Physics Based Control Oriented Model for HCCI Combustion Timing

Author(s):  
Mahdi Shahbakhti ◽  
Charles Robert Koch

Incorporating homogeneous charge compression ignition (HCCI) into combustion engines for better fuel economy and lower emission requires understanding the dynamics influencing the combustion timing in HCCI engines. A control oriented model to dynamically predict cycle-to-cycle combustion timing of a HCCI engine is developed. The model is designed to work with parameters that are easy to measure and to have low computation time with sufficient accuracy for control applications. The model is a full-cycle model and consists of a residual gas model, a modified knock integral model, fuel burn rate model, and thermodynamic models. In addition, semi-empirical correlations are used to predict the gas exchange process, generated work and completeness of combustion. The developed model incorporates the thermal coupling dynamics caused by the residual gases from one cycle to the next cycle. The model is parameterized by over 5700 simulations from a detailed thermokinetic model and experimental data obtained from a single-cylinder engine. Cross-validation of the model with both steady-state and transient HCCI experiments for four different primary reference fuel blends is detailed. With seven model inputs, the combustion timing of over 150 different HCCI points is predicted to within an average error of less than 1.5 deg of crank angle. A narrow window of combustion timing is found to provide stable and efficient HCCI operation.

Author(s):  
Mahdi Shahbakhti ◽  
Ahmad Ghazimirsaied ◽  
Charles Robert Koch

Control of Homogeneous Charge Compression Ignition (HCCI) engines to obtain the desirable operation requires understanding of how different charge variables influence the cyclic variations in HCCI combustion. Combustion timing for consecutive cycles at each operating point makes an ensemble of combustion timing which can exhibit different shapes of probability distributions depending on the random and physical patterns existing in the data. In this paper, a combined physical-statistical control-oriented model is developed to predict the distribution of HCCI combustion timing (CA50, crank angle of 50% fuel mass fraction burnt) for a range of operating conditions. The statistical model is based on the Generalized Extreme Value (GEV) distribution and the physical model embodies a modified knock integral model, a fuel burn rate model, a semi-empirical model for the gas exchange process and an empirical model to estimate the combustion timing dispersion. The resulting model is parameterized for the combustion of Primary Reference Fuel (PRF) blends using over 5000 simulations from a detailed thermo-kinetic model. Empirical correlations in the model are parameterized using the experimental data obtained from a single-cylinder engine. Once the model is parameterized it only needs five inputs: intake pressure, intake temperature, Exhaust Gas Recirculation (EGR) rate, equivalence ratio and engine speed. The main outputs of the model are CA50 and the Probability Density Function (PDF) metrics of CA50 distribution. Experimental CA50 is compared with predicted CA50 from the model and the results show a total average error of less than 1.5 degrees of crank angle for 213 steady-state operating points with four different PRF fuels at diversified operating conditions. Predicted PDF of the CA50 ensemble is compared with that of the experiments for PRF fuels at different running conditions. The results indicate a good agreement between simulation and the experiment.


Fuel ◽  
2019 ◽  
Vol 237 ◽  
pp. 658-675 ◽  
Author(s):  
Yingcong Zhou ◽  
Deivanayagam Hariharan ◽  
Ruinan Yang ◽  
Sotirios Mamalis ◽  
Benjamin Lawler

2020 ◽  
Vol 125 (1284) ◽  
pp. 296-340
Author(s):  
D.I.A. Poll ◽  
U. Schumann

ABSTRACTA simple yet physically comprehensive and accurate method for the estimation of the cruise fuel burn rate of turbofan powered transport aircraft operating in a general atmosphere was developed in part 1. The method is built on previously published work showing that suitable normalisation reduces the governing relations to a set of near-universal curves. However, to apply the method to a specific aircraft, values must be assigned to six independent parameters and the more accurate these values are the more accurate the estimates will be. Unfortunately, some of these parameters rarely appear in the public domain. Consequently, a scheme for their estimation is developed herein using basic aerodynamic theory and data correlations. In addition, the basic method is extended to provide estimates for cruise lift-to-drag ratio, engine thrust and engine overall efficiency. This step requires the introduction of two more independent parameters, increasing the total number from six to eight. An error estimate and sensitivity analysis indicates that, in the aircraft’s normal operating range and using the present results, estimates of fuel burn rate are expected to be in error by no more than 5% in the majority of cases. Initial estimates of the characteristic parameters have been generated for 53 aircraft types and engine combinations and a table is provided.


