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Aeromechanical design of turbine blades

Objective



Objectives and content

- Package A: Turbine External Flows
The improvement of the aerodynamics and film cooling of high pressure turbine is of prime importance for the overall performance of this major component of aicraft engines and power generators. This project aims at improving both the knowledge of the physical phenomena involved and the prediction capabilities. A substantial effort is dedicated to a detailed experimental investigation of unsteady aerodynamics and heat transfer of several "scale 1" full turbines. Different types of cooling as well as the influence of technological constraints are studied or taken into account. These investigations on actual full turbine geometries will help the understanding of the complex flow-field and will constitute a large and sharable data base necessary for the validation of advanced CFD methods. They will be completed by fundamental experimental studies on large scale facilities that will give a better insight of the "driving" physical phenomena and suggest new ideas for the irnprovement of the classical technologies. New advanced CFD methods will also be developed, adapted and tested against the experimental results. Moreover a thorough test of the available advanced CFD methods will be performed by the industrial partners on the data base and will help a fruitful cooperation for the analysis of the experimental results. All these activities take benefit from previous works and facilities elaborated or performed in the European framework.

- Package B: Turbine Internal Blade Cooling
The work proposed in this package is dedicated to the improvement of turbine internal blade cooling devices conception methods. Up to date methods are mainly empirical, based on experimental data arising from static model tests. Nevertheless, rotation has proved in recent experiments to have a dramatical influence on heat transfer rates in blade cooling passages, compared to those computed with static methods. Furthermore, CFD applications involving conventional treatment of turbulence- have shown poor capabilities for predicting heat transfer in such passages. The proposed package will consist mainly in conducting experiments on existing European rigs for realistic geometries and engine representative conditions, in order to provide the industrials with data bases usable for the derivation of correlative conception methods, and for the assessment of up to date CFD methods.

- Package C: HP Turbine Blade forced response
This package of work focuses exclusively on the prediction of turbine rotor blade dynamic characteristics when subject to aerodynamically induced vibration and the implications for structural integrity. Vibrational stresses can be caused by flow perturbations from upstream nozzle guide vanes. If sufficiently high alternating stresses are generated HCF cracking can occur which can propagate very rapidly to blade failure leading to in-flight engine shutdown. However, the emphasis of this package is put on the discrimination of all the necessary components in blade forced response predictions.

Funding Scheme

CSC - Cost-sharing contracts

Coordinator

Rolls Royce PLC
Address
Moor Lane
DE24 8BJ Derby
United Kingdom

Participants (12)

ABB Kraftwerke Ltd
Switzerland
Address

5401 Baden
BMW Rolls-Royce GmbH - Aeroengines
Germany
Address
11,Eschenweg
15827 Dahlewitz
FIAT AVIO SPA
Italy
Address
Via Nizza 312
10127 Torino (Turin)
GERMAN AEROSPACE CENTRE
Germany
Address
10,Bunsenstrasse 10
37073 Goettingen
Industria de Turbo Propulsores SA
Spain
Address
300,Parove Tecnologico 300
48016 Zamudio - Vizcaya
Kungliga Tekniska Högskolan
Sweden
Address
60,Brinellvägen 60
100 44 Stockholm
Office National d'Etudes et de Recherches A?rospatiales
France
Address
29 Avenue De La Division Leclerc
92322 Châtillon
SOCIETE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION
France
Address
Site De Villaroche, Rond Point Rene Ravaud - Reau
77550 Moissy Cramayel
SWISS FEDERAL INSTITUTE OF TECHNOLOGY LAUSANNE
Switzerland
Address
Ecublens
1015 Lausanne
THE CHANCELLOR, MASTERS AND SCHOLARS OF THE UNIVERSITY OF OXFORD
United Kingdom
Address
Parks Road
OX1 3PJ Oxford
TURBOMECA SA
France
Address
Avenue Du President Szydlowski
Bordes
UNIVERSITY OF LIMERICK
Ireland
Address
Plassey Technological Park
61 Limerick