Gas film riding seals have found wide acceptance in pipeline and process industry turbomachinery. The seals have not found many applications in either industrial or aircraft gas turbines, however. Gas turbine engines currently being designed will have higher compression ratios (greater than 30:1). The combination of increased pressure and more aggressive engine efficiency goals will severely tax the capability of present sealing systems. The film riding face seal (FRFS) has emerged as an attractive candidate for providing sealing for the hot high pressure engine compressor discharge air. Gas turbine relative surface velocity and temperature requirements in general, exceed those of other applications. In addition, the aerospace nature of the product imposes restrictions on the allowable size and weight of the seal. This paper describes development efforts currently under way to adapt the gas film riding face seal for the aircraft gas turbine engine. Also described are anticipated operational parameters for the next generation of engines, and challenges which need to be overcome to successfully apply these seals to these engines.


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    Titel :

    Development of film riding face seals for a gas turbine engine


    Weitere Titelangaben:

    Entwicklung von Gasfilm-Dichtungen für eine Gasturbine


    Beteiligte:
    Munson, J. (Autor:in) / Pecht, G. (Autor:in)


    Erscheinungsdatum :

    1991


    Format / Umfang :

    6 Seiten, 9 Bilder, 2 Tabellen, 10 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch





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