IMECH-IR  > 力学所知识产出(1956-2008)
Combustion of kerosene in a supersonic stream
Li JG(李建国); Yu G(俞刚); Zhang XY(张新宇); Huang QS
Source Publication38th Aerospace Sciences Meeting and Exhibit
Conference Name38th Aerospace Sciences Meeting and Exhibit 2000
Conference DateJanuary 10, 2000 - January 13, 2000
Conference PlaceReno, NV, United states
AbstractThe investigations on characteristics of selfignition and sustaining of kerosene-hydrogen dual fuel were conducted in a direct-connect supersonic combustor with a fixed entrance Mach 2.5. The experiments were conducted with stagnation temperature varied from 1416K to 1700 K and stagnation pressure kept in 1.8 MPa. The average droplet diameters of kerosene spray were measured by using of a laser particle sizer. Four types of integrated modular structure of pilot flame and recessed cavity flameholder with different configurations were tested to seek the required minimum hydrogen equivalence ratio for kerosene ignition and combustion sustaining. Under combined promotion of pilot hydrogen flame and recessed cavity, the required minimum hydrogen equivalence ratio of 0.03 was found in an optimized condition. Performances of the combustor were preliminarily estimated by using of the home-developed code SSC-3. A combustion efficiency of 50% was obtained in a combustor with length of 425 mm. The effects of configuration of integrated modular structure on combustor performances were discussed. © American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
KeywordCavity Flame Holders Combustion Efficiencies Combustor Performance Equivalence Ratios Modular Structures Optimized Conditions Stagnation Pressures Supersonic Combustors
Indexed ByEI
Document Type会议论文
Recommended Citation
GB/T 7714
Li JG,Yu G,Zhang XY,et al. Combustion of kerosene in a supersonic stream[C]38th Aerospace Sciences Meeting and Exhibit,2000.
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