Prediction of disk friction loss of centrifugal compressor impeller disk for aircraft gas turbine engine

Abstract

Using commercial CFD code (Fluent) analyzed disk friction loss for aircraft engine occur in the centrifugal compressor impeller disk. The disk friction loss is defined as the power loss due to skin friction and circulation of the fluid between the rotating disk and the stationary casing. In order to increase the efficiency of centrifugal compressor that will reduce the disk friction loss. In this study, disk friction loss due to changes the axial clearance between the impeller disk plane and casing and changes the surface roughness analyzed trend to occur and proposed the methods of reduction. For the rotating reference frame techniques were used for centrifugal compressor for steady-state analysis. The SRF (Single Rotating Reference Frame) mechanism for steady-state analysis techniques of the constant rotational motion is not used additional source or UDF (User Defined Function) and reducing computation time than Mixing plane or Sliding mesh technique and interpretation of the unsteady state. The results of CFD analysis were compared the Ali-Nemdili's empirical equation. The results of CFD analysis, the minimum result occurred when the axial clearance between the impeller disk plane and casing was 3. 5mm. A decrease of surface roughness also decreased the disk friction loss, but that had little effects.