A physics-based turbocharger model for automotive diesel engine control applications

2018 ◽  
Vol 233 (7) ◽  
pp. 1667-1686 ◽  
Author(s):  
Kang Song ◽  
Devesh Upadhyay ◽  
Hui Xie
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Turbine Rotor ◽  
Variable Geometry ◽  
Gas Velocity ◽  
Euler’S Equations ◽  
Variable Geometry Turbine ◽  
Euler's Equations ◽  
Compressor Power

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 the gas velocity. The compressor mass flow rate is modeled based on mass conservation, by approximating the compressor as an adiabatic converging-diverging nozzle with compressible fluid driven by external work input from the compressor wheel. The variable geometry turbine power is developed with Euler’s equations, where the turbine exit swirl and the gas acceleration in the vaneless space are neglected. The gas flow direction into the turbine rotor is assumed to align with the orientation of the variable geometry turbine vane. The gas exit velocity is calculated, similar to the compressor, based on an empirical model for the ratio between the turbine rotor inlet and exit velocities. A power loss model is also proposed that allows proper accounting of power transfer between the turbine and compressor. Model validation against experimental data is presented.

scholarly journals The Preliminary Design of Radial Inflow Turbines

1989 ◽  
Author(s):  
A. Whitfield
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
State Of The Art ◽  
Turbine Rotor ◽  
Working Fluid ◽  
Preliminary Design ◽  
Power Ratio ◽  
Mach Numbers ◽  
Absolute Dimensions

A procedure is described which develops the non-dimensional design of a radial inflow turbine rotor. The design is developed, for any specified non-dimensional power ratio, with the objective of minimising the inlet and discharge Mach numbers so that the passage losses are minimised. Initially state of the art efficiencies are assumed but are later modified through the specification of empirical losses. The resultant non-dimensional design can be transformed to absolute dimensions through the specification of the inlet stagnation conditions and the mass flow rate of the working fluid.

The Preliminary Design of Radial Inflow Turbines

1990 ◽  
Vol 112 (1) ◽  
pp. 50-57 ◽  
Author(s):  
A. Whitfield
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
State Of The Art ◽  
Turbine Rotor ◽  
Working Fluid ◽  
Preliminary Design ◽  
Power Ratio ◽  
Mach Numbers ◽  
Absolute Dimensions

A procedure is described that develops the nondimensional design of a radial inflow turbine rotor. The design is developed, for any specified nondimensional power ratio, with the objective of minimizing the inlet and discharge Mach numbers so that the passage losses are minimized. Initially state-of-the-art efficiencies are assumed, but these are later modified through the specification of empirical losses. The resultant nondimensional design can be transformed to absolute dimensions through the specification of the inlet stagnation conditions and the mass flow rate of the working fluid.

Numerical Investigation of the Effect of Jet-Flaps in a Transonic Turbine Cascade With Subsonic Operating Conditions

2012 ◽  
Author(s):  
Ping-Ping Chen ◽  
Wei-Yang Qiao ◽  
Pu-Wei Wang
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Operating Conditions ◽  
Slot Width ◽  
Design Parameters ◽  
Pressure Loss Coefficient ◽  
Flap Design ◽  
Variable Geometry Turbine ◽  
Jet Blowing

The objective of this article is to analyze numerically the effect of jet-flap on transonic high-pressure turbine cascades, which is one of usable flow control methods for a variable-geometry turbine (VGT). This paper is mainly on the discussion of the effect of different jet-flap design parameters with subsonic operating conditions: jet mass flow rate, jet slot location, jet blowing direction and jet slot width. With two-dimensional steady simulations, the jet-flap changes the cascade turning, the passage throat velocity distribution and throat area effectively, which will then contribute to a different turbine performance. Using a Cm = 2% pressure side (PS) jet-flap with 1.025mm slot width and counter-axial (-x) jet blowing direction, the incoming mass flow rate is diminished by 16.7%, the turning angle augmented by 3.7 degrees, but with an extended total-pressure loss coefficient from 0.05 (no jets) to 0.09.

Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Yunfei Wang ◽  
Huacheng Yuan ◽  
Jinsheng Zhang ◽  
Zhenggui Zhou
Keyword(s):  
Mach Number ◽  
Performance Analysis ◽  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Design Method ◽  
Aerodynamic Performance ◽  
Combined Cycle ◽  
Variable Geometry

Abstract Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet was carried out for tandem scheme turbine-based combined cycle (TBCC) propulsion system. The operation Mach number of the inlet was between 0 and 4. The design point was chosen as Mach number 4.0 in this paper. The determination of external and internal compression and the design method of annular to circle diffuser were illustrated. The inlet was unstart under Ma 3.0 without adjustment. Then, a variable scheme was designed to ensure self-start of the inlet and match the requirement of mass flow rate during the whole flight envelope. And four supports were used to fix the spike. According to the 3D numerical simulations, the total pressure recovery was 0.52 at Ma 4.0 at critical condition and the mass flow rate was consistent with the requirement at different flight Mach number.

Computed Performance Characteristics of Electrofluid Dynamic Colloid Generators

1971 ◽  
Vol 93 (2) ◽  
pp. 183-191
Author(s):  
J. E. Minardi
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Power Output ◽  
Applied Voltage ◽  
Electric Breakdown ◽  
Infinite Plane ◽  
Two Dimensional ◽  
Gas Velocity ◽  
Dynamic Generator

The effects of the electric breakdown limitation on the power output of an electrofluid dynamic generator operating with colloids are studied. The study is performed for both an axisymmetric cylinder of charge and a two-dimensional (Cartesian) slab of charge between infinite, plane, parallel electrodes. The ratio of radius to length or width to length varies from zero to infinity, thus both the so-called slender channels (reference [9]) and broad channels (reference [2]) as well as the intermediate geometries are studied. Normalized power (the value of which is basically limited by electric breakdown) is presented as a function of normalized gas velocity and normalized applied voltage. Also presented is a normalized power per unit mass flow rate as a function of the normalized velocity and voltage. A single chart is sufficient to cover all geometries because the normalized power includes a geometric factor which can be determined from an auxiliary curve to account for the particular geometry.

scholarly journals Kaji Eksperimental Pengunaan R22 dan R410A Berdasarkan Variasi Laku Aliran Massa Pada Mesin AC

2014 ◽  
Vol 9 (2) ◽  
pp. 1
Author(s):  
Dian Wahyu ◽  
Nasrullah - ◽  
Khairul Amri
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Air Conditioning ◽  
Electricity Consumption ◽  
Cooling Effect ◽  
Test Results ◽  
Ac Machines ◽  
Reduce Electricity Consumption ◽  
Compressor Power

The development of the use of air conditioning machines (AC machines) is very high , due to the increased consumption of electricity for household needs are also increasing . Based on field observations of R22 refrigerant is still widely used in commercial air conditioning machines , where the refrigerant has properties that are not friendly to the environment . R410A refrigerant has been recommended to replace worn R22 . It became one of the rationale for conducting the assessment directly to efforts to reduce electricity consumption due to the use of air conditioning machines in the household and the efforts to preserve the environment . The research was conducted on a commercial air conditioning machines by testing the engine for both types of refrigerant ( R22 and R410A ) . Testing the engine characteristics , tested by varying the refrigerant mass flow rate for both refrigerants . The test results showed , electricity consumption ( compressor power ) for the use of both types of refrigerants is similar but uses R410A refrigerant produces a greater cooling effect than by using refrigerant R22 . In Overall effect of the variation of mass flow rate for both refrigerants clearly evident , the increase in mass flow rate causes enhancement of several variables such as the increase in compressor power , cooling effect , the effect of heat release , but for the coeficient of perfomance ( COP ) , the addition of the mass flow rate after COP The optimum value of the COP does not increase anymore . In this study, the highest COP values obtained in the refrigerant mass flow rate 3.4 g / s for R410A and R22 for 1.9 has the highest COP of 1.7 at a flow rate of refrigerant mass 3 g / s . For maximum cooling impact , generated by 0.502 kW to 0.572 kW usage for R22 and R410A.

