Research Article  Open Access
Hongtao Zheng, Gang Pan, Xi Chen, Xiaoming Hu, "Effect of Dual Fuel Nozzle Structures on Combustion Flow Field in CRGT Combustor", Mathematical Problems in Engineering, vol. 2013, Article ID 913837, 11 pages, 2013. https://doi.org/10.1155/2013/913837
Effect of Dual Fuel Nozzle Structures on Combustion Flow Field in CRGT Combustor
Abstract
Three different structures of a new dual fuel nozzle design concept (inner swirl nozzle, double swirl nozzle, and outer swirl nozzle) were developed for the chemically recuperated gas turbine (CRGT) combustor. The combustion flow fields in the combustor with the three nozzles were investigated, respectively, based on the FLUENT simulation. The realizable  model and PDF model were adopted, respectively, for the turbulence flow and nonpremixed reformed gas combustion. The obtained results using these models showed good agreement with experimental results in original oil combustor. The effects of different dual fuel nozzle structures on the flow field, fuel concentration distribution, and temperature distribution in the combustor were simulated and analyzed. Results suggest that the double swirl nozzle and outer swirl nozzle can form a better flow field with obvious central recirculation zone (CRZ), shorten fuel and air mixing distance, and obtain a more uniform outlet temperature distribution, in comparison with the inner swirl nozzle. However, compared with double swirl nozzle, the outer swirl nozzle can result in a better combustion flow field with the high temperature region in the CRZ, which is important to stabilize the flame.
1. Introduction
Since gas turbine is compact, lightweight, quick starting, highly reliable, and simple to operate, it has been used widely for many years in aviation, shipping, electric power, fossil oil, and other industrial fields [1]. However, certain problems have been identified under practical operating conditions, namely, low thermal efficiency of the system and high emission including [2]. In order to solve these problems, the CRGT system is proposed [3]. In the CRGT system, gas turbine is started with the oil fuel. When the system runs stably, the mixture of oil and steam in the reformer is heated by the gas turbine flue gas, and an endothermic reaction occurs between the oil and the steam. The reaction results in the production of reformed gas which includes plenty of steam and hydrogen. The reformed gas is then fed into the turbine combustor. At the same time, the flow rate of oil fuel fed into the combustor is reduced gradually until the oil fuel is replaced by the reformed gas. Obviously, the combustor for the CRGT system should be able to burn the gas and oil dual fuels. Therefore, it is important to design a suitable dual fuel combustor for this system, especially a dual fuel nozzle.
Fuel nozzle is a key component of the combustor. Lots of researches on the fuel nozzle have been carried out through experiments. Terasaki and Hayashi [4] developed a double swirler burner. The emission characteristic of the burner was compared with those for the swirl burners of conventional configurations. The test results showed that the double swirler burner could achieve better fuelair mixing and the lowest emissions level. Iyogun et al. [5] investigated the impact of nozzle geometry on swirling flame stability. They found that the nonaxisymmetric fuel nozzle increased the size and dynamics of the flow recirculation zones and induced higher levels of turbulence intensities when compared with axisymmetric fuel nozzle. Li et al. [6] found that the heat transfer and CO emission of impinging premixed flames were affected by the nozzle diameter and nozzle arrangement. Zhen et al. [7] performed an experiment study to investigate the effects of the nozzle length on the emission of a burner utilizing a multifueljet inverse diffusion flame. They found that the flame centerline temperature and CO/CO_{2} concentrations were significantly affected by the nozzle length. Lee and Yoon [8] developed a gas turbine fuel nozzle for dimethyl ether. The performance of the newly developed nozzle was verified through a comparison with the original nozzle. The newly nozzle could prevent the flashback and reduce emissions of and CO. Mansour et al. [9] designed a highly stabilized concentric flow conical nozzle burner. The flow filed, temperature, and OH radical outside the cone were measured. They found that the flame of this burner had a better stabilization performance than the similar flames without cone. Koyama and Tachibana [10] designed a lowswirl burner for the liquidfuel. The effects of nozzle tip shape on flow patterns were investigated through experiment. They found that chamfer dimensions primarily affected the axial position of the flame. However, there is little published data on the dual fuel nozzle design for the CRGT system.
