Regular Analysis of Aero-Diesel Piston Engine between Combustion Chamber Size and Emission

The emission of aero-engines has been a focused issue, studying the regular of combustion chamber size on engine emission performance, with an aviation diesel piston engine as the object of study; the numerical model of diesel combustion spray and emission model are analyzed; and the dynamics grid of the combustion chamber is meshed by FIRE software, analyzing the relationship between the reentrant diameter, the maximum depth of the combustion chamber, and the emission generation, comparing the NOx and soot emissions under different combustion chamber sizes. The results show that reducing appropriately the reentrant-max diameter ratio and max diameter-max depth ratio of the combustion chamber can reduce emissions when maintaining the same compression ratio by adjusting the mid-depth. Modifying the geometry parameters of the combustion chamber to verify regularity, it was found that engine NOx emission decreased by 28% and soot emission decreased by 3.6% when changing the size, which verified the correctness of regular analysis.


Introduction
Piston engine is the main power unit for ground transportation as well as general aviation equipment [1].The emission problem of diesel engine has obtained more and more attention for its better fuel economy [2], especially at the time that the general aviation market is open to the whole world.General aviation aircraft have grown quite rapidly in recent years; the number of general aircraft in the United States has exceeded 300,000 by 2017.Some aero-gasoline engines have been replaced by aviation diesel engines, for example, the EPS engine and WMA-100 engine; however, pollution problems still exist.Currently, much research has been done on the emission of engine, and many emission control methods have been raised.However, most of them are based on engine reprocessing and injection control strategy [3][4][5][6].Chmielewski and Gieras [7] have adopted a variable turbo charging and exhaust gas circulation to improve emission control, and Bogarra et al. [8] have designed an electronic EGR system to ensure the EGR rate under different working conditions to reduce the emission of NO x .Besides, there are also some scholars [9][10][11] who have done a lot of research on emission from oxidation sensors and other research methods.These emission-related studies are mainly for automotive engines; some scholars have also made research on the emissions of aero-engines.For example, Liu et al. [12] provided a comprehensive review of low-emission combustion technologies for modern aero-gas turbines.Besides, Innocenti et al. [13] presented a numerical study where a hybrid CFD-chemical reactor network (CRN) approach is used to predict pollutant emissions in a tubular combustor for aero-gas engine applications.And in Xisto et al. [14], the synergistic combination of intercooling with pulsed detonation combustion is analyzed concerning its contribution to NO x and CO 2 emissions.There is very little research on emissions of aviation heavy oil piston engine.So far, the manufacturers who have obtained type certifications are Thielert in Germany, Continental in United States, Austro in Germany, SMA in France [15], the developing DeltaHawk in the U.S., and Wilksch in Britain [16][17][18][19].Emission control indicators have been formed on aviation turbine engines; Federal Aviation Administration (FAA) and European Aviation Safety Agency (EASA) have not made requirements for emissions when collecting airworthiness certificates of aviation piston engines.However, with the continuous advancement of environmental protection policies, the emission problem of aviation diesel piston engine will be brought to the agenda as soon as possible, and the research and development of emission control of aviation piston engine will also learn from the experience of automotive diesel engine.In this paper, engine emission under an instantaneous state is studied and the influence of different structural parameters on the emission is summarized starting from the basic parameters of the combustion chamber and by changing the structure parameters to provide the reference for the research of aero-diesel engine emission.

The Establishment of a Spray Numerical Model
Inside the cylinder of a direct injection engine, a series of physical changes occur when injecting diesel under high pressure, such as evaporation, break-up, interaction, and dispersion of diesel droplets.In order to better study diesel characteristics under combustion process, the numerical model is established for these processes.

