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High Temperature Material Processes: An International Quarterly of High-Technology Plasma Processes

Publicado 4 números por año

ISSN Imprimir: 1093-3611

ISSN En Línea: 1940-4360

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: 0.4 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: 0.00005 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: 0.07 SJR: 0.198 SNIP: 0.48 CiteScore™:: 1.1 H-Index: 20

Indexed in

THERMAL STATE OF THE AIRCRAFT GAS-TURBINE ENGINE SUPPORT

Volumen 19, Edición 3-4, 2015, pp. 332-344
DOI: 10.1615/HighTempMatProc.2016017013
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SINOPSIS

The main sources of the heat transferred to the aircraft engine support are considered, the methods of their determination are studied, and their quantitative comparison in particular operating conditions of the compressor support is made. A hydraulic analysis of the air cooling of the support is sequentially performed, and distribution of the convection heat transfer coefficients and the temperature through the engine support walls is calculated based on determination of the amount of heat in each source and in accordance with the results of the preliminary thermogas-dynamic calculation. A structural heat calculation is then performed based on the data obtained. The temperature distribution in the support elements is determined according to the structural calculation. The examples of the assessment of the impact of the amount of heat generated by different sources and the impact of changes in the amount of heat in a particular source on the required rate of engine oil circulation under a particular support cooling circuit are provided. The rate of heat exchange of the sources is compared depending on the engine operating mode. The aircraft engine support thermal state determination methods that allow choosing the required cooling system and also assessing and correcting the main parameters of the engine oil system have been developed based on the calculation sequence proposed.

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