Evaluation of flow field approximations for transonic compressor stages

Journal Article · Tue Jul 01 04:00:00 EDT 1997 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2841143· OSTI ID:516713

Dorney, D J ^[1]; Sharma, O P ^[2]

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1. Western Michigan Univ., Kalamazoo, MI (United States)
2. Pratt and Whitney, East Hartford, CT (United States)

The flow through gas turbine compressors is often characterized by unsteady, transonic, and viscous phenomena. Accurately predicting the behavior of these complex multi-blade-row flows with unsteady rotor-stator interacting Navier-Stokes analyses can require enormous computer resources. In this investigation, several methods for predicting the flow field, losses, and performance quantities associated with axial compressor stages are presented. The methods studied include: (1) the unsteady fully coupled blade row technique, (2) the steady coupled blade row method, (3) the steady single blade row technique, and (4) the loosely coupled blade row method. The analyses have been evaluated in terms of accuracy and efficiency.

• OSTI ID: 516713
• Report Number(s): CONF-960608--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 3 Vol. 119; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
COMPUTERIZED SIMULATION
FLUID FLOW
GAS COMPRESSORS
GAS TURBINE ENGINES
TRANSONIC FLOW
TURBULENT FLOW
UNSTEADY FLOW
VISCOUS FLOW