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Journal articles on the topic 'Variable geometry compressor'

Author: Grafiati

Published: 4 June 2021

Last updated: 15 February 2022

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1

Gallar, Luis, Manuel Arias, Vassilios Pachidis, and Riti Singh. "Stochastic axial compressor variable geometry schedule optimisation." Aerospace Science and Technology 15, no. 5 (2011): 366–74. http://dx.doi.org/10.1016/j.ast.2010.08.010.

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2

Nelson, S. A., Z. S. Filipi, and D. N. Assanis. "The Use of Neural Nets for Matching Fixed or Variable Geometry Compressors With Diesel Engines." Journal of Engineering for Gas Turbines and Power 125, no. 2 (2003): 572–79. http://dx.doi.org/10.1115/1.1563239.

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A technique which uses trained neural nets to model the compressor in the context of a turbocharged diesel engine simulation is introduced. This technique replaces the usual interpolation of compressor maps with the evaluation of a smooth mathematical function. Following presentation of the methodology, the proposed neural net technique is validated against data from a truck type, 6-cylinder 14-liter diesel engine. Furthermore, with the introduction of an additional parameter, the proposed neural net can be trained to simulate an entire family of compressors. As a demonstration, a family of co

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3

Sehra, A., J. Bettner, and A. Cohn. "Design of a High-Performance Axial Compressor for Utility Gas Turbine." Journal of Turbomachinery 114, no. 2 (1992): 277–86. http://dx.doi.org/10.1115/1.2929141.

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An aerodynamic design study to configure a high-efficiency industrial-size gas turbine compressor is presented. This study was conducted using an advanced aircraft engine compressor design system. Starting with an initial configuration based on conventional design practice, compressor design parameters were progressively optimized. To improve the efficiency potential of this design further, several advanced design concepts (such as stator ends bends and velocity controlled airfoils) were introduced. The projected poly tropic efficiency of the final advanced concept compressor design having 19

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4

Broichhausen, K. D., H. E. Gallus, and R. Mo¨nig. "Off-Design Performance of Supersonic Compressors With Fixed and Variable Geometry." Journal of Turbomachinery 110, no. 3 (1988): 312–21. http://dx.doi.org/10.1115/1.3262197.

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Regarding the extremely high pressure ratios of jet-engine compressors for the next decade, increasing interest belongs to the further development of supersonic compressors with supersonic relative flow at rotor inlet and supersonic absolute flow at stator inlet. In the past, different suitable design procedures for these components have been developed and tested successfully. However, there is a lack of information concerning the off-design performance of supersonic compressors. The present paper first systematically shows blading and flow path geometry of different experimentally investigate

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5

Muir, D. E., H. I. H. Saravanamuttoo, and D. J. Marshall. "Health Monitoring of Variable Geometry Gas Turbines for the Canadian Navy." Journal of Engineering for Gas Turbines and Power 111, no. 2 (1989): 244–50. http://dx.doi.org/10.1115/1.3240243.

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The Canadian Department of National Defence has identified a need for improved Engine Health Monitoring procedures for the new Canadian Patrol Frigate (CPF). The CPF propulsion system includes two General Electric LM2500 gas turbines, a high-pressure-ratio engine with multiple stages of compressor variable geometry. A general method for predicting the thermodynamic performance of variable geometry axial compressors has been developed. The new modeling technique is based on a meanline stage-stacking analysis and relies only on the limited performance data typically made available by engine manu

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6

Tesfamichael Baheta, Aklilu, S. I. Gilani, and Shaharin Anwar Sulaiman. "Performance Evaluation of a Variable Geometry Gas Turbine in a CHP Plant." Applied Mechanics and Materials 798 (October 2015): 59–63. http://dx.doi.org/10.4028/www.scientific.net/amm.798.59.

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This study is to develop mathematical models and evaluate the performance of a gas turbine with variable geometry compressor working in a CHP plant. A single shaft gas turbine plant can maintain the exhaust gas temperature if the load is not below 50 % of the full load by simultaneously regulating the compressor variable vanes position and fuel flow. For load less than 50% the engine is running to meet the power demand. This is achieved by controlling the fuel flow and air bleed at the downstream of the compressor to avoid surge formation while variable vanes are opened fully. To accommodate c

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7

Wirkowski, Paweł. "Modelling the characteristics of axial compressor of variable flow passage geometry, working in the gas turbine engine system." Polish Maritime Research 14, no. 3 (2007): 27–32. http://dx.doi.org/10.2478/v10012-007-0015-z.

