Numerical simulation of unsteady fluid flow and heat transfer in a transonic turbine stage
(2006) 2006 ASME International Mechanical Engineering Congress and Exposition, IMECE2006- Abstract
- With the attempts to increase power, efficiency and thrust, modern gas turbines operate with combustor outlet temperatures of 1800-2000 K, which are far beyond the allowable metal temperatures. Turbine blades are exposed to these high temperature gases and may undergo severe thermal stress and fatigue. Thus, in order to develop optimal cooling strategies and reduce the heat transfer it is important to obtain a good understanding of both the complex flow field and the heat transfer characteristics in a turbine rotor/stator hot-gas passage. In the past decade computational fluid dynamics (CFD) have started to play an increasingly important role and be an effective tool in the study and analysis of complex flow and the design of more... (More)
- With the attempts to increase power, efficiency and thrust, modern gas turbines operate with combustor outlet temperatures of 1800-2000 K, which are far beyond the allowable metal temperatures. Turbine blades are exposed to these high temperature gases and may undergo severe thermal stress and fatigue. Thus, in order to develop optimal cooling strategies and reduce the heat transfer it is important to obtain a good understanding of both the complex flow field and the heat transfer characteristics in a turbine rotor/stator hot-gas passage. In the past decade computational fluid dynamics (CFD) have started to play an increasingly important role and be an effective tool in the study and analysis of complex flow and the design of more efficient machinery components. The simulation of gas flow in turbomachines are challenging because of the complicated rotating geometries and unsteady flow nature. Modern turbomachinery operates under extremely complex three-dimensional and turbulent flow conditions, and it is difficult to accurately predict the heat loads on the blades. The objective of this work is to understand the unsteady flow field and heat transfer in a single transonic turbine stage using an unsteady quasi-3D structured Navier-Stokes solver. For the time accurate computation, a fully implicit time discretization, dual-time stepping, is performed. The results of the CFD simulations are compared with experimental heat transfer and aerodynamic results available for the so-called MT1 turbine stage. The predicted heat transfer and static pressure distributions show reasonable agreement with experimental data. (Less)
Please use this url to cite or link to this publication:
https://lup.lub.lu.se/record/594134
- author
- Mumic, Fadil LU and Sundén, Bengt LU
- organization
- publishing date
- 2006
- type
- Contribution to conference
- publication status
- published
- subject
- conference name
- 2006 ASME International Mechanical Engineering Congress and Exposition, IMECE2006
- conference location
- Chicago, IL, United States
- conference dates
- 2006-11-05 - 2006-11-10
- external identifiers
-
- other:IMECE2006-13668
- scopus:84920633435
- language
- English
- LU publication?
- yes
- id
- 816eb0a8-101b-4bc2-bf08-a8b2a16489b3 (old id 594134)
- date added to LUP
- 2016-04-04 14:33:24
- date last changed
- 2022-01-30 02:11:50
@misc{816eb0a8-101b-4bc2-bf08-a8b2a16489b3,
abstract = {{With the attempts to increase power, efficiency and thrust, modern gas turbines operate with combustor outlet temperatures of 1800-2000 K, which are far beyond the allowable metal temperatures. Turbine blades are exposed to these high temperature gases and may undergo severe thermal stress and fatigue. Thus, in order to develop optimal cooling strategies and reduce the heat transfer it is important to obtain a good understanding of both the complex flow field and the heat transfer characteristics in a turbine rotor/stator hot-gas passage. In the past decade computational fluid dynamics (CFD) have started to play an increasingly important role and be an effective tool in the study and analysis of complex flow and the design of more efficient machinery components. The simulation of gas flow in turbomachines are challenging because of the complicated rotating geometries and unsteady flow nature. Modern turbomachinery operates under extremely complex three-dimensional and turbulent flow conditions, and it is difficult to accurately predict the heat loads on the blades. The objective of this work is to understand the unsteady flow field and heat transfer in a single transonic turbine stage using an unsteady quasi-3D structured Navier-Stokes solver. For the time accurate computation, a fully implicit time discretization, dual-time stepping, is performed. The results of the CFD simulations are compared with experimental heat transfer and aerodynamic results available for the so-called MT1 turbine stage. The predicted heat transfer and static pressure distributions show reasonable agreement with experimental data.}},
author = {{Mumic, Fadil and Sundén, Bengt}},
language = {{eng}},
title = {{Numerical simulation of unsteady fluid flow and heat transfer in a transonic turbine stage}},
year = {{2006}},
}