The Diesel Droplet Evaporation
Model.The Dukowicz model has been used to establish a model, and the following assumptions have been made: ① the temperature of the whole diesel droplet is the same, ② droplets are spherical, ③ the droplets are surrounded by a steady gas-phase flow field, ④ the droplets' surface is quasi-static, and ⑤ the intersection of gas and liquid is in thermodynamic equilibrium.According to the above assumptions, diesel droplets are injected into the cylinder.The energy absorbed by diesel droplets is mainly used for heating and evaporating itself as shown in In this equation, m d is the mass of droplets, c pd is the diesel-specific heat capacity under constant pressure, L is the latent heat of droplet evaporation, α is the convective heat-transfer coefficient, and A s is the surface area of diesel droplets.
According to the thermodynamic equilibrium conditions, the expression equation of mass flow is shown in In this equation, f vs is the evaporative mass flow, q s is the surface heat flux density of diesel droplets, and Q is the heat from in-cylinder air to the droplets.
We set Le = 1, and the mass transfer coefficient is The Nusselt value is derived from the following formula according to the single droplet correlation theory: 5 R e and P r can be acquired through the experiment.
From equations ( 1), ( 2), ( 3), (4), and (5), the Nusselt value is used to replace the convective heat transfer coefficient, and the heat absorbed by the diesel droplets is shown in D d is the droplet diameter, λ is the thermal conductivity of gas mixture, T ∞ is the gas mixture temperature, and T s is the droplet temperature [20].
2.2.The Diesel Break-Up Model.After diesel is injected into the cylinder, the primary break-up occurs in the vicinity of the high-pressure nozzle, and the secondary break-up zone occurs in the farther area.The droplet radius can be estimated as shown in equation ( 7) by using the wave model: B is the magnitude constant 1, U is the velocity difference between gas-liquid two-phase motion, and σ is the surface tension of droplets.
The actual equation is , when BΛ>a 8 Jet surface wave formed during diesel injection.Λ is the corresponding wavelength, a is the amplitude critical value, and Ω is the maximum perturbation wave growth rate which causes break-up of the diesel jet.When the amplitude of the unstable wave is greater than the critical value, the diesel oil droplets break apart.

The Wall Interaction Model.
Because of the small volume of the reciprocating engine, the diameter of the working cylinder is also not big.During the diesel injection process, the interaction with the cylinder wall is inevitably occurred.Then, a variety of movement trails are produced after interaction, such as adherent cylinder wall, rebound, and movement on the wall.
The wall-jet model is used.It is supposed that the wall liquid film does not influence the droplet movement after the 2 International Journal of Aerospace Engineering wall interaction.The movement forms of the interaction are judged according to the parameter We, and the particle size is associated with the Weber value after interaction.The equation is We < 50, We > 300 9 d 1 is the droplet diameter before wall interaction, and d 0 is the droplet diameter after wall interaction.When the We value is less than 50, the reflection interaction model is used.When the value is greater than 50, the jet interaction model is adopted.

The Turbulent Dispersion Model.
Diesel is affected by the gas turbulence when injected into the cylinder.Then the random movement of the turbulent vortex causes a disturbance force to diesel droplets, and the turbulent dispersion model is mainly used to analyze the random disturbance.The smaller the droplet is, the more obvious the turbulent affect is, and the trail of the droplet motion is not smooth.The Gosman model is used, and u i ′ is attached to the average velocity of gas u g to describe the disturbance effect of turbulent dispersion on droplets.The equation is Rn i is the random number of the velocity component (0~1), k is the turbulent energy of the droplet, and erf −1 is the inverse Gaussian function.
The time t turb of interaction between diesel droplets and gas turbulence is shown in C τ and C r are both empirical coefficients, k is the turbulence pulsation energy, ε is the turbulence energy dissipation rate, u i ′ is the gas pulsation speed, u g is the gas speed, and u d is the movement speed of diesel droplets.
When the action time of diesel droplets in the turbulent cluster t > t turb , the droplet enters the next turbulent vortex cluster [21].