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Modelling the characteristics of axial compressor of variable flow passage geometry, working in the gas turbine engine system This paper concerns application of mathematical modelling methods to analyzing gas-dynamic processes in marine gas turbines. Influence of geometry changes in axial compressor flow passage on kinematical air flow characteristics, are presented. The elaborated mathematical model will make it possible to realize - in the future - simulative investigations of gas-dynamic processes taking place in a compressor fitted with controllable guide vanes.

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8

Song, Kang, Devesh Upadhyay, and Hui Xie. "A physics-based turbocharger model for automotive diesel engine control applications." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 233, no. 7 (2018): 1667–86. http://dx.doi.org/10.1177/0954407018770569.

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Control-oriented models of turbocharger processes such as the compressor mass flow rate, the compressor power, and the variable geometry turbine power are presented. In a departure from approaches that rely on ad hoc empirical relationships and/or supplier provided performance maps, models based on turbomachinery physics and known geometries are attempted. The compressor power model is developed using Euler’s equations of turbomachinery, where the gas velocity exiting the rotor is estimated from an empirically identified correlation for the ratio between the radial and tangential components of

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9

Whitfield, A., and A. H. Abdullah. "The Performance of a Centrifugal Compressor With High Inlet Prewhirl." Journal of Turbomachinery 120, no. 3 (1998): 487–93. http://dx.doi.org/10.1115/1.2841744.

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The performance requirements of centrifugal compressors usually include a broad operating range between surge and choke. This becomes increasingly difficult to achieve as increased pressure ratio is demanded. In order to suppress the tendency to surge and extend the operating range at low flow rates, inlet swirl is often considered through the application of inlet guide vanes. To generate high inlet swirl angles efficiently, an inlet volute has been applied as the swirl generator, and a variable geometry design developed in order to provide zero swirl. The variable geometry approach can be app

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10

Whitfield, A., and A. J. Sutton. "The Effect of Vaneless Diffuser Geometry on the Surge Margin of Turbocharger Compressors." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 203, no. 2 (1989): 91–98. http://dx.doi.org/10.1243/pime_proc_1989_203_154_02.

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A study into the effect of two methods of changing the geometry of a vaneless diffuser on the performance of the compressor of a road haulage diesel engine turbocharger is described. The development of compressor variable geometry will enable the full potential of variable geometry turbines to be realized. This will give a more flexible power unit which will provide, for example, better low-speed torque and hence a smaller gearbox, and shorter journey times or larger payloads than are currently the practice. The disadvantages are added complexity and cost in the relatively simple turbocharger,

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11

Salvage, J. W. "Development of a Centrifugal Compressor With a Variable Geometry Split-Ring Pipe Diffuser." Journal of Turbomachinery 121, no. 2 (1999): 295–304. http://dx.doi.org/10.1115/1.2841314.

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Higher noise levels resulted when a compressor was scaled to larger capacity. The machine’s sound pressure level was relieved by increasing the distance between the impeller blade tip and diffuser leading edge. However, the part-load surge line deteriorated severely as a consequence. A variable geometry pipe diffuser solved this problem, permitting operation at stringent off-design conditions. The addition of a variable diffuser permits compressor selection very near its most efficient full-load operating point, without regard for limitations normally imposed by part-load requirements. The pri

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12

Huang, Qiangqiang, and Xinqian Zheng. "Potential of Variable-Geometry Method for Compressor Range Extension for Turbocharged Engines." Journal of Propulsion and Power 33, no. 5 (2017): 1197–206. http://dx.doi.org/10.2514/1.b36004.

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13

Wöhr, Michael, Elias Chebli, Markus Müller, Hans Zellbeck, Johannes Leweux, and Andreas Gorbach. "Development of a turbocharger compressor with variable geometry for heavy-duty engines." International Journal of Engine Research 16, no. 1 (2014): 23–30. http://dx.doi.org/10.1177/1468087414562457.

