavity to prevent hot gas ingestion from the main flow, while cooling the rotor disk. The purge flow interacts with the main flow field and static pressure field imposed by the turbine blades. This complex interaction causes non-uniform and jet-like penetration of the purge flow into the main flow field,

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Konovalov, Dmytro, Halina Kobalava, Mykola Radchenko, Ionut-Cristian Scurtu, and Roman Radchenko. "Determination of hydraulic resistance of the aerothermopressor for gas turbine cyclic air cooling." E3S Web of Conferences 180 (2020): 01012. http://dx.doi.org/10.1051/e3sconf/202018001012.

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One of the promising trends to increase the fuel and energy efficiency of gas turbines is contact cooling of cyclic air by using a twophase jet apparatus – an aerothermopressor. The rational parameters of work processes of the aerothermopressor were studied. The experimental setup was designed to simulate the aerothermopressor operation in the cooling air cycle of the gas turbine and to determine pressure losses in the aerothermopressor flow part. Based on the obtained experimental data, an empirical equation was proposed to determine the hydraulic resistance coefficient of the aerothermopress

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Piskunov, Stanislav, Denis Popov, and Nikita Samoylenko. "Loss classification and review of secondary flow models in gas turbine cascades." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 63 (2020): 30–39. http://dx.doi.org/10.15593/2224-9982/2020.63.04.

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Much attention is paid to increasing the efficiency of turbofan engines by increasing the efficiency of the main modules. The aerodynamic efficiency of a turbine depends on the level of total pressure and kinetic energy losses, which are determined by the scale of secondary flows in the channels of the turbine cascades. There are many studies and articles on the topic of secondary flows, in which vortex structures are often given incorrect names. The problem lies in the absence of a unified model of secondary flows and mismatch in the names of the components of secondary flows in adaptation of

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Kim, Kyoung Hoon, Kyoung Jin Kim, and Hyung Jong Ko. "Effects of Wet Compression on Performance of Regenerative Gas Turbine Cycle with Turbine Blade Cooling." Applied Mechanics and Materials 224 (November 2012): 256–59. http://dx.doi.org/10.4028/www.scientific.net/amm.224.256.

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When water is injected at an inlet of compressor, wet compression occurs due to evaporation of water droplets. In this work, the effects of wet compression on the performance of regenerative gas turbine cycle with turbine blade cooling are analytically investigated. For various pressure ratios and water injection ratios, the important system variables such as ratio of coolant flow for turbine blade cooling, fuel consumption, specific power and thermal efficiency are estimated. Parametric studies show that wet compression leads to significant enhancement in both specific power and thermal effic

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Mousafarash, Ali. "Exergy and Exergoenvironmental Analysis of a CCHP System Based on a Parallel Flow Double-Effect Absorption Chiller." International Journal of Chemical Engineering 2016 (2016): 1–8. http://dx.doi.org/10.1155/2016/2370305.

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A combined cooling, heating, and power (CCHP) system which produces electricity, heating, and cooling is modeled and analyzed. This system is comprised of a gas turbine, a heat recovery steam generator, and a double-effect absorption chiller. Exergy analysis is conducted to address the magnitude and the location of irreversibilities. In order to enhance understanding, a comprehensive parametric study is performed to see the effect of some major design parameters on the system performance. These design parameters are compressor pressure ratio, gas turbine inlet temperature, gas turbine isentrop

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Verstraete, T., Z. Alsalihi, and R. A. Van den Braembussche. "Numerical Study of the Heat Transfer in Micro Gas Turbines." Journal of Turbomachinery 129, no. 4 (2006): 835–41. http://dx.doi.org/10.1115/1.2720874.

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This paper presents a numerical investigation of the heat transfer inside a micro gas turbine and its impact on the performance. The large temperature difference between turbine and compressor in combination with the small dimensions results in a high heat transfer causing a drop in efficiency of both components. Present study aims to quantify this heat transfer and to reveal the different mechanisms that contribute to it. A conjugate heat transfer solver has been developed for this purpose. It combines a three-dimensional (3D) conduction calculation inside the rotor and the stator with a 3D f

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Lee, Samuel P., Simon M. Barrans, and Ambrose K. Nickson. "The impact of volute aspect ratio and tilt on the performance of a mixed flow turbine." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 235, no. 6 (2021): 1435–50. http://dx.doi.org/10.1177/0957650921998228.

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Current trends in the automotive industry towards engine downsizing means turbocharging now plays a vital role in engine performance. The purpose of turbocharging is to increase the engine inlet air density by utilising, the otherwise wasted energy in the exhaust gas. This energy extraction is commonly accomplished through the use of a radial turbine. Although less commonly used, mixed flow turbines can offer aerodynamic advantages due to the manipulation of blade leading (LE) angles, improving performance at low velocity ratios. The current paper investigates the performance of a mixed flow t

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Anand, A. K., C. S. Cook, J. C. Corman, and A. R. Smith. "New Technology Trends for Improved IGCC System Performance." Journal of Engineering for Gas Turbines and Power 118, no. 4 (1996): 732–36. http://dx.doi.org/10.1115/1.2816988.

