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Content archived on 2024-04-30

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.

Call for proposal

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Coordinator

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

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Total cost
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Participants (12)