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research-article

Aerothermal Optimization of Fully Cooled Turbine Blade Tips

[+] Author and Article Information
Valeria Andreoli

Purdue University - Zucrow Laboratories, West Lafayette, IN, United States
vale.andreoli@gmail.com

James Braun

Purdue University - Zucrow Laboratories, West Lafayette, IN, United States
jamesbraun91@gmail.com

Guillermo Paniagua

Purdue University - Zucrow Laboratories, West Lafayette, IN, United States
gpaniagua@me.com

Cis De Maesschalck

Rolls-Royce plc, Derby, United Kingdom
cis.demaesschalck@gmail.com

Matthew Bloxham

Rolls-Royce Corporation, Indianapolis, IN, United States
Matthew.Bloxham@Rolls-Royce.com

Bill Cummings

Rolls-Royce Corporation, Indianapolis, IN, United States
william.cummings2@rolls-royce.com

Lawrence Langford

Rolls-Royce Corporation, Indianapolis, IN, United States
lawrence.langford@rolls-royce.com

1Corresponding author.

ASME doi:10.1115/1.4041961 History: Received October 21, 2018; Revised November 07, 2018

Abstract

Optimal turbine blade tip designs have the potential to enhance aerodynamic performance while reducing the thermal loads on one of the most vulnerable parts of the gas turbine. This paper describes a novel strategy to perform a multi-objective optimization of the tip geometry of a cooled turbine blade. The parameterization strategy generates arbitrary rim shapes around the coolant holes on the blade tip. The tip geometry performance is assessed using steady Reynolds-Averaged Navier-Stokes simulations with the k-? SST model for the turbulence closure. The fluid domain is discretized with hexahedral elements, and the entire optimization is performed using identical mesh characteristics in all simulations. This is done to ensure an adequate comparison among all investigated designs. Isothermal walls were imposed at engine-representative levels to compute the convective heat flux for each case. The optimization objectives were a reduction in heat load and an increase in turbine row efficiency. The multi-objective optimization is performed using a differential evolution strategy. Improvements were achieved in both the aerodynamic efficiency and heat load reduction, relative to a conventional squealer tip arrangement. Furthermore, this work demonstrates that the inclusion of over-tip coolant flows impacts the over-tip flow field, and that the rim-coolant interaction can be used to create a synergistic performance enhancement.

Rolls-Royce plc
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