0
research-article

Influence of Combustor Swirl on Endwall Heat Transfer and Film Cooling Effectiveness at the Large Scale Turbine Rig (LSTR)

[+] Author and Article Information
Holger Werschnik

ASME Member Research Assistant Institute of Gas Turbines and Aerospace Propulsion Technische Universität Darmstadt Darmstadt, Germany, 64287
werschnik@glr.tu-darmstadt.de

Jonathan Hilgert

Research Assistant Institute of Gas Turbines and Aerospace Propulsion Technische Universität Darmstadt Darmstadt, Germany, 64287
hilgert@glr.tu-darmstadt.de

Manuel Wilhelm

Research Assistant Institute of Gas Turbines and Aerospace Propulsion Technische Universität Darmstadt Darmstadt, Germany, 64287
wilhelm@glr.tu-darmstadt.de

Martin Bruschewski

Research Associate Institute of Gas Turbines and Aerospace Propulsion Technische Universität Darmstadt Darmstadt, Germany, 64287
martin.bruschewski@uni-rostock.de

Heinz-Peter Schiffer

ASME Member Professor Institute of Gas Turbines and Aerospace Propulsion Technische Universität Darmstadt Darmstadt, Germany, 64287
schiffer@glr.tu-darmstadt.de

1Corresponding author.

ASME doi:10.1115/1.4035832 History: Received July 12, 2016; Revised January 10, 2017

Abstract

At the Large Scale Turbine Rig (LSTR) at Technische Universiẗat Darmstadt the aerothermal interaction of combustor exit flow conditions on the subsequent turbine stage is examined. The rig resembles a high pressure turbine and is scaled to low Mach numbers. A baseline configuration with axial inflow and a swirling inflow representative for a lean combustor is modeled by swirl generators, whose clocking position towards the NGV leading edge can be varied. A staggered double-row of cylindrical film cooling holes on the endwall is examined. The effect of swirling inflow on heat transfer and film cooling effectiveness is studied, while the coolant mass flux rate is varied. Nusselt numbers are calculated using infrared thermography and the auxiliary wall method. Boundary layer, turbulence and five-hole probe measurements as well as numerical simulations complement the examination. The results for swirling inflow show a decrease of film cooling effectiveness of up to 40 % and an increase of Nusselt numbers of 10-25% in comparison to the baseline case for low coolant mass flux rates. For higher coolant injection, the heat transfer is on a similar level as the baseline. The differences vary depending on the clocking position. The turbulence intensity is increased to 30 % for swirling inflow.

Copyright (c) 2017 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In