Heavy Duty Gas Turbine Simulation: A Compressor IGV Airfoil Off-Design Characterization

Carcasci, Carlo; Soghe, Riccardo Da; Silingardi, Andrea; Astrua, Pio; Traverso, Stefano

doi:10.1115/gt2010-22628

Cited by 4 publications

(2 citation statements)

References 4 publications

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“…25 Moreover, there are some factors such as generating the proper compressor and turbine maps, the effect of Bleed valve and inlet guide vane (IGV) valve on the compressor map that make the physical modelling problem become more complex. 26,27 One solution is to provide a simplified mathematical model that consists of a set of algebraic equations and simple time delay controllers. 28 However, the applications of gas turbine systems depend greatly on the accuracy of the system model and governor parameters.…”

Section: Gas Turbine Modelling Preliminariesmentioning

confidence: 99%

Automatic model bank selection in multiple model identification of gas turbine dynamics

Hosseini

Fatehi

Sedigh

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part I:

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A multiple model structure of a prototype industrial gas turbine system is constructed under normal operation using a systematic method that incorporates non-linearity measure and H-gap metric tools with the multiple models technique. First, two new non-linearity indices for multiple input-multiple output systems are introduced and employed for decomposing the operating space of a gas turbine into some linear and non-linear modes. The non-linear modes may be further partitioned into some linear modes. The input and output data in each of the linear modes are used to construct an initial multiple model structure. In order to avoid the increase of the number of linear local models, the H-gap metric is extended to multiple input-multiple output systems and used to measure the similarity between linear local models and to merge the similar models. As a result, an algorithm is proposed for construction of multiple linear local models. The algorithm is employed for the identification of a single-shaft prototype industrial gas turbine.

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Section: Gas Turbine Modelling Preliminariesmentioning

confidence: 99%

Automatic model bank selection in multiple model identification of gas turbine dynamics

Hosseini

Fatehi

Sedigh

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part I:

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“…Variable inlet guide vanes (VIGVs) are widely used in axial-flow compressor and other fluid-machines [1][2][3] to provide the requested flow angle into downstream rotor to improve the compressor efficiency and stall margin at off-design conditions. 4,5 Research indicated that as the stagger angle increases the VIGV gradually comes into the high incidence operation conditions and the leading edge velocity spike induced flow separation arises leading to the rapid increase of losslevel, 6,7 which can cause considerable reduction of compressor efficiency. Therefore, some researchers proposed a new VIGV airfoil featuring "dual-peak" surface velocity distribution which can suppress the flow separation and achieve much lower loss-level at high incidence in two-and three-dimensional cases.…”

Section: Introductionmentioning

confidence: 99%

Leading edge redesign of dual-peak type variable inlet guide vane and its effect on aerodynamic performance

Shi

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Recently, a new type airfoil for variable inlet guide vane (VIGV), featuring “dual-peak” surface velocity pattern at high incidence, is proposed and shows wide low-loss operation range. To further improve its performance, this paper researches the influence of leading edge (LE) thickness and shape on the loss level and surface velocity features of the “dual-peak” type airfoil. Firstly, a polynomial-based continuous-curvature leading edge design method was briefly introduced and used in the LE redesign of sample airfoils. Then, steady simulations based on Reynolds-Averaged Navier-Stokes method (RANS), carried out by commercial software CFX after grid independent study, were used to determine the aerodynamic performance, surface velocity distribution and boundary-layer behaviors of all research airfoils. Simulation results indicate that there exists an optimized range of LE relative thickness that can achieve lower airfoil loss level at high incidence condition. For Case 1 ([Formula: see text]) and Case 2 ([Formula: see text]), the optimized LE relative thickness range is [Formula: see text] and [Formula: see text]. The LE shape optimization can further reduce the maximum incidence condition loss coefficient with proportion up to 18% for airfoils with optimal LE thickness. Analysis of flow mechanism indicates that the optimized LE thickness and shape can reduce the suction spike height and subsequent adverse pressure gradient, therefore, decrease the LE separation scale and result in a lower loss coefficient. As an application, a dual peak VIGV with circular LE, presented in previous paper as the optimized VIGV, is redesigned in the LE portion according to the research findings and achieved 0.6 percent improvement in passage-averaged total pressure recovery coefficient [Formula: see text] at extreme high stagger angle point and the low-loss operation range extends with about 5°, which confirms the effectiveness of the research findings in three-dimensional environment.

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A review of unconventional bottoming cycles for waste heat recovery: Part I – Analysis, design, and optimization

Saghafifar

Omar

Mohammadi

et al. 2019

Energy Conversion and Management

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Heavy Duty Gas Turbine Simulation: A Compressor IGV Airfoil Off-Design Characterization

Cited by 4 publications

References 4 publications

Automatic model bank selection in multiple model identification of gas turbine dynamics

Automatic model bank selection in multiple model identification of gas turbine dynamics

Leading edge redesign of dual-peak type variable inlet guide vane and its effect on aerodynamic performance

A review of unconventional bottoming cycles for waste heat recovery: Part I – Analysis, design, and optimization

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