On the other hand, the fast development of computer and methodology of numerical computation technology have enabled computational fluid dynamics (CFD) to play a great role in combustor design. Using CFD technology lowers experimental costs and provides guidance in the optimal design of the structure. Many scholars used the CFD to get information on the flow field of combustor. Liedtke and Schulz [11] designed a new lean burning combustor. They got an insight into the flow structures and information on the location of the pilot and main flame within the combustor by the commercial code CFDACE. Chui et al. [12] evaluated burner and combustor design concepts using CFD. They found that the CFD could be an efficient tool for evaluating such burner and combustor design. Koyama and Fujiwara [13] used CFD to predict the gas fuel concentration in the combustor with three gas swirl injection methods. They found that reverse swirl injection could result in good fuelair mixing and stable flame. Alattab and Zainal [14] used FLUENT to determine the optimum design of the pressurized cyclone combustor. Finally, the combustor height, diameter and outlet geometry were determined. Arghode and Gupta [15] calculated the combustor flow field with FLUENT, and discussed the effects of air and fuel injection diameter and confinement size on gas recirculation and fuel/air mixing characteristics. Xing et al. [16] investigated the effects of various heighttolength ratios of the cavity on the flow structure in the trapped vortex combustor through CFD method.
In this study, in order to burn the reformed gas effectively, three different structures of a new dual fuel nozzle design concept were developed. The FLUENT was used to analyze the nozzles for the CRGT combustor. The effects of different dual fuel nozzle structures on the flow field, fuel concentration distribution, and temperature distribution in the combustor were discussed. This work could help improve the design of the dual fuel nozzle for the CRGT combustor and save experiment cost.
2. Geometry and Mathematical Model
2.1. Geometry
The gas turbine combustor is designed to burn the fuel efficiently. The basic geometry of the combustor is shown in Figure 1. The size of the combustor is 391 mm in the direction, 245 mm in the direction, and 743 mm in the direction. In this paper, three different dual fuel nozzle structures (inner swirl nozzle, outer swirl nozzle, and double swirl nozzle) were developed, as shown in Figure 2. A hybrid mesh was generated for the combustor, as shown in Figure 3. And the total grid number is 3,500,000.
(a) Inner swirl nozzle
(b) Double swirl nozzle
(c) Outer swirl nozzle
Boundary conditions are as follows: reformed gas inlet temperature is 723 K, inlet flow rate is 0.3 kg/s, and the composition of reformed gas is shown in Table 1. Air inlet temperature is 670 K, inlet flow rate is 2.7 kg/s, and inlet pressure is 1.01325 MPa. Outlet: pressure outlet. Wall: adiabatic boundary.

2.2. Mathematical Model
The mathematical equations describing the reformed gas fuel combustion are based on the equations of conservation of mass, momentum, energy, and species transport together with other supplementary equations for the turbulence and combustion. The realizable  model [17] was adopted to simulate the turbulence flow. The equations for the turbulent kinetic energy and the dissipation rate of the turbulent kinetic energy were solved. For nonpremixed reformed gas combustion, the PDF model [18] was used. The equations are as follows (ignore radiation and gravitation) [19]:
Continuity Equation
Momentum Conservation Equation where is the stress tensor,
Energy Conservation Equation where is the effective conductivity, is the diffusion flux of species , and is the heat of chemical reaction,
Species Transport Equation where is the net rate of production of species by chemical reaction,
State Equation
Realizable  model where represents the generation of turbulence kinetic energy due to the mean velocity gradients, is the generation of turbulence kinetic energy due to buoyancy, represents the contribution of the fluctuating dilatation in compressible turbulence to the overall dissipation rate, and are userdefined source terms, 1.44, 1.9, 1.0, and 1.2,
PDF Combustion Model where is the mixture fraction, is the mixture fraction variance, and the constant values of , , and are 0.85, 2.86, and 2.0, respectively.
3. Model Validation
In order to validate the numerical model, the experiment and numerical simulation have been carried out for the original oil combustor. The boundary conditions of the experimental and numerical cases are as follows: the air mass flow rate is 1.19 kg/s, the temperature is 758.6 K, the pressure is 0.573 MPa, the oil mass flow rate is 0.0264 kg/s, and the temperature is 300 K. The combustor outlet temperature was measured by twenty thermocouples, which were arranged uniformly at the combustor outlet. In the experiment, the combustor outlet temperature was measured three times, and the final experimental data was the average of three measurements.