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14

Tsalavoutas, A., K. Mathioudakis, A. Stamatis, and M. Smith. "Identifying Faults in the Variable Geometry System of a Gas Turbine Compressor." Journal of Turbomachinery 123, no. 1 (2000): 33–39. http://dx.doi.org/10.1115/1.1330267.

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The influence of faults in the variable geometry (variable stator vanes) system of a multistage axial compressor on the performance of an industrial gas turbine is investigated. An experimental investigation has been conducted, by implanting such faults into an operating gas turbine. The faults examined are individual stator vane mistunings of different magnitudes and located at different stages. Fault identification is based on the aerothermodynamic measurement data and is achieved by employing two different techniques, namely adaptive performance modeling and monitoring the circumferential d

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15

Zeng, Tao, and Guoming G. Zhu. "Control-oriented turbine power model for a variable-geometry turbocharger." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 232, no. 4 (2017): 466–81. http://dx.doi.org/10.1177/0954407017702996.

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A control-oriented model for the variable-geometry turbocharger is critical for model-based variable-geometry turbocharger control design. Typically, the variable-geometry turbocharger turbine power is modeled with a fixed mechanical efficiency of the turbocharger on the assumption of an isentropic process. The fixed-efficiency approach is an oversimplification and may lead to modeling errors because of an overpredicted or underpredicted compressor power. This leads to the use of lookup-table-based approaches for defining the mechanical efficiency of the turbocharger. Unfortunately, since the

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16

Jiao, K., H. Sun, X. Li, et al. "Numerical investigation of the influence of variable diffuser vane angles on the performance of a centrifugal compressor." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 223, no. 8 (2009): 1061–70. http://dx.doi.org/10.1243/09544070jauto1202.

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In this study, the performance of a turbocharger compressor system for light-duty diesels, encompassing the airflow geometry from impeller inlet to volute exit, has been simulated numerically, and the effects of variable diffuser vane angles on the compressor performance and operating range have been investigated. It is found that the angle of the diffuser vane has significant influence on the compressor operating range, and optimized design of the variable diffuser vane angle can increase the stable operating range and improve the compressor efficiency significantly when compared with fixed d

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17

Canova, Marcello, Massimiliano Taburri, Lisa Fiorentini, Fabio Chiara, and Yue-Yun Wang. "Modeling and Analysis of a Turbocharged Diesel Engine with Variable Geometry Compressor System." SAE International Journal of Engines 4, no. 2 (2011): 2405–17. http://dx.doi.org/10.4271/2011-24-0123.

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18

Galindo, J., J. M. Lujan, C. Guardiola, and G. S. Lapuente. "A method for data consistency checking in compressor and variable-geometry turbine maps." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 220, no. 10 (2006): 1465–73. http://dx.doi.org/10.1243/09544070jauto82.

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19

Sanaye, Sepehr, and Salahadin Hosseini. "Off-design performance improvement of twin-shaft gas turbine by variable geometry turbine and compressor besides fuel control." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 7 (2019): 957–80. http://dx.doi.org/10.1177/0957650919887888.

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A novel procedure for finding the optimum values of design parameters of industrial twin-shaft gas turbines at various ambient temperatures is presented here. This paper focuses on being off design due to various ambient temperatures. The gas turbine modeling is performed by applying compressor and turbine characteristic maps and using thermodynamic matching method. The gas turbine power output is selected as an objective function in optimization procedure with genetic algorithm. Design parameters are compressor inlet guide vane angle, turbine exit temperature, and power turbine inlet nozzle g

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20

Camp, T. R., and J. H. Horlock. "An Analytical Model of Axial Compressor Off-Design Performance." Journal of Turbomachinery 116, no. 3 (1994): 425–34. http://dx.doi.org/10.1115/1.2929429.

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An analysis is presented of the off-design performance of multistage axial-flow compressors. It is based on an analytical solution, valid for small perturbations in operating conditions from the design point, and provides an insight into the effects of choices made during the compressor design process on performance and off-design stage matching. It is shown that the mean design value of stage loading coefficient (ψ = Δh0/U2) has a dominant effect on off-design performance, whereas the stage-wise distribution of stage loading coefficient and the design value of flow coefficient have little inf

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21

Justen, F., K. U. Ziegler, and H. E. Gallus. "Experimental Investigation of Unsteady Flow Phenomena in a Centrifugal Compressor Vaned Diffuser of Variable Geometry." Journal of Turbomachinery 121, no. 4 (1999): 763–71. http://dx.doi.org/10.1115/1.2836730.

