Experimental and Computational Study of Heat Transfer on a Turbine Blade Tip with a Shelf
Cooling of turbine parts in a gas turbine engine is necessary for operation as the temperature of combustion gases is higher than the melting temperature of the turbine materials. The gap between rotating turbine blades and the stationary shroud provides an unintended flow path for hot gases. Gases...
Main Author: | |
---|---|
Other Authors: | |
Format: | Others |
Language: | en_US |
Published: |
Virginia Tech
2017
|
Subjects: | |
Online Access: | http://hdl.handle.net/10919/76906 http://scholar.lib.vt.edu/theses/available/etd-02222005-134558/ |
id |
ndltd-VTETD-oai-vtechworks.lib.vt.edu-10919-76906 |
---|---|
record_format |
oai_dc |
spelling |
ndltd-VTETD-oai-vtechworks.lib.vt.edu-10919-769062020-09-29T05:44:29Z Experimental and Computational Study of Heat Transfer on a Turbine Blade Tip with a Shelf Morris, Angela Mechanical Engineering Thole, Karen A. Ng, Wing Fai Huxtable, Scott T. film-cooling gas turbines tip gap blade heat transfer Cooling of turbine parts in a gas turbine engine is necessary for operation as the temperature of combustion gases is higher than the melting temperature of the turbine materials. The gap between rotating turbine blades and the stationary shroud provides an unintended flow path for hot gases. Gases that flow through the tip region cause pressure losses in the turbine section and high heat loads to the blade tip. This thesis studies the heat transfer on an innovative tip geometry intended to help reduce aerodynamic losses. The blade tip has a depression (shelf) on the tip surface along much of the pressure side of the blade and film-cooling holes along the depression. This research experimentally measured the effect of the shelf, coolant flow and tip gap on heat transfer on the blade tip. Stationary experiments were performed in a low speed wind tunnel on a linear cascade with two different tip gaps and multiple coolant flow rates through the film-cooling holes. Tests showed that baseline Nusselt numbers on the tip surface were reduced with the shelf tip compared with a flat tip. Measurements indicated that film-cooling was more effective with a small tip gap than with a large tip gap. Experimental and computational results demonstrated a lack of coolant spreading that was detrimental to regions between the film-cooling holes. While the coolant was effective on the blade tip, the leading and trailing edge regions were found to have high heat transfer coefficients with little available cooling. Master of Science 2017-04-04T19:50:12Z 2017-04-04T19:50:12Z 2005-02-10 2005-02-22 2016-10-07 2005-06-13 Thesis Text etd-02222005-134558 http://hdl.handle.net/10919/76906 http://scholar.lib.vt.edu/theses/available/etd-02222005-134558/ en_US In Copyright http://rightsstatements.org/vocab/InC/1.0/ application/pdf Virginia Tech |
collection |
NDLTD |
language |
en_US |
format |
Others
|
sources |
NDLTD |
topic |
film-cooling gas turbines tip gap blade heat transfer |
spellingShingle |
film-cooling gas turbines tip gap blade heat transfer Morris, Angela Experimental and Computational Study of Heat Transfer on a Turbine Blade Tip with a Shelf |
description |
Cooling of turbine parts in a gas turbine engine is necessary for operation as the temperature of combustion gases is higher than the melting temperature of the turbine materials. The gap between rotating turbine blades and the stationary shroud provides an unintended flow path for hot gases. Gases that flow through the tip region cause pressure losses in the turbine section and high heat loads to the blade tip. This thesis studies the heat transfer on an innovative tip geometry intended to help reduce aerodynamic losses. The blade tip has a depression (shelf) on the tip surface along much of the pressure side of the blade and film-cooling holes along the depression. This research experimentally measured the effect of the shelf, coolant flow and tip gap on heat transfer on the blade tip.
Stationary experiments were performed in a low speed wind tunnel on a linear cascade with two different tip gaps and multiple coolant flow rates through the film-cooling holes. Tests showed that baseline Nusselt numbers on the tip surface were reduced with the shelf tip compared with a flat tip. Measurements indicated that film-cooling was more effective with a small tip gap than with a large tip gap. Experimental and computational results demonstrated a lack of coolant spreading that was detrimental to regions between the film-cooling holes. While the coolant was effective on the blade tip, the leading and trailing edge regions were found to have high heat transfer coefficients with little available cooling. === Master of Science |
author2 |
Mechanical Engineering |
author_facet |
Mechanical Engineering Morris, Angela |
author |
Morris, Angela |
author_sort |
Morris, Angela |
title |
Experimental and Computational Study of Heat Transfer on a Turbine Blade Tip with a Shelf |
title_short |
Experimental and Computational Study of Heat Transfer on a Turbine Blade Tip with a Shelf |
title_full |
Experimental and Computational Study of Heat Transfer on a Turbine Blade Tip with a Shelf |
title_fullStr |
Experimental and Computational Study of Heat Transfer on a Turbine Blade Tip with a Shelf |
title_full_unstemmed |
Experimental and Computational Study of Heat Transfer on a Turbine Blade Tip with a Shelf |
title_sort |
experimental and computational study of heat transfer on a turbine blade tip with a shelf |
publisher |
Virginia Tech |
publishDate |
2017 |
url |
http://hdl.handle.net/10919/76906 http://scholar.lib.vt.edu/theses/available/etd-02222005-134558/ |
work_keys_str_mv |
AT morrisangela experimentalandcomputationalstudyofheattransferonaturbinebladetipwithashelf |
_version_ |
1719345843664846848 |