The combustor outlet average temperatures have been obtained through both experimental investigation and numerical simulation, as seen in Figure 4. The temperature of simulation result is a little lower than that of the experimental result, but the relative error between the simulation and experimental results is only 6.3%. This confirms the reasonable accuracy of the numerical model adopted in the present paper. To further validate the suitability of the numerical model, the OTDF (overall temperature distribution factor), and RTDF (radial temperature distribution factor) of combustor have also been studied. As shown in Figure 5, the experimental and simulation values of OTDF are 17.3% and 16.3%, respectively. And the RTDF are 7.4% and 6.7% respectively, as seen in Figure 6. Figures 5 and 6 reveal that the numerical results operated in the present study fit satisfactorily with experimental data. Thus, the numerical model used in this paper is reliable and applicable for the solution of combustion flow field in combustor.
4. Results and Discussion
4.1. Flow Field Analysis
Studying the streamlines of velocity field in the combustor provides a better understanding of the effect of the dual fuel nozzle structure on the flow patterns. Figure 7 shows the streamlines of velocity field within the combustor under reactive situation for different dual fuel nozzle structures. As can be seen from the figures, the dual fuel nozzle structure has little effect on the flow field out of the combustor liner, but a significant effect on the flow field in the combustor liner. In the inner swirl nozzle combustor, the fuel flows directly to the combustor outlet, and some small vortexes form in the primary zone of the combustor. However, in the outer swirl nozzle or double swirl nozzle combustor, there is a counterrotating vortex pair forming in the primary zone of the combustor, which is the main characteristic of the CRZ. The CRZ can provide the heat source by upstream convection and mixing of hot reaction products with a fresh charge of fuel and air, and reduce the mixture velocity to be in the range of flame speed which is necessary for flame stabilization.
(a) Inner swirl nozzle
(b) Double swirl nozzle
(c) Outer swirl nozzle
The conclusion can be made that the nozzle with a swirler in the outer channel can obtain a better flow field. The reason is that the fuel flowing through the outer swirler can obtain a swirling velocity and then mix with the swirling air from the combustor swirler. After that, the swirling mixture of fuel and air flows forward and entraps the air in the center area of the combustor, and at the same time, the downstream air refills the region, then the CRZ is formed. However, in the inner swirl nozzle combustor, though the fuel flowing through the inner swirler can also obtain a swirling velocity, the axial direction velocity of the fuel flowing through the outer channel can offset the swirl effect of the fuel from the inner swiler, so the fuel flows directly to the combustor outlet finally. And due to the effect of the swirling air, there are some small vortexes in the primary zone. Therefore, the fuel concentration field and combustion field would be better in the outer swirl nozzle combustor and double swirl nozzle combustor than that in inner swirl nozzle combustor.
4.2. Fuel Concentration Distribution Analysis
Fuel injection and mixing are critical to achieving efficient and clean combustion in modern gas turbine combustors. The fuel concentration distribution analysis is an effective method to research the fuel injection and mixing in the combustor. In this paper, fuel concentration distribution within the combustor under a steady reactive condition for the three dual fuel nozzles was investigated numerically. The components of H_{2} and CO were selected to investigate the fuel concentration distribution in the combustor because they were the combustible components in the fuel. The profiles of H_{2} and CO mole fraction in the combustor middle plane are shown in Figures 8 and 9, respectively. In these figures, represents the position of the axis. The profiles of H_{2} and CO mole fraction show the radial spread of fuel jets, progress of fuelair mixing, and fuel combustion. As can be seen in Figure 8, the H_{2} mole fraction profiles for the three nozzles have different shapes. In the inner swirl nozzle combustor, at mm, the profile of H_{2} is a cone with its apex on the axis, which does not change at mm, suggesting that the mixing of air and fuel in the combustor is far from complete. The peak values of the H_{2} mole fraction are 0.40208 at and 0.3573 at , respectively, suggesting that the combustion of fuel is far from complete.