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The behavior of vaned radial diffusers is generally considered to be due to the flow phenomena in the vaneless and the semi-vaned space in the diffuser inlet region. Even considering unsteady aspects, the adjacent diffuser channel is regarded as less important. The flat wedge vaned diffuser of the centrifugal compressor stage investigated allows an independent continuous adjustment of the diffuser vane angle and the radial gap between impeller outlet and diffuser vane inlet, so that information about the importance of these geometric parameters can be obtained. The time-dependent pressure dist

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22

Li, Xu, Chuanlei Yang, Yinyan Wang, and Hechun Wang. "A prediction model of compressor with variable-geometry diffuser based on elliptic equation and partial least squares." Royal Society Open Science 5, no. 1 (2018): 171468. http://dx.doi.org/10.1098/rsos.171468.

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To achieve a much more extensive intake air flow range of the diesel engine, a variable-geometry compressor (VGC) is introduced into a turbocharged diesel engine. However, due to the variable diffuser vane angle (DVA), the prediction for the performance of the VGC becomes more difficult than for a normal compressor. In the present study, a prediction model comprising an elliptical equation and a PLS (partial least-squares) model was proposed to predict the performance of the VGC. The speed lines of the pressure ratio map and the efficiency map were fitted with the elliptical equation, and the

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23

Zhou, Junqiang, Lisa Fiorentini, and Marcello Canova. "Model-based optimisation and predictive control of a turbocharged diesel engine with variable geometry compressor." International Journal of Powertrains 5, no. 2 (2016): 167. http://dx.doi.org/10.1504/ijpt.2016.076559.

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24

Wiggins, J. O. "The “Axi-Fuge”—A Novel Compressor." Journal of Turbomachinery 108, no. 2 (1986): 240–43. http://dx.doi.org/10.1115/1.3262043.

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Modifying a simple-cycle gas turbine to include heat exchangers can improve its thermal efficiency significantly (as much as 20 percent). Advanced regenerative and intercooled regenerative gas turbines for marine application have recently been the subject of numerous studies, most of which have shown that lower fuel consumption can be achieved by adding heat exchangers to existing simple-cycle gas turbines. Additional improvements in thermal efficiency are available by increasing the efficiency of the turbomachinery itself, particularly that of the gas turbine’s air compressor. Studies by Cate

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25

Zhang, Zhongjie, Ruilin Liu, Guangmeng Zhou, et al. "Influence of varying altitudes on matching characteristics of the Twin-VGT system with a diesel engine and performance based on analysis of available exhaust energy." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 234, no. 7 (2019): 1972–85. http://dx.doi.org/10.1177/0954407019876220.

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A variable geometry turbocharger in series with a variable geometry turbocharger (Twin-VGT) system was designed to improve engine power at high altitudes. The influence of altitudes on the performance of the Twin-VGT system was investigated in the perspective of available exhaust energy. The interaction between exhaust flow characteristics of Twin-VGT and openings of Twin-VGT vanes was theoretically analyzed at different altitudes. Meanwhile, a model of a diesel engine matched with the Twin-VGT system was built to study the matching performance of the Twin-VGT system with engine at different a

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26

Thomas, Anand Mammen, Jensen Samuel J., Paul Pramod M., A. Ramesh, R. Murugesan, and A. Kumarasamy. "Simulation of a Diesel Engine with Variable Geometry Turbocharger and Parametric Study of Variable Vane Position on Engine Performance." Defence Science Journal 67, no. 4 (2017): 375. http://dx.doi.org/10.14429/dsj.67.11451.

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Modelling of a turbocharger is of interest to the engine designer as the work developed by the turbine can be used to drive a compressor coupled to it. This positively influences charge air density and engine power to weight ratio. Variable geometry turbocharger (VGT) additionally has a controllable nozzle ring which is normally electro-pneumatically actuated. This additional degree of freedom offers efficient matching of the effective turbine area for a wide range of engine mass flow rates. Closing of the nozzle ring (vanes tangential to rotor) result in more turbine work and deliver higher b

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27

Palmer, D. L., and W. F. Waterman. "Design and Development of an Advanced Two-Stage Centrifugal Compressor." Journal of Turbomachinery 117, no. 2 (1995): 205–12. http://dx.doi.org/10.1115/1.2835648.

