Experimental investigation of two-dimensional wall thermal loads in the near-injector region of a film-cooled combustion chamber

Wang, Taiping; Sun, Bing; Liu, Di; Xiang, Jixin

doi:10.1016/j.applthermaleng.2018.03.108

Cited by 11 publications

(3 citation statements)

References 19 publications

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“…Error analysis of the measurement data showed that the measurement error of heat flux is less than ±1.4%, and the temperature measurement error was ±0.4%. Therefore, the uncertainty of measuring the wall temperature can be largely ignored in its impact on heat flux [20]. During the experimental measurement process, the radii of the inner and outer walls of the combustion chamber were measured using a vernier caliper with a measurement accuracy of ±0.02 mm.…”

Section: Experimental Analysismentioning

confidence: 99%

Effects of Different Structural Film Cooling on Cooling Performance in a GO2/GH2 Subscale Thrust Chamber

Xiang,

Jia,

et al. 2024

Aerospace

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To investigate the wall cooling of the thrust chamber in an engine, two film-cooling structures, namely, a circular hole structure and a slot structure, were designed. Numerical simulations were performed to study the coupled flow and regenerative cooling heat transfer in thrust chambers with different structures. The influences of parameters such as the film mass flow rate and film hole size on wall cooling were analyzed. Experiments were conducted in a thrust chamber to validate the accuracy of the numerical calculation method. The results indicate that the slot-structured film adheres better to the wall than the circular-hole-structured film, and the film closely adhering to the wall provides better insulation against hot gas, resulting in a reduction of approximately 6% in wall temperature. When the film hole size changes, the change in circumferential wall temperature in the upstream region of the slot-structured film is more pronounced. This paper aims to provide a reference for the design of the cooling structure at the head of the thrust chamber in engineering and suggests directions for optimization and improvement.

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Section: Experimental Analysismentioning

confidence: 99%

Effects of Different Structural Film Cooling on Cooling Performance in a GO2/GH2 Subscale Thrust Chamber

Xiang,

Jia,

et al. 2024

Aerospace

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“…Arnold et al [4] carried out an experiment with a hydrogen film cooling ultra-small rocket combustor and obtained the axial and circumferential wall heat load. Taiping et al [5] carried out an experiment about the film cooling near the injector with a GH2/GO2 heat-sink combustor and measured the wall heat flux and wall temperature distribution under different chamber pressures and propellant proportions. Marco Pizzarelli et al [6] established a twodimensional model for liquid oxygen/methane engines (outflow cooling) and estimated it by simulation.…”

Section: Introductionmentioning

confidence: 99%

The Confirmation of Thermal Boundary Parameters in an Oxygen Kerosene Fuel-Rich Rocket Engine

et al. 2022

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The thermal environment is an important factor in the design of liquid rockets. In this paper, theoretical analysis, numerical simulation and experimental testing are conducted to study the boundary thermal characteristics of a GOX/kerosene liquid rocket motor with a total flow rate of 120 g/s and an oxygen-fuel ratio of 1:1. We measured the axial temperature in different positions in the combustor using thermocouples and the heat flux using a flux meter. We found that the heat flux at 182 mm increases by 6.8% when a carbon deposit exists. For the theoretical results, after correcting the thermal conductivity by the volume fraction of carbon deposition, the theoretical heat flux (1.11 MW/m2, using the corrected thermal conductivity) and the numerical result (0.89 MW/m2, considering the injectors) are similar to the experimental value (0.937 MW/m2). This study validates the accuracy of theoretical and simulation calculation in this case, and provides verification data for future numerical calculation, as well as data for setting gas temperature at the wall in the simulation of the gas phase.

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“…It is a necessary process for the design of film cooling in a LOX/GH 2 thrust chamber to deeply understand the mechanisms about film cooling and injector-wall interaction in the axial and circumferential directions under different conditions (Suslov et al, 2009;Wang et al, 2018). Some works have been done by published experiments on the investigation of film cooling in a LOX/GH 2 thrust chamber.…”

Section: Introductionmentioning

confidence: 99%

Research on coupled heat transfer of film cooling in LOX/GH<sub>2</sub> thrust chambers

Xiang

Sun

2018

JTST

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To better understand the performance of gaseous film cooling near the injector region in the LOX/GH 2 thrust chambers, a methodology is employed to simulate the coupled heat transfer of the film cooling in thrust chambers with regenerative cooling. The conjugated flow and heat transfer behaviors of film coolant, hot gas, cooling channels and regenerative coolant are numerically investigated. A three-dimensional non-adiabatic flamelet model using real gas equation of state is developed to solve the combustion and validated against the experimental data. Film cooling performance is predicted for the conditions with different geometrical parameters and mass flow rates of the film coolant. The result shows that the reverse flow zones are formed and developed in the region near the injectors The occurrence of those zones is responsible for the significant reduction of the hot-gas-side wall temperature near the head plate of the injector. The coolant mass flow rate has a great influence on the film cooling performance due to the variety of coolant momentum in the exit of orifices and vorticity in the near-injector region. An optimum mass flow rate for maximizing the averaged effectiveness exists for a given film orifice geometric configuration. The high averaged effectiveness and the uniform flux distribution of hot-gas-side wall are observed at small orifices spacing. The film cooling effectiveness in the orifice exit region is obviously enhanced when the diameter of the orifice increased in the front part of the combustion chamber. The results would be useful for the analysis and optimization design of the straight cylindrical coolant orifices in the LOX/GH 2 thrust chamber.

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Experimental investigation of two-dimensional wall thermal loads in the near-injector region of a film-cooled combustion chamber

Cited by 11 publications

References 19 publications

Effects of Different Structural Film Cooling on Cooling Performance in a GO2/GH2 Subscale Thrust Chamber

Effects of Different Structural Film Cooling on Cooling Performance in a GO2/GH2 Subscale Thrust Chamber

The Confirmation of Thermal Boundary Parameters in an Oxygen Kerosene Fuel-Rich Rocket Engine

Research on coupled heat transfer of film cooling in LOX/GH<sub>2</sub> thrust chambers

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