(a)
(b)
(c)
(d)
(e)
(f)
(a)
(b)
(c)
(d)
(e)
(f)
In the double swirl nozzle combustor, at mm, the profile of H_{2} has two peaks and shows an M shape. The H_{2} mole fraction decreases with increasing the axial distance, due to mixing with air and the combustion of fuel. And the radial space of the H_{2} distribution becomes wider with increasing the axial distance, due to the swirling flow of the fuel. More uniform profiles of H_{2} mole fraction are observed further downstream (i.e., and 210 mm). And the values of H_{2} mole fraction are nearly zero, illustrating that the combustion of fuel almost completes. It can also be seen from Figure 8, due to the swirling effect of the double swirl nozzle, that more fuel is injected away from the central axis of the combustor liner, so the H_{2} mole fraction is almost zero in the center area of the combustor.
In the outer swirl nozzle combustor, the Mshaped H_{2} mole fraction profiles are also presented. With increasing axial distance, due to the mixing with air and the combustion of fuel, the two peaks are diminished at mm. The value of the H_{2} mole fraction is nearly zero at mm illustrating that the combustion of fuel almost completes. And the radial space of the H_{2} distribution in this combustor is almost the same with the double swirl nozzle combustor. Different from the double swirl nozzle combustor, the H_{2} mole fraction just downstream of the outer swirl nozzle is not zero in the center area of this combustor. This illustrates that the fuel distribution space is broader in the outer swirl nozzle combustor than that in double swirl nozzle combustor.
As shown in Figure 9, the variation of the CO mole fraction profiles with axial distance is generally consistent with that of H_{2} mole fraction profiles. Cone shape for the inner swirl nozzle combustor and M shape for the other two nozzle combustors of CO mole fraction profiles are observed. It can also be seen from Figure 9 that the decreases of the CO mole fraction with increasing axial distance are not as significantly the same as the H_{2} mole fraction. The reason is that the burning speed of H_{2} is faster than that of CO.
A comparison of the fuel concentration profiles shows that the double swirl nozzle and outer swirl nozzle can inject the fuel into a broader space than the inner swirl nozzle. So the fuel can be mixed with air rapidly in the double swirl nozzle combustor and outer swirl nozzle combustor. The distance of the complete fuel combustion is shorter in the double swirl nozzle combustor and outer swirl nozzle combustor than in the inner swirl nozzle combustor.
4.3. Temperature Distribution Analysis
The temperature distributions within the combustor under a steady reactive condition for the three nozzles are compared in Figure 10. In the inner swirl nozzle combustor, the high temperature region is mainly located in the dilution zone. It is because the fuel is not mixed rapidly and well with the air. In the double swirl nozzle combustor, the high temperature region is mainly located in the primary zone, but near the combustor liner. It is because there is little fuel in the center area of the combustor, so the fuel is burned near the combustor liner. This would cause a high combustor liner metal temperature and then shorten the service life of the combustor liner. In the outer swirl nozzle combustor, the high temperature region is mainly located in the CRZ, which is useful to stabilize the flame. The combustion flow field in this combustor is better compared to that of the former two combustors.
(a) Inner swirl nozzle
(b) Double swirl nozzle
(c) Outer swirl nozzle
Figure 11 shows temperature profiles along the central axis in the combustor liner for the three nozzles. As can be seen from the figure, the trends of the temperature profiles are different for the three nozzles. For the fuel that is not mixed well with the air in the primary zone, the highest temperature on the central axis in the inner swirl nozzle combustor is near the combustor outlet. Because the fuel is burned near the combustor liner, the highest temperature on the central axis in the double swirl nozzle combustor is lower than that of the other two combustors. In the outer swirl nozzle combustor, due to the better combustion flow field, the highest temperature on the central axis is in the CRZ.
The combustor outlet temperature distribution and the corresponding pattern factor have a strong impact on a gas turbine plant. Figure 12 shows the outlet temperature distributions of different nozzle structures. It is observed under all situations that the outlet temperature distributions are not the same. In the inner swirl nozzle combustor, the maximum value of outlet temperature is almost at the center position of the combustor outlet, which is 1500 K. In the double swirl nozzle combustor, the maximum value of outlet temperature is located in the upper right of the combustor outlet, which is 1340 K. In the outer swirl nozzle combustor, the position of the maximum outlet temperature is almost the same with the double swirl nozzle combustor and the maximum temperature value is 1350 K.