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This paper describes the aeromechanical design and development of a 3.3 kg/s (7.3 lb/sec), 14:1 pressure ratio two-stage centrifugal compressor, which is used in the T800-LHT-800 helicopter engine. The design employs highly nonradial, splitter bladed impellers with swept leading edges and compact vaned diffusers to achieve high performance in a small and robust configuration. The development effort quantified the effects of impeller diffusion and passive inducer shroud bleed on surge margin as well as the effects of impeller loading on tip clearance sensitivity and the impact of sand erosion a

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28

Jiang, P. M., and A. Whitfield. "Investigation of Vaned Diffusers as a Variable Geometry Device for Application to Turbocharger Compressors." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 206, no. 3 (1992): 209–20. http://dx.doi.org/10.1243/pime_proc_1992_206_179_02.

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The potential of guide vanes as a variable geometry device, placed in the conventional vaneless diffuser, to extend the operating range of a turbocharger compressor is investigated. Vaned diffusers are not normally employed in turbocharger applications as the consequent reduction in operating range is more damaging than the beneficial improvement in peak efficiency and pressure ratio. The variable geometry concept considered here is primarily one in which the guide vanes are introduced at the near surge flow conditions. The leading edge vane angle is set to accept the highly tangential flow at

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29

Zhou, Junqiang, Lisa Fiorentini, Marcello Canova, and Yue-Yun Wang. "Coordinated Performance Optimization of a Variable Geometry Compressor With Model Predictive Control for a Turbocharged Diesel Engine." IEEE Transactions on Control Systems Technology 24, no. 3 (2016): 804–16. http://dx.doi.org/10.1109/tcst.2015.2468085.

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30

Camporeale, S. M., B. Fortunato, and A. Dumas. "Dynamic modelling of recuperative gas turbines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 214, no. 3 (2000): 213–25. http://dx.doi.org/10.1243/0957650001538317.

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This paper describes the mathematical model and the computational procedure adopted for the development of a modularly structured computer code able to simulate the dynamic behaviour of recuperative gas turbine power plants. For accurate simulation of the turbine components, the model includes a stage-by-stage procedure for the air-cooled turbine based on the blade geometry and the characteristics of the cooling system. The counter-flow surface heat exchanger, assumed as recuperator, is described by a set of partial differential equations, giving à One-dimensional description of the temperatur

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31

Gottschall, M., and K. Vogeler. "Vortex development induced by part gap geometry and endwall configurations for variable stator vanes in a compressor cascade." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 227, no. 6 (2013): 692–702. http://dx.doi.org/10.1177/0957650913495539.

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32

Gro¨nstedt, U. T. J., and P. Pilidis. "Control Optimization of the Transient Performance of the Selective Bleed Variable Cycle Engine During Mode Transition." Journal of Engineering for Gas Turbines and Power 124, no. 1 (2000): 75–81. http://dx.doi.org/10.1115/1.1394965.

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The transient performance of the selective bleed variable cycle engine (VCE) has been optimized during the transition from subsonic to supersonic mode. The selective bleed VCE concept has been developed with a short take-off vertical landing (STOVL) aircraft in mind and the engine is characterized by its twin mode VCE feature. The transition optimization is constrained by the requirement of maintaining thrust and compressor surge margins. The engine variable geometry component schedules and the fuel flow are used as optimization variables. A differential algebraic formulation of an inter-compo

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33

Zhu, Dengting, Yun Lin, and Xinqian Zheng. "Strategy on performance improvement of inverse Brayton cycle system for energy recovery in turbocharged diesel engines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 1 (2019): 85–95. http://dx.doi.org/10.1177/0957650919847920.

