Shock-Boundary Layer Interactions in Supersonic Turbine Cascades
Abstract
Supersonic turbines offer size and cost reduction in high-speed propulsion and power generation systems. The detailed analysis of these systems is challenging due to the shock-boundary layer interactions (SBLIs) which arise when the detached oblique shock waves forming at the stator-rotor leading edges impinge on the boundary layers of the neighboring airfoils. The shocks impose intense adverse pressure gradients on the boundary layers that cause flow separation. This may lead to the formation of separation and reattachment shocks that interact with the turbulent boundary layers, resulting in strong pressure fluctuations and intense thermal loading which can compromise the turbine structural integrity. Moreover, the total pressure losses from the SBLIs also reduce the system s overall efficiency. Studies have been sought mainly for canonical configurations such as compression ramps and oblique shocks impinging on flat plates. Although these flow configurations allow an assessment of several physical mechanisms taking place in turbulent supersonic flows, understanding the physics of SBLI phenomena for more realistic configurations with wall curvature and confinement effects is essential to develop efficient supersonic fluid machinery, including the development of effective cooling strategies and active flow control for multi-point operation. This project aims to study supersonic turbine cascades, in particular the SBLIs taking place on both sides of the blades, and their possible interactions with the blade trailing edges. Special attention will be given to the characterization of the dynamics of the separation bubbles, shock waves and trailing edge flows
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 07, 2024
- Source ID
- FA95502310615
Entities
People
- William Wolf
Organizations
- Air Force Office of Scientific Research
- United States Air Force