Fuel ◽  
2018 ◽  
Vol 215 ◽  
pp. 879-891 ◽  
Author(s):  
Gokhan Coskun ◽  
Usame Demir ◽  
Hakan S. Soyhan ◽  
Ali Turkcan ◽  
Ahmet N. Ozsezen ◽  
...  

2012 ◽  
Author(s):  
Mitsuo Asanuma ◽  
Akira Iijima ◽  
Koji Yoshida ◽  
Hideo Shoji ◽  
Go Emori

2020 ◽  
Vol 142 (6) ◽  
Author(s):  
Felix Klein ◽  
Stephan Staudacher

Abstract Fair comparison of future aircraft engine concepts requires the assumption of similar technological risk and a transparent book keeping of losses. A 1000 km and a 7000 km flight mission of a single-aisle airplane similar to the Aribus A321neo LR have been used to compare composite cycle engines, turbocompound engines and advanced gas turbines as potential options for an entry-into-service time frame of 2050+. A 2035 technology gas turbine serves as reference. The cycle optimization has been carried out with a peak pressure ratio of 250 and a maximum cycle temperature of 2200 K at cruise as boundary conditions. With the associated heat loss and the low efficiency of the gas exchange process limiting piston component efficiency, the cycle optimization filtered out composite cycle concepts. Taking mission fuel burn (MFB) as the most relevant criterion, the highest MFB reduction of 13.7% compared to the 2035 reference gas turbine is demonstrated for an air-cooled turbocompound concept with additional combustion chamber. An intercooled, hectopressure gas turbine with pressure gain combustion achieves 20.6% reduction in MFB relative to the 2035 reference gas turbine.


2017 ◽  
Vol 178 ◽  
pp. 205-216 ◽  
Author(s):  
Mohammed AlAbbad ◽  
Tamour Javed ◽  
Fethi Khaled ◽  
Jihad Badra ◽  
Aamir Farooq

2016 ◽  
Vol 82 (835) ◽  
pp. 15-00414-15-00414 ◽  
Author(s):  
Hirotaka SUZUKI ◽  
Takahiro SHIMA ◽  
Yuki TAKAMURA ◽  
Akira IIJIMA ◽  
Hideo SHOJI

2013 ◽  
Vol 152 (1) ◽  
pp. 3-9
Author(s):  
Jacek HUNICZ ◽  
Michał GĘCA

In this study experimental and modeling investigations of a gasoline HCCI engine with internal gas recirculation have been presented. Experimental measurements enabled identification of attainable range of valvetrain settings and air excess coefficient that allows a realization of the HCCI combustion. Factors determining the charge exchange process and the resulting in-cylinder temperature were specified based on computational analysis.


Author(s):  
Ida Truedsson ◽  
Martin Tuner ◽  
Bengt Johansson ◽  
William Cannella

The current research focuses on creating a homogeneous charge compression ignition (HCCI) fuel index suitable for comparing different fuels for HCCI operation. One way to characterize a fuel is to use the auto-ignition temperature (AIT). The AIT can be extracted from the pressure trace. Another potentially interesting parameter is the amount of low temperature heat release (LTHR) that is closely connected to the ignition properties of the fuel. The purpose of this study was to map the AIT and the amount of LTHR of different oxygenated reference fuels in HCCI combustion at different cylinder pressures. Blends of n-heptane, iso-octane, and ethanol were tested in a cooperative fuels research (CFR) engine with a variable compression ratio. Five different inlet air temperatures ranging from 50 °C to 150 °C were used to achieve different cylinder pressures and the compression ratio was changed accordingly to keep a constant combustion phasing, CA50, of 3 ± 1 deg after top dead center (TDC). The experiments were carried out in lean operation with a constant equivalence ratio of 0.33 and with a constant engine speed of 600 rpm. The amount of ethanol needed to suppress the LTHR from different primary reference fuels (PRFs) was evaluated. The AIT and the amount of LTHR for different combinations of n-heptane, iso-octane, and ethanol were charted.


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