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The application of gas turbine technology to IGCC systems requires careful consideration of the degree and type of integration used during the system design phase. Although gas turbines provide the primary output and efficiency gains for IGCC systems, as compared with conventional coal-fired power generation systems, they are commercially available only in specific size ranges. Therefore, it is up to the IGCC system designer to optimize the IGCC power plant within the required output, efficiency, and site conditions by selecting the system configuration carefully, particularly for air separati

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Moliere, Michel, Jean-Noël Jaubert, Romain Privat, and Thierry Schuhler. "Stationary gas turbines: an exergetic approach to part load operation." Oil & Gas Science and Technology – Revue d’IFP Energies nouvelles 75 (2020): 10. http://dx.doi.org/10.2516/ogst/2020001.

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As renewables are progressively displacing thermal plants in the power generation scene worldwide, the vocation of stationary Gas Turbines (GT) is deeply evolving. In this irreversible move GT plants are called upon to become cycling units with increasingly variable load profiles. This is dictated by the need to compensate for the fluctuations of renewable energy sources and secure the spinning reserve that is indispensable for the stability of the grids. This new scenario creates a serious challenge for gas turbine designers and operators in terms of investment policy, plant management and eq

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Khodak, E. A., and G. A. Romakhova. "Thermodynamic Analysis of Air-Cooled Gas Turbine Plants." Journal of Engineering for Gas Turbines and Power 123, no. 2 (2000): 265–70. http://dx.doi.org/10.1115/1.1341204.

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At present high temperature, internally cooled gas turbines form the basis for the development of highly efficient plants for utility and industrial markets. Minimizing irreversibility of processes in all components of a gas turbine plant leads to greater plant efficiency. Turbine cooling, like all real processes, is an irreversible process and results in lost opportunity for producing work. Traditional tools based on the first and second laws of thermodynamics enable performance parameters of a plant to be evaluated, but they give no way of separating the losses due to cooling from the overal

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Hu, Bo, Xuesong Li, Yanxia Fu, Chunwei Gu, Xiaodong Ren, and Jiaxing Lu. "Axial Thrust, Disk Frictional Losses, and Heat Transfer in a Gas Turbine Disk Cavity." Energies 12, no. 15 (2019): 2917. http://dx.doi.org/10.3390/en12152917.

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The gas turbine is a kind of high-power and high-performance energy machine. Currently, it is a hot issue to improve the efficiency of the gas turbines by reducing the amount of secondary air used in the disk cavity. The precondition is to understand the effects of the through-flow rate on the axial thrust, the disk frictional losses, and the characteristics of heat transfer under various experimental conditions. In this paper, experiments are conducted to analyze the characteristics of flow and heat transfer. To ensure the safe operation of the gas turbine, the pressure distribution and the a

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Heng, Wu, Li Benwei, Zhao Shufan, and Wang Yonghua. "Study on the Mechanism of a Carrier-based Engine Parts' Performance Decline and Its Impact on the Whole Engine Performance." MATEC Web of Conferences 179 (2018): 01012. http://dx.doi.org/10.1051/matecconf/201817901012.

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The technical approach "use – parts' change - engine performance change" has been adopted to study and analyse the gas unit parts' performance changes of an engine after a long time operation. The mechanism of performance decline of the turbine is analysed based on the numerical simulation, the impact of components' performance decline on overall engine performance is studied and the correlation analysis is carried out. The results show that the change of turbine tip clearance, roughness increase and surface change will lead to the enhancement of secondary flow and the increase of influence ar

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El-Masri, M. A. "A Modified, High-Efficiency, Recuperated Gas Turbine Cycle." Journal of Engineering for Gas Turbines and Power 110, no. 2 (1988): 233–42. http://dx.doi.org/10.1115/1.3240112.

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The thermal efficiency of an intercooled/recuperated cycle may be increased by: (a) evaporatively aftercooling the compressor discharge; and (b) injecting and evaporating an additional amount of water in the recuperator. Comparative computations of such a modified cycle and intercooled/recuperated cycles carried out over a wide range of pressure ratios and turbine inlet temperatures and at two different levels of component technologies show an advantage of over five percentage points in efficiency for the modified cycle. About 60 percent of this improvement results from modification (a) and 40

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Rao, K. V. J., S. Kolla, Ch Penchalayya, M. Ananda Rao, and J. Srinivas. "Optimum stage design in axial-flow gas turbines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 216, no. 6 (2002): 433–45. http://dx.doi.org/10.1243/095765002761034203.