The Establishment of an Emission
Numerical Model At high temperature, the following reaction occurs among N 2 , O 2 , and NO, and the equation is as shown in k 3 is a constant value, and k 1 , k 2 , k 4 , and k 5 are positive reaction rates related to temperature.m 3 /(kmol.s).

Soot Model.
Soot is a major component of diesel particulate emissions.The Kennedy/Hiroyasu/Magnussen model is used to describe the formation of soot.The equation is s ∅ s is the soot formation rate, and s n is the soot nucleus formation rate which is irrelevant to temperature.Partial oxidation and thermal cracking of hydrocarbon molecules take place under the condition of high temperature and oxygen deficiency to form various unsaturated hydrocarbons, which continuously dehydrogenate and polymerize into carbonbased soot nucleus.s g is the surface generation rate of soot, which is proportional to temperature.s o 2 is the soot oxidation rate, which is proportional to temperature [22].

The Establishment and Analysis of the Combustion Chamber Model
The FIRE software is one of the professional software for engine combustion simulation which is launched by AVL Company in the USA and used by most of the engine R&D companies for simulating engine combustion [23].We can put the engine parameters provided by the engine company like nozzle diameter and the top dead center gap into the corresponding module of FIRE.But the shape of the combustion chamber can only be required when the engine company provides the corresponding detailed drawings.In AVL FIRE, the simulated combustion process begins from the opening of the intake valve to the closing of the exhaust valve.The original data of the engine provided is that the closing angle of the intake valve is 36 °behind the bottom dead center and the opening angle of the exhaust valve is 48 °in front of the bottom dead center.According to general design principle, the top dead center defined is 720 °CA and the bottom dead center is 540 °CA, while the combustion simulation process is from 576 °CA to 848 °CA.
Before the accurate combustion simulation, the combustion chamber should be mesh-generated.Three dynamic meshes which are divided by FIRE software under different crank angles are shown in Figures 1 and 2.

International Journal of Aerospace Engineering
In order to optimize the design of the combustion chamber, new programs are provided on the basis of the original one.Specific data is shown as Table 1, and the geometry and size of the combustion chamber are shown as Figure 3.
The optimization of the combustion chamber geometry shape can increase the turbulent motion properly, improve the mixed effects of fuel and air, speed up the combustion speed, and prolong the vortex duration.The reentrant-max diameter ratio and max diameter-max depth ratio of the combustion chamber are important parameters for optimization, where the reentrant-max diameter ratio refers to the ratio of the reentrant diameter to the maximum diameter, which affects the squish effect in the combustion chamber.The max diameter-max depth ratio refers to the ratio between the maximum diameter and the maximum depth, which affects the mixture of fuel and air.These two ratios both affect the turbulence and squish flow effects in the cylinder during combustion, thereby affecting the combustion and emission of the engine.
Two programs are selected in order to study the influence of the basic size of the dumbbell-type combustion chamber on emission.On the basis of the original, one program changes the maximum diameter of the combustion chamber and its reentrant diameter to achieve the effect of changing  International Journal of Aerospace Engineering the reentrant-max diameter ratio, which is 0.83 in the original scheme and 0.77 after modification.On the basis of program 1, program 2 keeps the reentrant-max diameter ratio unchanged and changes the maximum depth to achieve the effect of changing the max diameter-max depth ratio.The max diameter-max depth ratio of the original is 3.0, and that of program 2 is 2.51.In the design of two programs, the middepth is constantly adjusted to achieve a constant compression ratio of the engine.The combustion numerical simulation analysis of two designing programs is carried out.Three programs are analyzed and compared.Since the combustion is mainly carried out near the top dead center, the maximum pressure and maximum temperature appear under the piston downward at 10 °CA.Since the generation of NO x and soot has a direct relationship with temperature, 730 °CA is thus selected for the analysis under transient state when the NO x and soot emission directly reflects ultimate emissions.Therefore, the angle is analyzed and the temperature inside the cylinder is as shown in Figures 4-6.
It is concluded through analyzing the temperature fields under three programs that the temperature inside the cylinder will change together with the change in the chamber size, while the flame transmission rule has not changed and the maximum temperature appears in the same position as the flame transmission path.The temperature drops at 16.4 K in program 1 and at 42.4 K in program 2 compared with the original program, and the drop in temperature has a certain effect on the generation of NO x and soot.This is mainly because the combustion chamber in program 1 adopts a smaller reentrant-max diameter ratio, and a larger squish  5 International Journal of Aerospace Engineering flow is formed in the piston compression process, which improves the mixing quality of fuel and air and is beneficial to combustion.Also, the flame spreads more evenly, as shown in Figure 5. Therefore, the combustion temperature value in program 1 drops more than that in the original program.Program 2 reduces the max diameter-max depth ratio based on program 1, which improves the turbulent flow of the intake vortex formed in the combustion chamber.Meanwhile, with the max diameter-max depth ratio decreasing, the distance between the nozzle and the combustion chamber wall is reduced, which can strengthen the turbulence intensity near the chamber wall.Besides, a better quality of the mixture of fuel and air is obtained and the flame spreads more evenly; thus, the combustion efficiency is improved, as shown in Figure 6.The temperature of the combustion chamber drops.
The distributions of NO x under 730 °CA are, respectively, shown in Figures 7-9, which are similar to the temperature fields inside the cylinder.Besides, the temperature is the main reason for NO x generation.
By comparing the new program with the original one, the maximum generation of NO x was found to decrease.It decreases by 11.7% in program 1 and 28% in program 2, and there is a general downward trend.NO x is related to the temperature in the combustion chamber.When the temperature in the combustion chamber drops, the concentration of NO x will decrease.As indicated in equations 12 and 13, the positive reaction rate decreases when the temperature lowers, and the generated NO x decreases.With the decrease in the reentrant-max diameter ratio in program 1, the temperature field in the combustion chamber drops, and the production of NO x decreases accordingly.Meanwhile,

