Accession Number:

ADA512637

Title:

Effects of Reacting Cross-Stream Flow on Turbine Film Cooling (Postprint)

Descriptive Note:

Conferece proceedings Postprint

Corporate Author:

AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH PROPULSION DIRECTORATE

Report Date:

2010-01-01

Pagination or Media Count:

11.0

Abstract:

Film cooling plays a critical role in providing effective thermal protection to components in modern gas turbine engines. A significant effort has been undertaken over the last 40 years to improve the distribution of coolant and to ensure that the airfoil is protected by this coolant from the hot gases in the freestream. This film, under conditions with high fuel air ratios, may actually be detrimental to the underlying metal. The presence of unburned fuel from an upstream combustor may interact with this oxygen rich film coolant jet resulting in secondary combustion. The completion of the reactions can increase the gas temperature locally resulting in higher heat transfer to the airfoil directly along the path line of the film coolant jet. This secondary combustion could damage the turbine blade, resulting in costly repair, reduction in turbine life, or even engine failure. However, knowledge of film cooling in a reactive flow is very limited. The current study explores the interaction of cooling flow from typical cooling holes with the exhaust of a fuel-rich well-stirred reactor operating at high temperatures over a flat plate.

Subject Categories:

  • Thermodynamics
  • Jet and Gas Turbine Engines
  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE