Turbotech. Teilprojekt 1.1.2.4: Rotationssymmetrische Berechnung der Meridianstroemung in vielstufigen Axialverdichtern unter Einbeziehung der Gittercharakteristiken und Seitenwandgrenzschicht Abschlussbericht

The objective of this study is to develop a method for calculating the meridian flow field in multistage, highly loaded axial-flow compressors with variable geometry. For the present state of research, the complexity of the flow field present in a multistage turbomachine requires considerable concessions with regard to the general applicability of the numerical methods used. Although first promising applications of three-dimensional field methods have been existing for the calculation of multistage turbomachinery, the use of these methods for the calculation of multistage machinery is not to be expected in the foreseeable future. Therefore, the meridian flow methods based on the assumption of rotationally symmetrical flow have become generally accepted for technical problems. Within the framework of the present study, therefore, a method for the calculation of the meridian flow field in multistage axial-flow compressors was developed on the basis of the finite element method. A newly developed iteration method helps mastering the problems occurring during the recalculation of compressors with high compression ratio as a result of the nonlinearity of the equation of motion. The calculation of side wall boundary layer development using a two-dimensional integral method permits modeling the boundary layer stabilization which was experimentally verified for multistage axial-flow compressors. In addition to this, such a method, besides determining the annular chamber blocking, can be used to make statements on the boundary loss. (orig.)SIGLEAvailable from TIB Hannover: F95B1957+a / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekBundesministerium fuer Forschung und Technologie (BMFT), Bonn (Germany); Siemens AG, Erlangen (Germany)DEGerman