A Reduced Complexity Model for the Compressor Power of an Automotive Turbocharger

2018 ◽  
Vol 140 (6) ◽  
Author(s):  
Tao Zeng ◽  
Devesh Upadhyay ◽  
Guoming Zhu
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Power Transmission ◽  
Bench Tests ◽  
Operational Conditions ◽  
Low Mass ◽  
Model Compressor ◽  
Compressor Power ◽  
Operational Range

Control-oriented models for automotive turbocharger (TC) compressors typically describe the compressor power assuming an isentropic thermodynamic process with fixed isentropic and mechanical efficiencies for power transmission between the turbine and the compressor. Although these simplifications make the control-oriented model tractable, they also introduce additional errors due to unmodeled dynamics. This is especially true for map-based approaches since the manufacture-provided maps tend to be sparse and often incomplete at the operational boundaries, especially at operational conditions with low mass flow rate and low speed. Extrapolation scheme is often used when the compressor is operated outside the mapped regions, which introduces additional errors. Furthermore, the manufacture-provided compressor maps, based on steady-flow bench tests, could be quite different from those under pulsating engine flow. In this paper, a physics-based model of compressor power is developed using Euler equations for turbomachinery, where the mass flow rate and the compressor rotational speed are used as model inputs. Two new coefficients, speed and power coefficients, are defined. As a result, this makes it possible to directly estimate the compressor power over the entire compressor operational range based on a single analytic relationship. The proposed modeling approach is validated against test data from standard TC flow bench tests, standard supercharger tests, steady-state, and certain transient engine dynamometer tests. Model validation results show that the proposed model has acceptable accuracy for model-based control design and also reduces the dimension of the parameter space typically needed to model compressor dynamics.

Enthalpy Determination Methods for Compressor Performance Calculations

2007 ◽  
Author(s):  
David Ransom ◽  
Klaus Brun ◽  
Rainer Kurz
Keyword(s):  
Equation Of State ◽  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Gas Mixture ◽  
Performance Simulation ◽  
Simple Process ◽  
Compressor Performance ◽  
Determination Methods ◽  
Compressor Power

In the field of compressor performance simulation and measurement, the most commonly used method to evaluate compressor performance is based on the analysis of inlet and discharge pressures and temperatures. Combined with gas mixture properties and known mass flow rate, it is a simple process to determine overall compressor power and efficiency. However, the critical step in this process is the conversion of pressure, temperature, and gas property information into both actual and ideal enthalpy differences. In addition to the abundance of equation of state (EOS) formulations, there are also multiple methods commonly applied for the calculation of the enthalpy differences. This paper reviews several of the methods used for this critical calculation and provides a comparison using multiple gas compositions.

Design and Validation of a Burner With Variable Geometry for Extended Combustion Range

2012 ◽  
Author(s):  
Fabrice Giuliani ◽  
Jakob Woisetschläger ◽  
Thomas Leitgeb
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Measurement Techniques ◽  
Design And Technology ◽  
Variable Geometry ◽  
Atmospheric Conditions ◽  
Stability Range ◽  
University Of Technology ◽  
Core Concepts

A study on innovative gas turbine core concepts supported by the NEWAC project (NEW Aero-engine Core concepts, Integrated Project co-funded by the European Commission within the Sixth Framework Programme under contract No. AIP5-CT-2006-030876) focused on the ability of the combustor to maintain combustion during a drastic reduction of the main air, e.g. due to an active control on the core flow to improve the off-design efficiency. A feasibility study was performed at Graz University of Technology including dimensioning, design and validation of a test burner with variable geometry. A low power premixed methane / air burner with swirl-stabilised flame was chosen, on which the outlet surface and the ratio axial to tangential momentum on the mass flow rate could be controlled. During testing at atmospheric conditions, special attention was paid to the extension of the flammability domain and to the flame dynamics (transition attached-detached, flame stability, blowout limits). It was established for instance that based on this technology, a detached flame can be maintained when reducing the design mass flow rate by 40 per cent within a safe stability range. The paper discusses the background of the study, the burner’s design and technology, the measurement techniques and the results of the validation campaign. A discussion on possible advantages of using variable geometry in a combustion chamber versus conventional technologies closes the paper, taking into account the technical challenges to be met.

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