A linearized unsteady aerodynamic analysis for real blade supersonic cascades

Journal Article · Wed Oct 01 04:00:00 EDT 1997 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2841178· OSTI ID:563923

Montgomery, M D; Verdon, J M ^[1]; Fleeter, S ^[2]

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1. United Technologies Research Center, East Hartford, CT (United States)
2. Purdue Univ., West Lafayette, IN (United States). School of Mechanical Engineering

The prediction capabilities of a linearized unsteady potential analysis have been extended to include supersonic cascades with subsonic axial flow. The numerical analysis of this type of flow presents several difficulties. First, complex oblique shock patterns exist within the cascade passage. Second, the acoustic response is discontinuous and propagates upstream and downstream of the blade row. Finally, a numerical scheme based on the domain of dependence is required for numerical stability. These difficulties are addressed by developing a discontinuity capturing scheme and matching the numerical near-field solution to an analytical far-field solution. Comparisons with semi-analytic results for flat plate cascades show that reasonable predictions of the unsteady aerodynamic response at the airfoil surfaces are possible, but aeroacoustic response calculations are difficult. Comparisons between flat plate and real blade cascade results show that one effect of real blades is the impulsive loads due to motion of finite strength shocks.

• Sponsoring Organization: USDOE
• OSTI ID: 563923
• Report Number(s): CONF-960608--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 4 Vol. 119; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
AERODYNAMICS
COMPRESSOR BLADES
COMPUTER CALCULATIONS
NUMERICAL ANALYSIS
TURBINE BLADES