NUMERICAL AND EXPERIMENTAL STUDY ON BLEED IMPACT ON INTERMEDIATE COMPRESSOR DUCT PERFORMANCE
Paper in proceeding, 2018

In this study, a comparison is done between an inhouse experimental test rig at GKN Aerospace and simulations done using an in-house CFD solver at Chalmers University of Technology. The geometry represents an intermediate compressor duct of an aircraft engine. The main focus is on comparing the flow field at different operating conditions. Those conditions are controlled by extracted massflow through a bleed pipe, upstream of the intermediate compressor duct. The work presented in this paper is done using a RANS solver with the Spalart Allmaras turbulence model. The CFD simulations compare well with measured data, for the lower bleed fraction, especially in terms of pressure coefficients in the intermediate compressor duct and at downstream locations. There are strong local effects due to instabilities in the bleed pipe for the higher bleed fraction, which caused the fluctuations in the pressure coefficient and resulted in degraded convergence. The difference in the flow field is also visible when comparing the operating points, where stronger total pressure wakes are noticed in the results for the lower bleed case.

Author

Elias Siggeirsson

Chalmers, Mechanics and Maritime Sciences (M2), Fluid Dynamics

Niklas Andersson

Chalmers, Mechanics and Maritime Sciences (M2), Fluid Dynamics

Fredrik Wallin

GKN Aerospace Sweden

Proceedings of ASME Turbo Expo 2018

Vol. 2B-2018 GT2018-76649
9780791851005 (ISBN)

ASME 2018 Turbo Expo
Oslo, Norway,

Areas of Advance

Transport

Subject Categories

Aerospace Engineering

Fluid Mechanics and Acoustics

Infrastructure

C3SE (Chalmers Centre for Computational Science and Engineering)

Driving Forces

Innovation and entrepreneurship

DOI

10.1115/GT2018-76649

More information

Latest update

7/17/2024