6
International Journal of Aerospace Engineering the velocity of the flow field in the combustion chamber will accelerate, resulting in a more even distribution of NO x than the original.On the basis of program 1, program 2 continues to reduce the max diameter-max depth ratio, and the temperature of the combustion chamber is lower than that of program 1, so the generation of NO x is more reduced.At the same time, the velocity of the flow field in the combustion chamber increases more and the turbulence is strengthened.
Under the action of a strong flow field, the distribution of NO x in the combustion chamber is more even.
As shown in Figures 10-12, soot generation analysis of original and new programs is done.Soot is generated mainly in the diffusion combustion phase, mainly formed in the bottom of the combustion chamber, so the distributions and temperature fields are slightly different.It is found that, through comparison, the maximum generation of soot has risen by 5.8% in program 1 and reduced by 3.6% in program 2 based on that of the original.Soot is associated with the combustion temperature, and the combustion high efficiency in the cylinder can reduce soot generation.As shown in equation 14, the rate of formation of soot is related to temperature.The surface generation rate of soot and the soot oxidation rate decrease when the temperature in the cylinder lowers so that soot decreases.Program 1 reduces the reentrant-max diameter ratio.However, the maximum depth remains the same.So it is easy to touch the bottom of the combustion chamber in the process of jet fuel, and at a certain moment the combustion gets affected and soot is generated easily.We can clearly see, in Figure 11, that soot on the bottom left side of the combustion chamber apparently increases.In the meantime, the period under 730 °CA belongs to the diffusion stage of combustion in the cylinder.At this Thus, the max depth of the combustion chamber increases and enlarges the fuel atomization space.Meanwhile, the flow field of the combustion chamber speeds up due to squish flow effects.Under the action of these favorable factors, soot reduces.
After analyzing and comparing modified programs for the combustion chamber, it is clearly shown that NO x emission decreased significantly in program 2, while soot generation has a slight reduction.Generally speaking, emission still tends to decrease.
It is beneficial to decrease the reentrant-max diameter and max diameter-max depth ratio appropriately, but the combustion of the engine will be affected if the size of the combustion chamber is greatly modified or the reentrantmax diameter and max diameter-max depth ratio are greatly reduced.Too much decrease in the max diameter-max depth ratio will lead to fuel directly spraying on the inner wall of the combustion chamber.In this way, fuel attached to the inner wall promotes the generation of soot and emissions worsen.Too much reduction in the reentrant-max diameter ratio makes it difficult to form an orderly flow field in the combustion chamber, which will affect the mixture of fuel and air then bring down the combustion quality and worsen the emission.