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The inverse Brayton cycle is a potential technology for waste heat energy recovery. It consists of three components: one turbine, one heat exchanger, and one compressor. The exhaust gas is further expanded to subatmospheric pressure in the turbine, and then cooled in the heat exchanger, last compressed in the compressor into the atmosphere. The process above is the reverse of the pressurized Brayton cycle. This work has presented the strategy on performance improvement of the inverse Brayton cycle system for energy recovery in turbocharged diesel engines, which has pointed the way to the futur

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34

Rane, Sham, Ahmed Kovačević, and Nikola Stošić. "Grid Generation for CFD Analysis and Design of a Variety of Twin Screw Machines." Designs 3, no. 2 (2019): 30. http://dx.doi.org/10.3390/designs3020030.

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A detailed study of the fluid flow and thermodynamic processes in positive displacement machines requires 3D CFD modeling in order to capture their real geometry, including leakage gaps. However, limitations in the conventional computational grids, used in commercial software packages, exclude their use for classical twin screw machines. The screw compressor rotor grid generator (SCORG) is a customized grid generation tool developed to overcome these limitations. This paper shows how it can be further extended to include non-conventional rotor designs, such as those with variable lead or profi

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35

Eggers, Torben, Hye Rim Kim, Simon Bittner, Jens Friedrichs, and Joerg R. Seume. "Aerodynamic and Aeroelastic Effects of Design-Based Geometry Variations on a Low-Pressure Compressor." International Journal of Turbomachinery, Propulsion and Power 5, no. 4 (2020): 26. http://dx.doi.org/10.3390/ijtpp5040026.

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In modern aircraft engines, the low-pressure compressor (LPC) is subjected to a flow characterized by strong wakes and secondary flows from the upstream fan. This concerns ultra-high bypass ratio (UHBR) turbofan engines, in particular. This paper presents the aerodynamic and aeroelastic sensitivities of parametric variations on the LPC, driven by the design considerations in the upstream fan. The goal of this investigation was to determine the influence of design-based geometry parameter variations on the LPC performance under realistic inlet flow distributions and the presence of an s-duct. A

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Benvenuti, Erio. "Design and Test of a New Axial Compressor for the Nuovo Pignone Heavy-Duty Gas Turbines." Journal of Engineering for Gas Turbines and Power 119, no. 3 (1997): 633–39. http://dx.doi.org/10.1115/1.2817031.

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This axial compressor design was primarily focused to increase the power rating of the current Nuovo Pignone PGT10 Heavy-Duty gas turbine by 10 percent. In addition, the new 11-stage design favorably compares with the existing 17-stage compressor in terms of simplicity and cost. By scaling the flowpath and blade geometry, the new aerodynamic design can be applied to gas turbines with different power ratings as well. The reduction in the stage number was achieved primarily through the meridional flowpath redesign. The resulting higher blade peripheral speeds achieve larger stage pressure ratios

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37

Coppinger, M., and E. Swain. "Performance prediction of an industrial centrifugal compressor inlet guide vane system." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 214, no. 2 (2000): 153–64. http://dx.doi.org/10.1243/0957650001538254.

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Variable inlet guide vanes (VIGVs) can significantly extend the stable operating range of industrial centrifugal compressors as a result of imparting swirl to the inlet flow. Typical setting angles range from −20° to +80°; therefore the vanes are normally made from flat plate. An undesirable consequence of the large setting angles required by the vanes is a pressure loss, leading to a decrease in the overall stage efficiency. An ideal inlet guide vane system will therefore induce large swirl angles in the inlet flow with a low associated pressure loss. Efforts have been made to determine the p

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CIEŚLIKOWSKI, Bogusław, Mariusz CYGNAR, and Janusz JAKÓBIEC. "Multifaceted diagnostic inference process for identifying the causes of self-ignition engine faults resulting from PM sediments." Combustion Engines 168, no. 1 (2017): 186–90. http://dx.doi.org/10.19206/ce-2017-130.

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Optimization of the fuel combustion process in a self-ignition engine with the multi-stage HPCR injection system sets the main trends in research on the thermodynamic stability of fuels, and the mechanisms of PM formation. The stages were indicated of the multifaceted diagnostic inference on the causes of failures of a turbocharger with variable geometry (VTG) which occur as a result of PM sedimentation in the nozzle area. An evaluation of the engine performance was conducted using a dedicated tester and an additional recording of the injector coil current characteristics with parallel reading

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39

Kvasha, Yu A., and N. A. Zinevych. "On the effect of the meridional contour shape on the power characteristics of a centrifugal compressor wheel." Technical mechanics 2020, no. 3 (2020): 12–17. http://dx.doi.org/10.15407/itm2020.03.012.

