Experimental and numerical investigation of non-reaction flow characteristics in a concentric staged dual-swirl combustor

Li, Le; Zhu, Pengfei; Li, Qiandong; Suo, Jianqin; Zheng, Longxi

doi:10.1007/s12206-022-0341-1

Cited by 4 publications

(9 citation statements)

References 21 publications

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Section: Model Of Concentric and Hierarchical Combustion Chamber At H...mentioning

confidence: 99%

“…Of the stages of combustion, the concentric stage can not only consider stable combustion under a low working load and efficient combustion under a large working load but can also make the distribution of the temperature of the outlet more uniform. 18,19 So, due to the increase of temperature rise and heat capacity, the key technical problems for the high temperature combustion chamber are to broaden the stable working range, reduce the non-uniformity of outlet temperature distribution and improve the temperature resistance of flame tube. The graded zoned combustor can better organize the combustion in the high temperature combustion chamber.…”

Section: Model Introductionmentioning

confidence: 99%

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High-dimensional multi-objective optimization algorithm for combustion chamber of aero-engine based on artificial neural network-multi-objective particle swarm optimization

Liang

Tian

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper considers optimizing the performance of high-temperature combustion chamber of an aero-engine based on a concentric and hierarchical model. First, sample data for the design variables are obtained based on Latin hypercube sampling method, and a one-dimensional program is used to obtain the true values of combustion efficiency and total pressure loss corresponding to each group of variables. The obtained data are then pre-processed to establish a dataset. Second, a multi-layer artificial neural network (ANN) architecture is designed and a surrogate model of the combustion-related performance of the combustor is established using a data-driven method. The results of global sensitivity analysis based on variance show that ratio of fuel flow to air flow (fuel–air ratio) and the total inlet pressure are the most important factors influencing the two objective functions. Finally, we optimize the multi-objective combustion-related performance of the surrogate model by applying the particle swarm optimization algorithm to it. The results of experiments show that the ANN-based model could accurately predict the efficiency of combustion and total pressure loss of the chamber, yielding root mean-squared errors of 0.0107 and 0.3032%, respectively. It also had better generalization ability than the cubic polynomial surrogate model. Compared with the cubic polynomial model, it generated an optimal Pareto solution set as prediction that had higher values in both objective functions. The proposed model might require better data that can be obtained using intelligent sampling methods so that deeper neural networks can be designed to reduce error and improve its optimization design.

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Section: Model Of Concentric and Hierarchical Combustion Chamber At H...mentioning

confidence: 99%

Section: Model Introductionmentioning

confidence: 99%

High-dimensional multi-objective optimization algorithm for combustion chamber of aero-engine based on artificial neural network-multi-objective particle swarm optimization

Liang

Tian

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…This article also focuses on the design and manufacturing of a rectangular test piece for conducting experiments on the non-reacting flow field and ignition propagation process, and it validates the numerical simulation method used in this article based on experimental results. The experiments on the characteristics of the center-staged dual-swirl flow field and the ignition propagation process were conducted on the test bench at Northwestern Polytechnical University, and the experimental system is shown in Figure 2 [33]. The test bench consists of an air supply system, a premix section, a measurement section, a visualization test section, a PIV system, and a high-speed camera.…”

Section: Physical Modelmentioning

confidence: 99%

Study on the Influence of the Pilot Stage Swirl Intensity on the Double-Swirl Combustor’s Ignition Process via Large Eddy Simulation

Zhu

et al. 2023

Machines

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The ignition reliability of the combustion chamber is crucial for the overall performance of an engine. As the aero-engine combustion chambers continue to advance, the scope of the ignition problem has also expanded. This study employs large eddy simulation to investigate the flow characteristics and ignition process of a double-swirl combustor. The non-reacting flow field and ignition propagation process are acquired using particle image velocimetry (PIV) and high-speed cameras. Experimental findings are employed to validate the numerical simulations. The results demonstrate a close relationship between the ignition process of the double-swirl combustor and the flow field within the combustor. Following the spark discharge, a core is generated at the edge of the recirculation zone. Over time, the spark gradually propagates towards the center of the combustor along the direction of swirl due to the flow. Once the flame reaches the head, the fuel and gas mixture ignited by the core within the recirculation zone stabilizes within the boundary layer of the primary and pilot stages. The flame continues to propagate throughout the combustor until complete ignition is achieved. Additionally, the swirl intensity of the pilot mode is identified as a key factor influencing the ignition propagation process of the double-swirl combustor.

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“…Thus, efficient combustion organization methods such as LPP and RQL are proposed. The dual-swirl direct-mixing combustion scheme used in this paper not only can be applied to the high temperature rise combustor to solve the contradiction between lean blowout (LBO) under low power conditions and flame radiation under maximum power conditions but also can be applied to the low-emission combustor, which effectively reduces NOx emissions. − The chemiluminescence characteristics reflect the distribution of the reaction zone, the heat release rate, and the flame structure in the combustor, which can help to explain the combustion instability, flame stabilization, and pollutant emission performance. A deeper chemiluminescence analysis can help researchers investigate flow/spray/flame interaction and improve combustor design in the future.…”

Section: Introductionmentioning

confidence: 99%

OH* Chemiluminescence Characteristics of the RP-3 Fueled Dual-Swirl Direct-Mixing Combustor

et al. 2023

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The flame structure characteristics of the RP-3 fueled dual-swirl direct-mixing combustor are studied experimentally. The flame shape is marked by the OH* radical, which is captured by a CMOS camera with an image intensifier. The flow fields and spray distributions are obtained by particle image velocimetry. The variation of pilot/main-stage flame structure with global fuel-air ratio (FAR), fuel ratio (FR), pilot/main-stage swirl numbers (S p and S m), and Δp/p (total pressure loss coefficient) is further investigated. The typical flame structure, consisting of two main-stage combustion zones (pilot-stage and main-stage combustion zones), is first analyzed. Then, according to the relationship between integral OH* intensity and global heat release rate, increasing swirl number will weaken the effect of strain rate on OH* chemiluminescence. The global FAR has little impact on the flame structure, while modifying the FR will alter the flame mode. The influence of the S p on the flame structure is more significant than that of the S m. Within the range of experimental conditions, the greater the swirl number, the smaller the Δp/p is required to obtain the maximum OH* radical intensity. The addition of non-swirl flow in the main-stage swirler can improve the stability of the pilot-stage flame. The equivalent swirl number is further evaluated by the neural network.

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Experimental and numerical investigation of non-reaction flow characteristics in a concentric staged dual-swirl combustor

Cited by 4 publications

References 21 publications

High-dimensional multi-objective optimization algorithm for combustion chamber of aero-engine based on artificial neural network-multi-objective particle swarm optimization

High-dimensional multi-objective optimization algorithm for combustion chamber of aero-engine based on artificial neural network-multi-objective particle swarm optimization

Study on the Influence of the Pilot Stage Swirl Intensity on the Double-Swirl Combustor’s Ignition Process via Large Eddy Simulation

OH* Chemiluminescence Characteristics of the RP-3 Fueled Dual-Swirl Direct-Mixing Combustor

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