Integrated lifing analysis of a film-cooled turbine blade

Integrated lifing analysis of a film-cooled turbine blade

Tinga, T.
de Wolf, W.B.
Visser, W.P.J.
Woldendorp, S.

National Aerospace Laboratory NLR

2001-09-04

A method to predict gas turbine component life based on engine performance analysis is demonstrated on a hot section gas turbine component. The mechanical and thermal loading of the first stage high pressure turbine rotor blade of the FlOO-PW-220 engine, one of the most severely loaded components in the engine, is analyzed and a life assessment is performed. For this analysis, engine performance history is obtained from in-flight monitored engine parameters and flight conditions and downloaded for processing by a tool integrating a number of software tools and models. Data acquisition is performed by the FACE system installed in a large number of RNLAF F-16 fighter aircraft. Data then is processed by a thermodynamical engine system model, calculating gas properties like pressure and temperature at the required station in the engine. A computational fluid dynamics model, including the blade film cooling, is used to calculate the heat transfer to the blade. A thermal finite element model calculates the temperature distribution in the component and the stress distribution is obtained with a structural finite element analysis. Finally a life consumption model is used to determine the creep and fatigue damage accumulation in the component. The tool has significant potential to enhance on-condition maintenance and optimize aircraft operational use.

http://resolver.tudelft.nl/uuid:8853d21c-cb8c-4df1-9add-e7820f6bc33f

Nationaal Lucht- en Ruimtevaartlaboratorium

Campus only

NLR Technical Publication TP 2001-402

Aerospace Engineering Reports

report

(c)2001 National Aerospace Laboratory NLR