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This work is concerned with the development of approaches to the optimal aerodynamic design of centrifugal compressor wheels, which is due to the use of centrifugal stages in compressors of modern aircraft gas turbine engines and power plants. The aim of this work is a computational study of the effect of the meridional contour shape of a centrifugal compressor wheel on its power characteristics. The basic method is a numerical simulation of 3D turbulent gas flows in centrifugal wheels on the basis of the complete averaged Navier¬–Stokes equations and a two-parameter turbulence model. The comp

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Eynon, P. A., and A. Whitfield. "The effect of low-solidity vaned diffusers on the performance of a turbocharger compressor." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 211, no. 5 (1997): 325–39. http://dx.doi.org/10.1243/0954406971522088.

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The design of low-solidity diffuser vanes and the effect on the performance of a turbo-charger compressor is discussed. The effect of vane number and turning angle was investigated while maintaining a basic design with a solidity of 0.69 and a leading edge angle of 75°. This large leading edge angle was specifically chosen so that the vane would be aligned with the low flowrates close to surge. Tests were initially conducted with six, eight and ten vanes and a turning angle of 10°. Based on these results the ten-vane design was selected for further investigation with 15 and 20° of vane turning

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Kim, T. S., and S. T. Ro. "The effect of gas turbine coolant modulation on the part load performance of combined cycle plants. Part 1: Gas turbines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 211, no. 6 (1997): 443–51. http://dx.doi.org/10.1243/0957650981537339.

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This paper demonstrates a favourable influence of turbine coolant modulation on the part load performance of gas turbines. A general simulation programme is developed, which is capable of accurately estimating the design and part load performance of modern heavy-duty gas turbines characterized by intensive turbine blade cooling Investigations are made for a typical gas turbine and two distinct load control schemes are considered: the fuel-only control and the variable compressor geometry control. Maintaining blade temperatures as high as possible whose purpose is to minimize coolant consumptio

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Kim, T. S., and S. T. Ro. "The effect of gas turbine coolant modulation on the part load performance of combined cycle plants. Part 2: Combined cycle plant." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 211, no. 6 (1997): 453–59. http://dx.doi.org/10.1243/0957650981537348.

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For combined cycle plants that consist of heavy-duty gas turbine and single-pressure heat recovery steam generator, the effect of gas turbine coolant modulation on plant performance is analysed. Two distinct schemes for gas turbine load control are adopted (the fuel-only control and the variable compressor geometry control), based on the gas turbine calculation in Part 1 of this series of papers. Models for heat recovery steam generator and steam turbine are combined with the gas turbine models of Part 1 to result in a complete analysis routine for combined cycles. The purpose of gas turbine c

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Wang, Haoping, Qiankun Qu, and Yang Tian. "Nonlinear observer based sliding mode control and oxygen fraction estimation for diesel engine." Transactions of the Institute of Measurement and Control 40, no. 7 (2017): 2227–39. http://dx.doi.org/10.1177/0142331217700242.

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In this paper, a nonlinear observer based sliding mode control (NOSMC) approach for air-path and a model-based observer for oxygen concentration in the diesel engine equipped with a variable geometry turbocharger and exhaust gas recirculation is introduced. We propose a less conservative observer design technique for Lipschitz nonlinear systems using Ricatti equations. The observer gains are obtained by solving the linear matrix inequality (LMI). Then a robust nonlinear control method, sliding mode control is applied for the states of intake and exhaust manifold pressure and compressor mass fl

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Hashmi, Muhammad Baqir, Tamiru Alemu Lemma, and Zainal Ambri Abdul Karim. "Investigation of the Combined Effect of Variable Inlet Guide Vane Drift, Fouling, and Inlet Air Cooling on Gas Turbine Performance." Entropy 21, no. 12 (2019): 1186. http://dx.doi.org/10.3390/e21121186.