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This paper proposes the formulation and solution procedures in the stage optimization of the effective dimensions of an axial-flow gas turbine. Increasing the stage efficiency and minimizing the overall mass of components per stage are the common objectives in gas turbine design. This multiple objective function, with important constraints like natural frequency limits, root stress values, and tip deflection in blades, constitutes the overall optimization problem. The problem is solved by using a modified nonlinear simplex method with a built-in user interactive program that helps in on-line m

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Mankonen, Aleksi, Juha Kaikko, Esa Vakkilainen, and Vitaliy Sergeev. "Thermodynamic analysis of a condensing evaporator in an evaporative gas turbine cycle." MATEC Web of Conferences 245 (2018): 07007. http://dx.doi.org/10.1051/matecconf/201824507007.

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Low efficiency is the main stumbling block preventing the widespread adoption of small-scale gas turbines in distributed energy production. The evaporative gas turbine cycle has been proposed as a way to improve efficiency, but the large number of components required make the configuration complex and expensive. The condensing evaporator is a component that simplifies the evaporative gas turbine cycle. The heat and mass exchanger device is designed for an externally fired application, which means that the flue gas stream is replaced by moist air. The air-water mixture condenses inside a tube b

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Hoffren, J., T. Talonpoika, J. Larjola, and T. Siikonen. "Numerical Simulation of Real-Gas Flow in a Supersonic Turbine Nozzle Ring." Journal of Engineering for Gas Turbines and Power 124, no. 2 (2002): 395–403. http://dx.doi.org/10.1115/1.1423320.

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In small Rankine cycle power plants, it is advantageous to use organic media as the working fluid. A low-cost single-stage turbine design together with the high molecular weight of the fluid leads to high Mach numbers in the turbine. Turbine efficiency can be improved significantly by using an iterative design procedure based on an accurate CFD simulation of the flow. For this purpose, an existing Navier-Stokes solver is tailored for real gas, because the expansion of an organic fluid cannot be described with ideal gas equations. The proposed simulation method is applied for the calculation of

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Ameri, A. A., E. Steinthorsson, and D. L. Rigby. "Effect of Squealer Tip on Rotor Heat Transfer and Efficiency." Journal of Turbomachinery 120, no. 4 (1998): 753–59. http://dx.doi.org/10.1115/1.2841786.

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Calculations were performed to simulate the tip flow and heat transfer on the GE-E3 first-stage turbine, which represents a modern gas turbine blade geometry. Cases considered were a smooth tip, 2 percent recess, and 3 percent recess. In addition, a two-dimensional cavity problem was calculated. Good agreement with experimental results was obtained for the cavity calculations, demonstrating that the k–ω turbulence model used is capable of representing flows of the present type. In the rotor calculations, two dominant flow structures were shown to exist within the recess. Also areas of large he

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Schädler, Rainer, Dominic Hänni, Anestis Kalfas, et al. "Noise characteristics of a reduced blade count rotor with improved stage efficiency." Journal of the Global Power and Propulsion Society 3 (November 18, 2019): 653–67. http://dx.doi.org/10.33737/jgpps/112303.

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A reduction in rotor blade count in combination with a gain in aerodynamic performance is a desirable design goal for gas turbines to reduce the overall operational costs. Reducing the number of blades provokes inherently an increase in blade loading which drives the secondary flow strength. In the presented experimental work, the results of inter-stage probe measurements in a highly loaded 1.5-stage axial turbine rig show the potential to improve the stage efficiency for a reduced blade count rotor with respect to a baseline configuration with more blades. Time-resolved probe measurements rev

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Horlock, J. H. "The Evaporative Gas Turbine [EGT] Cycle." Journal of Engineering for Gas Turbines and Power 120, no. 2 (1998): 336–43. http://dx.doi.org/10.1115/1.2818127.

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Humidification of the flow through a gas turbine has been proposed in a variety of forms. The STIG plant involves the generation of steam by the gas turbine exhaust in a heat recovery steam generator (HRSG), and its injection into or downstream of the combustion chamber. This increases the mass flow through the turbine and the power output from the plant, with a small increase in efficiency. In the evaporative gas turbine (or EGT) cycle, water is injected in the compressor discharge in a regenerative gas turbine cycle (a so-called CBTX plant—compressor [C], burner [B], turbine [T], heat exchan

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50

Choi, Myung Gon, and Jaiyoung Ryu. "Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine." Energies 11, no. 10 (2018): 2654. http://dx.doi.org/10.3390/en11102654.

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Combined cycle power plants (CCPPs) are becoming more important as the global demand for electrical power increases. The power and efficiency of CCPPs are directly affected by the performance and thermal efficiency of the gas turbines. This study is the first unsteady numerical study that comprehensively considers axial gap (AG) in the first-stage stator and first-stage rotor (R1) and hot streaks in the combustor outlet throughout an entire two-stage turbine, as these factors affect the aerodynamic performance of the turbine. To resolve the three-dimensional unsteady-state compressible flow, a

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