Simulation of a multi-stage cooling scheme for gas turbine engines: Part I

M. Ghorab, Ibrahim Hassan, M. Beauchamp

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Citations (Scopus)

Abstract

This paper presents heat transfer characteristics for a Multi-Stage Cooling Scheme (MSCS) design applicable to high temperature gas turbine engines in aerospace and electric power generation. The film cooling and impingement techniques are considered concurrently throughout this study. The proposed design involves passing cooling air from the inside of the turbine blade to the outside through three designed stages. The coolant air is passed through a circular hole into an internal gap creating an impingement of air inside the blade. It then exits through a sequence of two differently shaped holes onto the blade's external surface. The film cooling effectiveness is enhanced by increasing the internal gap height and offset distance. This effect is significantly diminished however by changing the inclination angle from 90° to 30° at large gap height. The coolant momentum became more uniform by creating the internal gap consequently the coolant air is spread closer to the external blade surface. This reduces jet liftoff as the air exits its hole and also provides internal cooling for the blade. The hole exit positioned on the outer surface of the blade is designed to give a positive and a wide downstream lateral spreading. The MSCS demonstrates greater film cooling effectiveness performance than traditional schemes.

Original languageEnglish
Title of host publicationProceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air
Pages821-832
Number of pages12
Volume4 PART B
DOIs
Publication statusPublished - 2007
Externally publishedYes
Event2007 ASME Turbo Expo - Montreal, Que., Canada
Duration: 14 May 200717 May 2007

Other

Other2007 ASME Turbo Expo
CountryCanada
CityMontreal, Que.
Period14/5/0717/5/07

Fingerprint

Gas turbines
Turbines
Cooling
Coolants
Air
Electric power generation
Turbomachine blades
Momentum
Heat transfer
Temperature

Keywords

  • CFD
  • Film cooling
  • Gas turbine
  • Heat transfer
  • Impingement
  • MSCS

ASJC Scopus subject areas

  • Engineering(all)

Cite this

Ghorab, M., Hassan, I., & Beauchamp, M. (2007). Simulation of a multi-stage cooling scheme for gas turbine engines: Part I. In Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air (Vol. 4 PART B, pp. 821-832) https://doi.org/10.1115/GT2007-28036

Simulation of a multi-stage cooling scheme for gas turbine engines : Part I. / Ghorab, M.; Hassan, Ibrahim; Beauchamp, M.

Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. Vol. 4 PART B 2007. p. 821-832.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Ghorab, M, Hassan, I & Beauchamp, M 2007, Simulation of a multi-stage cooling scheme for gas turbine engines: Part I. in Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. vol. 4 PART B, pp. 821-832, 2007 ASME Turbo Expo, Montreal, Que., Canada, 14/5/07. https://doi.org/10.1115/GT2007-28036
Ghorab M, Hassan I, Beauchamp M. Simulation of a multi-stage cooling scheme for gas turbine engines: Part I. In Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. Vol. 4 PART B. 2007. p. 821-832 https://doi.org/10.1115/GT2007-28036
Ghorab, M. ; Hassan, Ibrahim ; Beauchamp, M. / Simulation of a multi-stage cooling scheme for gas turbine engines : Part I. Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. Vol. 4 PART B 2007. pp. 821-832
@inproceedings{b3125820d1d64c05a6092c80a2e078f4,
title = "Simulation of a multi-stage cooling scheme for gas turbine engines: Part I",
abstract = "This paper presents heat transfer characteristics for a Multi-Stage Cooling Scheme (MSCS) design applicable to high temperature gas turbine engines in aerospace and electric power generation. The film cooling and impingement techniques are considered concurrently throughout this study. The proposed design involves passing cooling air from the inside of the turbine blade to the outside through three designed stages. The coolant air is passed through a circular hole into an internal gap creating an impingement of air inside the blade. It then exits through a sequence of two differently shaped holes onto the blade's external surface. The film cooling effectiveness is enhanced by increasing the internal gap height and offset distance. This effect is significantly diminished however by changing the inclination angle from 90° to 30° at large gap height. The coolant momentum became more uniform by creating the internal gap consequently the coolant air is spread closer to the external blade surface. This reduces jet liftoff as the air exits its hole and also provides internal cooling for the blade. The hole exit positioned on the outer surface of the blade is designed to give a positive and a wide downstream lateral spreading. The MSCS demonstrates greater film cooling effectiveness performance than traditional schemes.",
keywords = "CFD, Film cooling, Gas turbine, Heat transfer, Impingement, MSCS",
author = "M. Ghorab and Ibrahim Hassan and M. Beauchamp",
year = "2007",
doi = "10.1115/GT2007-28036",
language = "English",
isbn = "079184790X",
volume = "4 PART B",
pages = "821--832",
booktitle = "Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air",

}

TY - GEN

T1 - Simulation of a multi-stage cooling scheme for gas turbine engines

T2 - Part I

AU - Ghorab, M.

AU - Hassan, Ibrahim

AU - Beauchamp, M.

PY - 2007

Y1 - 2007

N2 - This paper presents heat transfer characteristics for a Multi-Stage Cooling Scheme (MSCS) design applicable to high temperature gas turbine engines in aerospace and electric power generation. The film cooling and impingement techniques are considered concurrently throughout this study. The proposed design involves passing cooling air from the inside of the turbine blade to the outside through three designed stages. The coolant air is passed through a circular hole into an internal gap creating an impingement of air inside the blade. It then exits through a sequence of two differently shaped holes onto the blade's external surface. The film cooling effectiveness is enhanced by increasing the internal gap height and offset distance. This effect is significantly diminished however by changing the inclination angle from 90° to 30° at large gap height. The coolant momentum became more uniform by creating the internal gap consequently the coolant air is spread closer to the external blade surface. This reduces jet liftoff as the air exits its hole and also provides internal cooling for the blade. The hole exit positioned on the outer surface of the blade is designed to give a positive and a wide downstream lateral spreading. The MSCS demonstrates greater film cooling effectiveness performance than traditional schemes.

AB - This paper presents heat transfer characteristics for a Multi-Stage Cooling Scheme (MSCS) design applicable to high temperature gas turbine engines in aerospace and electric power generation. The film cooling and impingement techniques are considered concurrently throughout this study. The proposed design involves passing cooling air from the inside of the turbine blade to the outside through three designed stages. The coolant air is passed through a circular hole into an internal gap creating an impingement of air inside the blade. It then exits through a sequence of two differently shaped holes onto the blade's external surface. The film cooling effectiveness is enhanced by increasing the internal gap height and offset distance. This effect is significantly diminished however by changing the inclination angle from 90° to 30° at large gap height. The coolant momentum became more uniform by creating the internal gap consequently the coolant air is spread closer to the external blade surface. This reduces jet liftoff as the air exits its hole and also provides internal cooling for the blade. The hole exit positioned on the outer surface of the blade is designed to give a positive and a wide downstream lateral spreading. The MSCS demonstrates greater film cooling effectiveness performance than traditional schemes.

KW - CFD

KW - Film cooling

KW - Gas turbine

KW - Heat transfer

KW - Impingement

KW - MSCS

UR - http://www.scopus.com/inward/record.url?scp=34548762637&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=34548762637&partnerID=8YFLogxK

U2 - 10.1115/GT2007-28036

DO - 10.1115/GT2007-28036

M3 - Conference contribution

AN - SCOPUS:34548762637

SN - 079184790X

SN - 9780791847909

VL - 4 PART B

SP - 821

EP - 832

BT - Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air

ER -