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A MISTUNED FORCED RESPONSE ANALYSIS OF AN EMBEDDED COMPRESSORBLISK USING A REDUCED ORDER MODEL
(Energy Technology)
KTH, School of Industrial Engineering and Management (ITM), Energy Technology.
2018 (English)In: Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference, 2018Conference paper, Published paper (Refereed)
Abstract [en]

Accuracy when assessing mistuned forced response analysesis still a mayor concern. Since a full coupled analysis is still verycomputational expensive, several simplifications and reduced ordermodels are carried out. The use of a reduction method, theassumptions and simplifications, generate different uncertaintiesthat challenge the accuracy in the results. Experimental dataare needed for validation and also to understand the propagationof these uncertainties. This paper shows a detailed mistunedforced response analysis of a compressor blisk. The blisk belongsto the Purdue Three-Stage(P3S) Compressor Research Facility.Two different stator-rotor-stator configurations of 38 and 44 upstreamstator vanes are taken into consideration. Several loadingconditions are analyzed at three different speed lines. A reducedorder model known as subset nominal mode (SNM), has beenused for all the analyses. This reduction takes as a basis a setof modes within a selected frequency spectrum. A detailed comparisonbetween the predicted and measured results have beenperformed, showing a good agreement for the high loading conditions.

Place, publisher, year, edition, pages
2018.
Keyword [en]
aeroelasticity, fem, reduced order models, ROM, craig-bampton, craig-chang, subset nominal mode, snm, forced response, mistuning, mistuned, flutter, high cycle fatigue
National Category
Aerospace Engineering
Research subject
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-227657OAI: oai:DiVA.org:kth-227657DiVA, id: diva2:1205012
Conference
ASME Turbo Expo 2018
Note

QC 20180514

Available from: 2018-05-09 Created: 2018-05-09 Last updated: 2018-05-14Bibliographically approved
In thesis
1. Development of Accurate Reduced Order Models in a Simulation Tool for Turbomachinery Aeromechanical Phenomena
Open this publication in new window or tab >>Development of Accurate Reduced Order Models in a Simulation Tool for Turbomachinery Aeromechanical Phenomena
2018 (English)Doctoral thesis, comprehensive summary (Other academic)
Abstract [en]

Modern gas turbines are still vulnerable to vibrations when operated at certain speeds. This unstable environment can lead to high cycle fatigue (HCF) and damage several of the components inside the turbine. Since engineers are striving to increase the turbines’ efficiency with thinner and more complex blade shapes, these critical speeds will always be present. For these reasons, aeromechanical analyses that is the study of structural and aerodynamic forces need to be assessed with a high level of accuracy. Since this type of analysis are very computational expensive, reduced order models (ROMs) are utilized to decrease the degrees of freedom (DoF) for a faster computation without compromising the accuracy. The present work focuses on cyclic and noncyclic ROMs implemented in an already existing aeroelastic tool, with different characteristics in their condensation and ease of usage depending on the analysis.

 

The AROMA (Aeroelastic Reduced Order Model Analysis) tool has been previously developed to predict the fatigue life of turbomachinery blades with the use of ROMs. The aim of this work has been to improve the tool in terms of accuracy, flexibility and speed, by employing additional reduction methods capable to predict forced responses analysis of large industrial-size models.

 

The understanding of an aeroelastic phenomena would not be complete if mistuning is not considered in the analysis. A mistuned bladed-disk means that all its sectors do not share the same mass and stiffness properties, which in reality this is the case. Mistuning can be addressed as probabilistic, taking into account the manufacturing tolerances and wear of the bladed disk, or it can be assessed as deterministic, also known as intentional mistuning.

 

The latter is achieved to increase the flutter stability by breaking the circumferential traveling waves modes due to energy confinement, and also to have a certain understanding of the forced response amplitude, which helps in designing for worst and best case scenarios.

 

The ROMs that have been incorporated in the AROMA tool are known as the component mode synthesis (CMS) and subset nominal mode (SNM) approaches. The CMS is split into two branches, these are the fixed- and freeinterface methods known as Craig-Bampton (CB) and Craig-Chang (CC), respectively. An intensive study with numerical and experimental validation has been performed for these three reduction methods. The outcome of the study is that each of these methods have their own drawbacks and benefits depending on the aeromechanical analysis problem. The SNM showed that it produces fast computations, with high level of accuracy when the mistuning level is low. On the other hand, a novel and unique approach, Craig-Chang multisubstructuring (CCMS), demonstrated fast computations and high accuracy when the mistuning level is high.

Place, publisher, year, edition, pages
Stockholm: KTH Royal Institute of Technology, 2018. p. 68
Series
TRITA-ITM-AVL ; 2018:7
Keyword
flutter, forced response, high cycle fatigue, reduced order models, ROM, craig-bampton, mistuning, tuned, mistuned, cyclic, noncyclic, craig-chang, free-interface. fixed-interface, subset nominal mode, SNM, CBMS, CCMS, CCC, CBC, FEM, CMS, modal, eigen, modeshapes, aeroelasticity, aeromechanical, tool, turbomachinery, turbine, compressor, AROMA
National Category
Aerospace Engineering
Research subject
Energy Technology
Identifiers
urn:nbn:se:kth:diva-227658 (URN)978-91-7729-750-5 (ISBN)
Public defence
2018-06-07, Kollegiesalen, Brinellvägen 8, Stockholm, 10:00 (English)
Opponent
Supervisors
Note

QC 20180514

Available from: 2018-05-14 Created: 2018-05-09 Last updated: 2018-05-15Bibliographically approved

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