The present work investigated the laminar flame speed measurement of kerosene-relevant fuel, including Jet A-1 commercial kerosene, and surrogate kerosene fuel and its pure components (n-decane, n-propyl-benzene and propyl-cyclohexane), using a high-pressure Bunsen flame burner. The OH* chemiluminescence technique and the kerosene-PLIF technique were used for flame contours detection in order to calculate the laminar flame speed. The experiments were firstly conducted for n-decane/air flame at T = 400 K, φ=0.6-1.3 and atmospheric pressure conditions in order to validate the whole experimental system and measurement methodology. The laminar flame speed of Jet A-1/air, surrogate/air and pure kerosene component (n-decane, n-propyl-benzene and propyl-cyclohexane) was then measured under large operating conditions, including temperature T = 400-473 K, pressure P = 0.1-1.0 MPa and equivalence ratio φ=0.7-1.3. It was found that these three pure components of kerosene have very similar laminar flame speed. By comparing the experimental results of surrogate kerosene and Jet A-1 commercial kerosene, it was observed that the proposed surrogate kerosene, i.e., mixtures of 76.7wt% n-decane, 13.2wt% n-propyl-benzene and 10.1wt% propyl-cyclohexane, can appropriately reproduce the flame speed property of Jet A-1 commercial kerosene fuel. The experimental results were further compared with simulation results using a skeletal kerosene mechanism.

Quantitative measurements of chemiluminescence emissions as a result of CH*, OH*, C₂*, and CO₂* were conducted in CH₄/air premixed flames at different equivalence ratios (θ = 0.7–1.33), and numerical results based on one-dimensional flame simulations were compared to these data. A wavelength-dependent and optical-path-corrected emission calibration method was applied to quantify the emission of each excited species. The numerically simulated emission intensities of OH* and CH* are within the same order of magnitude as the experimental values for the same flame conditions. When self-absorption and cooling water thermosteresis are taken into account, the simulated OH* values are 1.0–1.4 times greater than the experimental results, while the CH* values are approximately 2.3–4.1 times greater. These findings suggest that more work is required to refine the temperature dependence factors for the CH* formation rate coefficients at high temperatures.

In this study, the mechanical behavior and porosity of a T700/epoxy composite material under high temperature conditions were investigated. The 0°/90° compression, tensile, interlaminar, and in-plane shear experiments of composite samples were performed at temperatures from 23°C to 170°C. The true strain–stress curves of composite samples were obtained. The cross section and fracture regions of the tested samples were analyzed by Scanning Electron Microscopy and X-ray tomography to understand the microstructure property relationships. It was observed that the mechanical performance of carbon fiber/epoxy composites generally decreased with increasing temperature. By comparing the fracture morphology, it was found that the fracture mechanism of the composites changed from interfacial debonding to matrix failure with increasing temperature. Three-dimensional visualization of porosities after mechanical experiments under high temperature conditions was reconstituted from X-ray tomography scan images. The results showed that the porosity fraction of the tested samples under high temperature conditions was generally higher than that under lower temperature conditions. Moreover, for the 90° tensile test, the diameter of the pores was mainly located at 4–12 μm and was almost constant along different distances to the failure edge. Meanwhile, compared with the tensile test, larger size of pores in samples of 90° compression tests were observed.