By combining the three-dimensional model software and grid generation software,the combustor parametric model and high quality and high speed gridding in the full flow field has been realized.Based on the research of ...By combining the three-dimensional model software and grid generation software,the combustor parametric model and high quality and high speed gridding in the full flow field has been realized.Based on the research of the parametric modeling,an optimizing design,CFD analysis and performance prediction of the combustor have been accomplished,and the rule of the combustor performance variation with structural parameters was presented.The results show that the combustor capability has no significant change with the radial swirler parameters and the primary holes area.The combustor capability has significant change with position and profile of the primary holes and dilution holes,and the combustor outlet temperature profile and emission change greatly when the total hole area of the burnerinnerliner changes.The parametric model method is helpful to provide a fast design method for the aero-engine combustor design.展开更多
In this paper, two engineering application examples of combustor design software package for small gas turbine engine were provided. First, the software package was used to analyze the internal flow fields of a revers...In this paper, two engineering application examples of combustor design software package for small gas turbine engine were provided. First, the software package was used to analyze the internal flow fields of a reverse how combustor, the results showed a strong recirculating zone was produced at primary zone of liner, this recirculating zone provided a stable heat resource for high efficiency combustion, the flow field at liner was unsymmetrical, there was full mix between high temperature gas and cold dilution gas, a lot of airflow was used to protect liner wall because of greater liner surface aera, total pressure loss of combustor was small, combustor had good performances. Secondly, the software package was used to help to design a new reverse flow combustor, the results revealed that for preliminary combustor design scheme, there wasn’t strong recalculation at primary zone, jet penetration depths at primary holes were very small and wall temperature at outer liner was higher, many good suggestions for improve combustor design were put forward, important guide value of the software package for the development of combustor was verified.展开更多
A trapped vortex combustor （TVC） has been a very promising novel concept for it offers improvements in lean blow out, altitude relight, operating range, as well as a potential to decrease NOx emissions compared to c...A trapped vortex combustor （TVC） has been a very promising novel concept for it offers improvements in lean blow out, altitude relight, operating range, as well as a potential to decrease NOx emissions compared to conventional combustors. The present paper discusses the improved designs of the new combustor over the prior ones of our research group, including that：a） the over-all dimensions, both axial and radial, are reduced to those of an actual aero-engine combustor; b） the air flow distribution is optimized, and especially 15% of the air is fed into the liner as cooling air; c） a straight-wall diffuser with divergence angle 9°is added. A series of experiments （cavity-fueled only, under atmospheric pressure） has been conducted to investigate the performance of the improved TVC. Experimental results show that at the inlet temperature of 523 K, the inlet pressure of 0.1 MPa, stable operation of the TVC test rig is observed for the Mach number 0.15-0.34, indicating good flame stability; the combustion efficiency obtained in this paper falls into the range of 60%-96%; as the total excess air ratio increases, the combustion efficiency decreases, while the increase of the inlet temperature is beneficial to high combustion efficiency; besides, the optimal Mach numbers for high combustion efficiency under different inlet conditions are confirmed. The outlet temperature profiles feature a bottom in the midheight of the exit. This paper demonstrates the feasibility for the TVC to be applied to a realistic aero-engine preliminarily and provides reference for TVC design.展开更多
文摘By combining the three-dimensional model software and grid generation software,the combustor parametric model and high quality and high speed gridding in the full flow field has been realized.Based on the research of the parametric modeling,an optimizing design,CFD analysis and performance prediction of the combustor have been accomplished,and the rule of the combustor performance variation with structural parameters was presented.The results show that the combustor capability has no significant change with the radial swirler parameters and the primary holes area.The combustor capability has significant change with position and profile of the primary holes and dilution holes,and the combustor outlet temperature profile and emission change greatly when the total hole area of the burnerinnerliner changes.The parametric model method is helpful to provide a fast design method for the aero-engine combustor design.
文摘In this paper, two engineering application examples of combustor design software package for small gas turbine engine were provided. First, the software package was used to analyze the internal flow fields of a reverse how combustor, the results showed a strong recirculating zone was produced at primary zone of liner, this recirculating zone provided a stable heat resource for high efficiency combustion, the flow field at liner was unsymmetrical, there was full mix between high temperature gas and cold dilution gas, a lot of airflow was used to protect liner wall because of greater liner surface aera, total pressure loss of combustor was small, combustor had good performances. Secondly, the software package was used to help to design a new reverse flow combustor, the results revealed that for preliminary combustor design scheme, there wasn’t strong recalculation at primary zone, jet penetration depths at primary holes were very small and wall temperature at outer liner was higher, many good suggestions for improve combustor design were put forward, important guide value of the software package for the development of combustor was verified.
基金Aeronautical Science Foundation of China (2008ZB52013)Funding of Jiangsu Innovation Program for Graduate Education (CXLX11_0211)
文摘A trapped vortex combustor （TVC） has been a very promising novel concept for it offers improvements in lean blow out, altitude relight, operating range, as well as a potential to decrease NOx emissions compared to conventional combustors. The present paper discusses the improved designs of the new combustor over the prior ones of our research group, including that：a） the over-all dimensions, both axial and radial, are reduced to those of an actual aero-engine combustor; b） the air flow distribution is optimized, and especially 15% of the air is fed into the liner as cooling air; c） a straight-wall diffuser with divergence angle 9°is added. A series of experiments （cavity-fueled only, under atmospheric pressure） has been conducted to investigate the performance of the improved TVC. Experimental results show that at the inlet temperature of 523 K, the inlet pressure of 0.1 MPa, stable operation of the TVC test rig is observed for the Mach number 0.15-0.34, indicating good flame stability; the combustion efficiency obtained in this paper falls into the range of 60%-96%; as the total excess air ratio increases, the combustion efficiency decreases, while the increase of the inlet temperature is beneficial to high combustion efficiency; besides, the optimal Mach numbers for high combustion efficiency under different inlet conditions are confirmed. The outlet temperature profiles feature a bottom in the midheight of the exit. This paper demonstrates the feasibility for the TVC to be applied to a realistic aero-engine preliminarily and provides reference for TVC design.
