Low pressure turbine airfoils of the present generation usually operate at subsonic conditions, with exit Mach numbers of about 0.6. To reduce the costs of experimental programs it can be convenient to carry out measurements in low speed tunnels in order to determine the cascades performance. Generally speaking, low speed tests are usually carried out on airfoils with modified shape, in order to compensate for the effects of compressibility. A scaling procedure for high-lift, low pressure turbine airfoils to be studied in low speed conditions is presented and discussed. The proposed procedure is based on the matching of a prescribed blade load distribution between the low speed airfoil and the actual one. Such a requirement is fulfilled via an Artificial Neural Network (ANN) methodology and a detailed parameterization of the airfoil. A RANS solver is used to guide the redesign process. The comparison between high and low speed profiles is carried out, over a wide range of Reynolds numbers, by using a novel three-equation, transition-sensitive, turbulence model. Such a model is based on the coupling of an additional transport equation for the so-called laminar kinetic energy (LKE) with the Wilcox k-omega model and it has proven to be effective for transitional, separated-flow configurations of high-lift cascade flows.

Redesign of High-Lift Low Pressure Turbine Airfoils For Low Speed Testing / M. Marconcini; F. Rubechini; R. Pacciani; A. Arnone; F. Bertini. - In: JOURNAL OF TURBOMACHINERY. - ISSN 0889-504X. - ELETTRONICO. - 134:(2012), pp. 051017-1-051017-8. [10.1115/1.4004474]

Redesign of High-Lift Low Pressure Turbine Airfoils For Low Speed Testing

MARCONCINI, MICHELE;RUBECHINI, FILIPPO;PACCIANI, ROBERTO;ARNONE, ANDREA;
2012

Abstract

Low pressure turbine airfoils of the present generation usually operate at subsonic conditions, with exit Mach numbers of about 0.6. To reduce the costs of experimental programs it can be convenient to carry out measurements in low speed tunnels in order to determine the cascades performance. Generally speaking, low speed tests are usually carried out on airfoils with modified shape, in order to compensate for the effects of compressibility. A scaling procedure for high-lift, low pressure turbine airfoils to be studied in low speed conditions is presented and discussed. The proposed procedure is based on the matching of a prescribed blade load distribution between the low speed airfoil and the actual one. Such a requirement is fulfilled via an Artificial Neural Network (ANN) methodology and a detailed parameterization of the airfoil. A RANS solver is used to guide the redesign process. The comparison between high and low speed profiles is carried out, over a wide range of Reynolds numbers, by using a novel three-equation, transition-sensitive, turbulence model. Such a model is based on the coupling of an additional transport equation for the so-called laminar kinetic energy (LKE) with the Wilcox k-omega model and it has proven to be effective for transitional, separated-flow configurations of high-lift cascade flows.
2012
134
051017-1
051017-8
M. Marconcini; F. Rubechini; R. Pacciani; A. Arnone; F. Bertini
File in questo prodotto:
File Dimensione Formato  
JTM-v134-2012-051017.pdf

Accesso chiuso

Descrizione: Articolo
Tipologia: Pdf editoriale (Version of record)
Licenza: Tutti i diritti riservati
Dimensione 2.22 MB
Formato Adobe PDF
2.22 MB Adobe PDF   Richiedi una copia

I documenti in FLORE sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificatore per citare o creare un link a questa risorsa: https://hdl.handle.net/2158/390596
Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus 13
  • ???jsp.display-item.citation.isi??? 13
social impact