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Variable geometry gas turbines are susceptible to various malfunctions and performance deterioration phenomena, such as variable inlet guide vane (VIGV) drift, compressor fouling, and high inlet air temperatures. The present study investigates the combined effect of these performance deterioration phenomena on the health and overall performance of a three-shaft gas turbine engine (GE LM1600). For this purpose, a steady-state simulation model of the turbine was developed using a commercial software named GasTurb 12. In addition, the effect of an inlet air cooling (IAC) technique on the gas turb

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Doyle, Timothy J., Raymond W. Kornbau, and Arthur L. Smookler. "Surface Ship Machinery—A Survey of Propulsion, Electrical, and Auxiliary System Development." Marine Technology and SNAME News 29, no. 03 (1992): 115–43. http://dx.doi.org/10.5957/mt1.1992.29.3.115.

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Propulsion, auxiliary, and electric machinery developments for surface combatants are surveyed---overall system characteristics are covered to permit a broad coverage of related activities. Prime movers in both propulsion and ship service sizes are discussed. All will demonstrate improved economy, especially at part power, and increased attention to thermal and acoustic signatures. Gas turbines are the source of propulsion power, but diesels join turbines in ship service application. Electric drives may be selected where machinery is widely separated or geometries are restrictive. Reversing mo

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Song, Kang, Devesh Upadhyay, and Hui Xie. "Control of diesel engines with electrically assisted turbocharging through an extended state observer based nonlinear MPC." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 233, no. 2 (2017): 378–95. http://dx.doi.org/10.1177/0954407017744145.

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A two-layer controller for a diesel engine equipped with an electrically assisted turbocharger is proposed. A previously identified control-oriented plant model is used for control design. A GT-SUITE based high fidelity engine model is used as the plant. The high-level controller is designed based on the active disturbance rejection control method and uses an extended state observer for added robustness. The high-level controller tracks the boost pressure and intake manifold oxygen concentration. The low-level controller seeks to deliver the desired compressor power through an optimal affine s

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Leinhos, Dirk C., Norbert R. Schmid, and Leonhard Fottner. "The Influence of Transient Inlet Distortions on the Instability Inception of a Low-Pressure Compressor in a Turbofan Engine." Journal of Turbomachinery 123, no. 1 (2000): 1–8. http://dx.doi.org/10.1115/1.1330271.

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While studies on compressor flow instabilities under the presence of inlet distortions have been carried out with steady distortions in the past, the investigation presented here focuses on the influence of transient inlet distortions as generated by variable geometry engine intakes of super- and hypersonic aircraft on the characteristic and the nature of the instability inception of a LPC. The flow patterns (total pressure distortion with a superimposed co- or counterrotating swirl) of the distortions are adopted from a hypersonic concept aircraft. A LARZAC 04 twin-spool turbofan was operated

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Stein, W., and M. Rautenberg. "Analysis of Measurements in Vaned Diffusers of Centrifugal Compressors." Journal of Turbomachinery 110, no. 1 (1988): 115–21. http://dx.doi.org/10.1115/1.3262156.

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In vaned diffusers of centrifugal compressors many different flow phenomena interfere with one another, and different geometric parameters influence the flow field. Variations of these parameters allow the designer to optimize the diffuser for a certain application or to use a variable geometry for controlling the stage over a wide range. Two vaned diffusers that differ only in their passage widths are investigated using different types of measuring technique, in order to analyze the flow structure and to use it as a verification of a calculation method that allows detailed predictions of flow

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Morgan, G., G. Rzevski, and P. Wiese. "Multiagent control of variable geometry axial turbo compressors." Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 218, no. 3 (2004): 157–71. http://dx.doi.org/10.1177/095965180421800301.

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Nosov, N. V., N. P. Kostin, and R. V. Ladyagin. "Estimation of texture parameters for the precision surfaces using the quasioptimal correlation algorithms." Vektor nauki Tol'yattinskogo gosudarstvennogo universiteta, no. 1 (2021): 24–31. http://dx.doi.org/10.18323/2073-5073-2021-1-24-31.

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The authors considered a new method of texture analysis of machined precision surfaces based on using computer optics and the autocorrelation method of processing the images of micro-relief textures under the study. This method is based on a probabilistic comparative evaluation of the unknown texture of the micro-relief under the investigation with the available textures of reference micro-patterns, in which microrelief parameters are determined. The paper proposes an approach to identify the profile surface roughness of a gas turbine engine (GTE) blade after vibro-contact polishing according

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