On the Design and Matching of Turbocharger Single Scroll Turbines for Pass Car Gasoline Engines

Gugau, Marc; Roclawski, Harald

doi:10.1115/1.4027710

Cited by 7 publications

(2 citation statements)

References 6 publications

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“…Nowadays, flow unsteadiness is considered damaging for turbine performance. However, Gugau & Roclawski (2012) suggest that an over-torque can be recovered by the rotor, while Binder et al (2013) notice that the rotor response is unusually high for some opening of guide vane. However, no explanation is given on the nature of the physical phenomenon.…”

Section: Introductionmentioning

confidence: 99%

Transient flow in infinitely thin airfoil cascade

Hermet

Binder

Gressier

2019

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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Pulsed flows in turbines have many industrial applications. However, the influence of pulsed flow on turbine performance is complex and imperfectly understood. There is no clear consensus in the literature regarding generic trends. Those are difficult to extract since a majority of studies are based on industrial geometries, which involve strong interactions between many physical phenomena. In order to isolate and understand the main expression of the physics, the problem is simplified and an investigation is carried out on the severe transient regime inside a thin airfoil cascade, caused by a sudden change of inlet conditions, without viscosity effect. Different time scales of the inlet perturbation are examined, from a sudden step of the flow features to a more progressive ramp. The consequences of the different regimes observed inside the flow regarding some indicators of performance are detailed. Finally, the characteristic time of the transient flow is isolated and proposed as an indicator to assess the relevance of the quasi-steady assumption.

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Section: Introductionmentioning

confidence: 99%

Transient flow in infinitely thin airfoil cascade

Hermet

Binder

Gressier

2019

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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“…Kong et al [2] work were on fuzzy logic and they used the fuzzy approaches for searching optimal component matching point in gas turbine performance simulation. Gugau and Roclawskip [3] have used an optimization software for producing the matching maps that fits turbine and compressor (turbocharger) to the internal combustion gasoline engine, and keeps fuel consumption low at all engine speeds. Tsoutsanis et al [4] developed a novel compressor map generation method, with the primary objective of improving the accuracy and fidelity of the engine model performance prediction.…”

Section: Matching Proceduresmentioning

confidence: 99%

A New Approach of Gas Turbine Component Matching for Electrical Power Generation

Ebaid¹,

Al-Hamdan²

2017

IJMEA

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Abstract:Gas turbines are often required to operate at different power levels and under varying environmental conditions.But by the nature of the thermodynamic processes in the engine, it is not possible to obtain the same level of efficiency within the entire range of operation. Therefore, depending on the particular application, for example for power generation, the rotational speed would be constant and dictated by the electrical generating machine. Gas turbine engine consists of various components which are linked together in such a way that there exists a mechanical and thermodynamic interdependence among some components. This means that some operational compatibility (matching) between components will be required for a steady state or equilibrium operation. The steady state of gas turbine engine for power generation can be achieved by the matching of its compressor and turbine. The usual approach of matching the compressor and the turbine is usually based on using an iterative procedure to determine the turbine operating points which are then plotted on the compressor characteristics. The draw back of this process is being laborious and time consuming. The new approach developed overcomes this by superimposing the turbine performance characteristics on the compressor performance characteristics while meeting the components matching conditions. This can be done by introducing a new mass flow dimensionless parameter. Superimposing the turbine map on the compressor map cannot be totally accepted until both maps axes (the abscissa and the ordinate) are identical. This paper explains the new approach adopted to a single shaft gas turbine engine. Theoretically, the developed techniques can be applied to other gas turbine engines.

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Development and validation of a radial turbine efficiency and mass flow model at design and off-design conditions

Serrano

Arnau

Dombrovsky

et al. 2016

Energy Conversion and Management

118

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ElsevierSerrano Cruz, JR.; Arnau Martínez, FJ.; García-Cuevas González, LM.; Dombrovsky, A.; Tartoussi, H. (2016). Development and validation of a radial turbine efficiency and mass flow model at design and off-design conditions. Energy Abstract Turbine performance at extreme off-design conditions is growing in importance for properly computing turbocharged reciprocating internal combustion engines behaviour during urban driving conditions at current and future homologation cycles. In these cases, the turbine operates at very low flow rates and power outputs and at very high blade to jet speed ratios during transitory periods due to turbocharger wheel inertia and the high pulsation level of engine exhaust flow. This paper presents a physically based method that is able to extrapolate radial turbines reduced mass flow and adiabatic efficiency in blade speed ratio, turbine rotational speed and stator vanes position. The model uses a very narrow range of experimental data from turbine maps to fit the necessary coefficients. By using a special experimental turbocharger gas stand, experimental data have been obtained for extremely low turbine power outputs for the sake of model validation. Even if the data used for fitting only covers the turbine normal operation zone, the extrapolation model provides very good agreement with the experiments at very high blade speed ratio points; producing also good results when extrapolating in rotational speed and stator vanes position. RPerfect gas constant (Jkg −1 K −1 ) r Rotor radius (m) sd Standard deviation (−) 12 provided by manufacturers as a standard practice. Turbine maps are necessary 13 when using 1D or 0D modelling tools to predict the whole engine behaviour. In 14 1D modelling approach the one-dimensional unsteady non-homentropic mass, 15 momentum and energy conservation laws (Euler equations) are solved. Specific 16 source terms are used to simulate the friction and heat exchange in the pipes. 17 The 1D simulation codes make possible the calculation of gas dynamics engine 18 behaviour at low computational costs. Some engine components are modelled 19 4 with a 0D approach, using specific lumped parameter models or performance 20 maps. That is the case of cylinders, injectors, valves, compressors and turbines 21 which are coupled to the 1D computational domain as it is described in [4]. 22 For that reason, turbocharged ICE designers must rely on map extrapolation 23 tools when predicting engine performance outside of turbine design operative 24 conditions [5]. It is typical in pulsating flow conditions, requiring different mod-25 elling approaches similar to the proposed in [6], where meanline one-dimensional 26 models are discussed and in [7], where non-adiabatic pressure loss boundary con-27 dition is discussed. One-dimensional tools are also used in design process for 28 fast evaluation of turbine capabilities as in [8]. In [9] a Taylor series expansion 29 is used to develop a model able of predicting mass flow parameter of radial 30 turbines. 31 CFD models for turb...

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On the Design and Matching of Turbocharger Single Scroll Turbines for Pass Car Gasoline Engines

Cited by 7 publications

References 6 publications

Transient flow in infinitely thin airfoil cascade

Transient flow in infinitely thin airfoil cascade

A New Approach of Gas Turbine Component Matching for Electrical Power Generation

Development and validation of a radial turbine efficiency and mass flow model at design and off-design conditions

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