Numerical Investigation of Heat Transfer on Film‐cooled Turbine Blades

Abstract

The accurate heat transfer prediction of film‐cooled blades is a key issue for the aerothermal turbine design. For this purpose, advanced numerical methods have been developed at Snecma Moteurs. The goal of this paper is the assessment of a three‐dimensional Navier‐Stokes solver, based on the ONERA CANARI‐COMET code, devoted to the steady aerothermal computations of film‐cooled blades. The code uses a multidomain approach to discretize the blade to blade channel with overlapping structured meshes for the injection holes. The turbulence closure is done by means of either Michel mixing length model or Spalart‐Allmaras one transport equation model. Computations of thin 3D slices of three film‐cooled nozzle guide vane blades with multiple injections are performed. Aerothermal predictions are compared to experiments carried out by the von Karman Institute. The behavior of the turbulence models is discussed, and velocity and temperature injection profiles are investigated.

Evaluation of Predicted Heat Transfer on a Transonic Vane Using v2-f Turbulence Models

“…Ginibre et al [5] computed wall heat flux on a 3D slice of high pressure film cooled nozzle guide vane (NGV) with multiple rows of injections to evaluate 3D Navier-Stokes solver developed by Snecma Moteurs. The turbulence closure was done by means of algebraic mixing length model and Spalart-Allmaras one-transport equation model.…”