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International Journal of Energetic Materials and Chemical Propulsion

Erscheint 6 Ausgaben pro Jahr

ISSN Druckformat: 2150-766X

ISSN Online: 2150-7678

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 0.7 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 0.7 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.1 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00016 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.18 SJR: 0.313 SNIP: 0.6 CiteScore™:: 1.6 H-Index: 16

Indexed in

GRAPHITE ROCKET NOZZLE EROSION RATE REDUCTION BY BOUNDARY-LAYER CONTROL USING ABLATIVE MATERIALS AT HIGH PRESSURES

Volumen 7, Ausgabe 5, 2008, pp. 399-419
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v7.i5.40
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ABSTRAKT

The objective of this work is to study the effect of a nozzle boundary-layer control system (NBLCS) for reducing the nozzle throat erosion rates at broad range of pressures from 7 to 48 MPa (1,000 to 7,000 psia). A comprehensive model for graphite nozzle erosion minimization (GNEM) and numerical code developed by the authors, have been advanced to include the effect of gas-mixture injection from a NBLCS, which contains four center-perforated grains of ablative materials (made of succinic acid and poly-vinyl acetate) positioned across the nozzle entrance. This design allows a small portion of hot combustion product gases generated from the rocket-motor combustor to enter into the center-perforated ablative grains, which causes the evaporation of the ablative material to produce relatively low-temperature fuel-rich gases to be injected in an upstream location of the nozzle throat station. The injection of this gas-mixture is numerically shown to reduce the bulk temperature of combustion product gases into the boundary-layer region near the throat thereby resulting in a much cooler nozzle throat surface. This injection also reduces the mass fractions of the oxidizing gaseous species such as H2O, OH, and CO2 in the combustion products, thus reducing the chemical attack on the nozzle throat surface. The erosion rates of the graphite nozzles at ultra high-pressure operating conditions are significantly reduced by several orders of magnitudes and the thermochemical erosion process becomes a kinetic-controlled process.

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