The Experiment
According to the size of the combustion chamber of program 2, the bench test is carried out after the assembly, and the AVL and opaque smoke meter instrument is connected.The main equipment used in the experiment is the AVL DIT-EST Gas 1000 emission analyzer to detect NO x in the exhaust gas.The size of the equipment is small around 344 mm * 252 mm * 85 mm, and the weight is light.The parameters in the measurement process can be read directly, and exhaust gas can be diagnosed by itself.Technical parameters are shown in Table 2.
The measurement unit of AVL DITEST Gas 1000 is shown in Figure 13.The function of each connector is marked in the figure.
The AVL439 opaque smoke meter can be used to detect the soot of exhaust gas.This meter is designed on the basis of Beer-Lamber's rule as shown in equation 15.The device is 650 mm * 420 mm * 450 mm in size and is connected to the engine exhaust pipe according to the designed connector.
N is the opacity, in %; K is the absorption, in m −1 ; and L is the length, in m.
The main technical parameters of the equipment are shown in Table 3.
The above equipment on the bench is installed, as shown in Figure 14, and the engine is tested.The test steps are as follows: (1) Install it on the engine test bench according to the AVL analyzer and smoke meter instructions The engine was tested and the engine basic parameters and emissions data are recorded.The recorded data is shown in Table 4.The engine power torque does not change substantially, but the emissions were reduced compared to the original combustion chamber.
It can be seen from the experimental data that the emissions corresponding to program 2 and the experimental data of the original have a downward trend, and the data of the decline is basically consistent with the data calculated by

Conclusion
(1) Reducing the maximum diameter and reentrant diameter of the combustion chamber can reduce the combustion temperature in the engine cylinder, which can reduce the generation of NO x , but the amount of soot is increased.The maximum diameter size is reduced by 4.3%, the reentrant diameter size was reduced by 10.4%, the temperature was reduced by 16.4 K, the NO x was reduced by 11.7%, and the soot was increased by 5.8% (2) The maximum depth and middle depth of the combustion chamber can also affect the temperature and emissions in the cylinder.The maximum depth increases by 14.7%, NO x decreases by 28%, and the soot maximum production decreases by 3.6% (3) In the bench test of the modified combustion chamber, the engine power and torque are basically unchanged, but the emission generation is indeed reduced, which proves that the optimization of the combustion chamber and analysis is feasible

Figure 1 :Figure 2 :
Figure 1: The meshes of the combustion chamber under 740 °CA.

Figure 12 :
Figure 12: The distribution of soot under 730 °CA of program 2.

( 2 )( 3 ) 4 ) 5 )
Start the engine and wait for oil temperature to reach 70 °C, and start measuring emissions data under different RPM Insert the sampling tube of AVL DITEST Gas 1000 into the engine exhaust pipe and read the data (Read the opaque data on the smoke meter (After the measurement, the air pump shall keep working for 10 min to clean the internal pipeline of AVL DITEST Gas 1000

Table 3 :
AVL439 main technical parameter.Aerospace Engineering the simulation, which indicates that the simulation calculation method is feasible.

Table 1 :
Basic size of the combustion chamber.

Table 4 :
Emission data under different operating conditions.