Skip to Main content Skip to Navigation
Theses

Contribution to Aerothermal Study of a Film Cooling Geometric Design using ZnO Phosphorescence Thermography and Numerical Simulations

Abstract : Film cooling of aircraft gas turbine blades has been in use since a few decades now to improve the Turbine Inlet Temperature (TIT) and to extend the lifetime of the turbine blade. Additionally, stringent emission norms stipulate the improvement of overall efficiency of the gas turbine engine and hence the need to improve film cooling process. Film cooling is a technique where a cold jet is injected through discrete holes on the surface of the turbine blade, so as to form a layer of cool air over the surface of the blade, effectively protecting the blade from high temperature crossflows arising from the combustion chamber. This problem can be viewed as a Jet In Cross-Flow (JICF) phenomena where the interaction of the crossflow with a jet injected perpendicular or at an angle creates a system of vortices. One of the most important vortex systems in this arrangement is the Counter Rotating Vortex Pair arising from the shear forces at the sides of the ejecting jet with the crossflow primarily. The bending of the jet along the direction of the crossflow promotes the CRVP to ingest hot crossflow into the jet stream which reduces the effectiveness of the film cooling system. Hence, in this study, an auxiliary hole system is studied experimentally and numerically to reduce the intensity and the height of the CRVP which eventually helps in an augmented adiabatic film cooling effectiveness. The auxiliary holes placed upstream of the main film cooling hole reduces the intensity of the main hole CRVP due to the reduction in the shear forces experienced by the jet emanating from the main hole. In this thesis numerical analysis through RANS study using k-ω SST turbulence model to have a preliminary understanding of the auxiliary hole system and a detailed understanding of the flow structure using Large Eddy Simulation are performed. The highlight of this work is the development of single camera phosphor thermometry using the spectral intensity ratio method. This technique allows the measurement of the instantaneous and mean flow temperature non-intrusively. A detailed analysis of the emission properties of ZnO phosphor upon excitation by a 266nm laser is described. A calibration procedure for the intensity ratio method is defined and it is tested using a Rayleigh-Bénard natural convection process. This phosphor thermometry procedure with the validated code is implemented on the new BATH test Rig to study film cooling arrangements. Three different configurations are tested for their aero-thermal characteristics at penetration blowing ratio regime. Analysis of the experimental and numerical results help in identifying key vortex structures, leading to the better understanding of reasons for the augmentation of film cooling effectiveness in the auxiliary hole system compared to a classical simple cylindrical hole.
Document type :
Theses
Complete list of metadata

https://tel.archives-ouvertes.fr/tel-03771422
Contributor : ABES STAR :  Contact
Submitted on : Wednesday, September 7, 2022 - 1:12:59 PM
Last modification on : Thursday, September 8, 2022 - 3:40:12 AM

File

2022ESMA0006_subramanian.pdf
Version validated by the jury (STAR)

Identifiers

  • HAL Id : tel-03771422, version 1

Collections

Citation

Arunprasath Subramanian. Contribution to Aerothermal Study of a Film Cooling Geometric Design using ZnO Phosphorescence Thermography and Numerical Simulations. Other. ISAE-ENSMA Ecole Nationale Supérieure de Mécanique et d'Aérotechique - Poitiers, 2022. English. ⟨NNT : 2022ESMA0006⟩. ⟨tel-03771422⟩

Share

Metrics

Record views

13

Files downloads

0