(a) Inner swirl nozzle
(b) Double swirl nozzle
(c) Outer swirl nozzle
Figures 13–15 show the OTDF (overall temperature distribution factor), RTDF (radial temperature distribution factor) and CTDF (circumferential temperature distribution factor) of combustor, respectively. The OTDF, RTDF and CTDF are defined respectively as follows: where is combustor outlet maximum temperature, is combustor outlet radial maximum temperature, is combustor outlet circumferential maximum temperature, is combustor outlet average temperature, and is air inlet temperature.
The combustor design requires OTDF to be less than 30%35%. As can be seen from Figure 13, the OTDF of the inner swirl nozzle combustor is 32.27%, which is higher than 30% and does not meet the requirement fully. However, the OTDF of the double and outer swirl nozzle combustors satisfy the requirement, which are 7% and 12.94%, respectively.
The combustor design requires RTDF and CTDF to be less than 10%. As can be seen from Figures 14 and 15, the RTDF and CTDF of the inner swirl nozzle combustor are higher than 10%. The double swirl nozzle combustor has the smallest RTDF and CTDF which are 3.87% and 1.85%, respectively. Though the RTDF and CTDF of the outer swirl nozzle combustor are larger than the double swirl nozzle combustor, they are still less than 10%. The conclusion can be made that the double swirl nozzle combustor outlet temperature distribution is the best, followed by the outer swirl nozzle combustor and the worst is the inner swirl nozzle combustor.
The results of the study as discussed above provide the guideline to decide upon the different dual fuel nozzle structures to have the desired performances. In summary, the combustor with the outer swirl nozzle can obtain a better combustion flow field. So this nozzle is selected for the CRGT system finally.
5. Conclusion
In this paper, in order to burn reformed gas effectively, three different structures of a new dual fuel nozzle design concept (inner swirl nozzle, double swirl nozzle, and outer swirl nozzle) were developed. And the combustion flow field in the combustor with the nozzles was investigated, respectively. The realizable  model was used for turbulence modeling, PDF model for nonpremixed gas combustion. The effects of the different dual fuel nozzle structures on the flow field, fuel concentration distribution, and temperature distribution in the combustor were simulated and analyzed. The conclusions are as follows.(1)Due to the swiler in the outer channel of the nozzle, the double swirl nozzle and outer swirl nozzle combustor can get a better flow filed with an obvious CRZ.(2)The fuel concentration distribution presents a cone shape in the inner swirl nozzle combustor and an M shape in the double swirl nozzle combustor and outer swirl nozzle combustor. The profile of fuel concentration distribution in the upstream region in the combustor for the double swirl nozzle and outer swirl nozzle is more uniform than that for inner swirl nozzle. The mixing of fuel and air is more rapid in the double swirl nozzle and outer swirl nozzle combustors than in the inner swirl nozzle combustor, which results in shorter distance of complete fuel combustion in the combustor.(3)The high temperature region is near the combustor outlet for the inner swirl nozzle and the outlet temperature distribution factors do not meet the requirement fully. The outlet temperature distribution factors for the double swirl nozzle meet the requirement fully, but the high temperature region is near the combustor liner which can shorten the service life of the liner. In the outer swirl nozzle combustor, the high temperature region is mainly located in the CRZ and the outlet temperature distribution factors also satisfy the requirement fully.
The results obtained in this study show the differences in flow field, fuel concentration distribution, and temperature distribution when the combustor is equipped with the three dual fuel nozzles, respectively. The results illustrate that the combustor with the outer swirl nozzle has a better combustion flow field.
References
 G. L. Juste, “Hydrogen injection as additional fuel in gas turbine combustor. Evaluation of effects,” International Journal of Hydrogen Energy, vol. 31, no. 14, pp. 2112–2121, 2006. View at: Publisher Site  Google Scholar
 T. Nakagaki, T. Ogawa, H. Hirata, K. Kawamoto, Y. Ohashi, and K. Tanaka, “Development of chemically recuperated micro gas turbine,” Journal of Engineering for Gas Turbines and Power, vol. 125, no. 1, pp. 391–397, 2003. View at: Publisher Site  Google Scholar
 K. F. Kesser, M. A. Hoffman, and J. W. Baughn, “Analysis of a basic chemically recuperated gas turbine power plant,” Journal of Engineering for Gas Turbines and Power, vol. 116, no. 2, pp. 277–284, 1994. View at: Publisher Site  Google Scholar
 T. Terasaki and S. Hayashi, “The effects of fuelair mixing on NOx formation in nonpremixed swirl burners,” in Proceedings of the 26th Symposium International on Combustion, pp. 2733–2739, The Combustion Institute, 1996. View at: Google Scholar
 C. O. Iyogun, M. Birouk, and J. A. Kozinski, “Experimental investigation of the effect of fuel nozzle geometry on the stability of a swirling nonpremixed methane flame,” Fuel, vol. 90, no. 4, pp. 1416–1423, 2011. View at: Publisher Site  Google Scholar
 H. B. Li, H. S. Zhen, C. W. Leung, and C. S. Cheung, “Nozzle effect on heat transfer and CO emission of impinging premixed flames,” International Journal of Heat and Mass Transfer, vol. 54, no. 1–3, pp. 625–635, 2011. View at: Publisher Site  Google Scholar
 H. S. Zhen, Y. S. Choy, C. W. Leung, and C. S. Cheung, “Effects of nozzle length on flame and emission behaviors of multifueljet inverse diffusion flame burner,” Applied Energy, vol. 88, no. 9, pp. 2917–2924, 2011. View at: Publisher Site  Google Scholar
 M. C. Lee and Y. Yoon, “Development of a gas turbine fuel nozzle for DME and a design method thereof,” Fuel, vol. 102, pp. 823–830, 2012. View at: Publisher Site  Google Scholar
 M. S. Mansour, A. M. Elbaz, and M. Samy, “The stabilization mechanism of highly stabilized partially premixed flames in a concentric flow conical nozzle burner,” Experimental Thermal and Fluid Science, vol. 43, pp. 55–62, 2012. View at: Publisher Site  Google Scholar
 M. Koyama and S. Tachibana, “Technical applicability of lowswirl fuel nozzle for liquidfueled industrial gas turbine combustor,” Fuel, vol. 107, pp. 766–776, 2013. View at: Publisher Site  Google Scholar
 O. Liedtke and A. Schulz, “Development of a new lean burning combustor with fuel film evaporation for a micro gas turbine,” Experimental Thermal and Fluid Science, vol. 27, no. 4, pp. 363–369, 2003. View at: Publisher Site  Google Scholar
 E. H. Chui, A. J. Majeski, M. A. Douglas, Y. Tan, and K. V. Thambimuthu, “Numerical investigation of oxycoal combustion to evaluate burner and combustor design concepts,” Energy, vol. 29, no. 910, pp. 1285–1296, 2004. View at: Publisher Site  Google Scholar
 M. Koyama and H. Fujiwara, “Development of a dualfuel gas turbine engine of liquid and lowcalorific gas,” JSME International Journal B, vol. 49, no. 2, pp. 224–229, 2006. View at: Publisher Site  Google Scholar
 K. A. Alattab and Z. A. Zainal, “Design and performance of a pressurized cyclone combustor (PCC) for high and low heating value gas combustion,” Applied Energy, vol. 88, no. 4, pp. 1084–1095, 2011. View at: Publisher Site  Google Scholar
 V. K. Arghode and A. K. Gupta, “Development of high intensity CDC combustor for gas turbine engines,” Applied Energy, vol. 88, no. 3, pp. 963–973, 2011. View at: Publisher Site  Google Scholar
 F. Xing, P. Wang, S. Zhang et al., “Experiment and simulation study on lean blowout of trapped vortex combustor with various aspect ratios,” Aerospace Science and Technology, vol. 18, no. 1, pp. 48–55, 2012. View at: Publisher Site  Google Scholar
 M. Graça, A. Duarte, P. J. Coelho, and M. Costa, “Numerical simulation of a reversed flow smallscale combustor,” Fuel Processing Technology, vol. 107, pp. 126–137, 2013. View at: Publisher Site  Google Scholar
 C. Ghenai, “Combustion of syngas fuel in gas turbine can combustor,” Advances in Mechanical Engineering, vol. 2010, Article ID 342357, 13 pages, 2010. View at: Publisher Site  Google Scholar
 ANSYS Fluent 12.0 Theory Guide.
Copyright
Copyright © 2013 Hongtao Zheng et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.