The use of Optical Pyrometers for Temperature Measurement and Evaluation of Turbine Blades

    CA Smith, Rotadata Ltd., Derby, UK. Gas Turbine O&M Expo, London, UK. 2005.

    Access to reliable engine data is a pre-requisite of avoiding unscheduled removals and premature failures. Modern air cooled turbine blades exhibit defects not detectable by traditional methods of engine condition monitoring. Rotadata optical pyrometers provide a thermal image map of individual blade surfaces under engine operating conditions. Data is used to diagnose and monitor blade abnormalities (e.g blade to blade differences; hot spots caused by TBC erosion. This allows the operator to optimise planned maintenance and dramatically reduce operating costs.


    An integrated approach to the Application of High Bandwidth Optical Pyrometry to Turbine Blade Surface Temperature Mapping

    J Douglas, CA Smith and SJR Taylor, Rotadata Ltd, Derby, UK. 18th International Congreess on Instrumentaton in Aerospace Simulation Facilities, Toulouse, France, 1999.

    As gas turbine manufacturers strive for improved efficiency the turbine operating temperatures increase which can only be met by improvements in blade and coating materials together with advances in cooling and coating technologies. The ultimate, and possibly the only, environment capable of testing modern blade systems is in a working engine and it is from this environment that a range of instrumentation technologies must acquire valid balde performance data. A critical blade parameter is the surface temperature distribution and this pape will review the various technologies currently applied to blade surface temperature distribution measurement. Optical Pyrometry, is discussed in more detail and the definition of an integrated high bandwidth detection and data collection system developed.


    A comparison of Multi Fibre and Single Fibre Optical Probes

    Dr P. Russhard, Rolls Royce, Derby, UK. 2015

    An opportunity arose in a BTT test on a has turbine HP compressor and Fan to exchange single fibre optical probes for multi-fibre probes. An analysis of the data will highlight the differences between the data sets so that the audience can make an informed judgement as to the impact of probe technology upon BTT system capability. The techniques used to extract data will be based upon previous presentations at IIS conferences demonstrating the complete end to end BTT process. The presentation will be confined to vibration modes encountered during the engine test and therefore cannot be exhaustive but will give insight to both prove and system suppliers as to the effects of different probe technologies and perceived probe resolution.


    The feasibility of Blade Tip Timing Technology Application to the Measurement of Compressor Blade Displacement

    Dr P. Russhard, Rotadata Ltd, Derby, UK. 2015

    At constant speed, non-vibrating blade tips pass the probes at equal intervals of time on each revolution. However, vibrating blades will reach the probes slightly later or earlier. Taking the difference between the expected and actual arrival times allows the calculation of individual blade tip displacements at the probe. In order to obtain the data some method of accurately detecting the revolution time and the blade arrival times are nescessary. In many applications of BTT the casual attitude to collecting data has led to a total loss of analytical capability once the test has been completed. System installations which seem trivial at first can quite easily lead to a loss of data.


    Blade Tip Timing: Initial data required to specify a BTT system configuration

    P. Russhard, Rotadata, Derby, UK. 2015

    It is nescessary to collate some key pieces of information before deciding whether a BTT system is suitable for a particular application and try and ensure that the end user is fully aware of its capabilities for each particular application. Once initial information is collated it is possible to make an estimate of the effectiveness of a BTT configuration before undertaking the design work.


    Manufacturing and Testing of TPX Lh2-Turbopump Prototype

    P. Fayolle, P.Fonteyn and F.Laither, Scecma Vernon, 27200, France., H.Olofsson, I.Forsberg, Volvo Aero Corporation, Sweden., J.Dehouve, B.Pouffary, P.Supie, Cnes, Every, France, 2010.

    A demonstration program was initiated by Snecma and Volvo Aero Corporation under CNES and SNSB support to design, manufacture, and test a new LH2-turbopump which prepares future developments in terms of reduction of cost and improvement of robustness. TPX turbopump features innovative technologies such as hydrostatic fluid-film bearings, open-face impeller, and blisk turbine, and should pave the way to a complete new family of turbopumps. This paper deals first with the preparation of TPX prototype hardware; major manufacturing and assembly achievements are described, including implementation of instrusive instrumentation. Then, the objectives of the test campaign performed at Snecma cryogenic test facility in 2010 are recalled, as part of the Vulcain X engine demonstration program. Finally, the first test results obtained for the turbopump alone (turbine fed by cold gas) are briefly discussed.

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