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Evolution of the methodology of weight estimation and engine feasibility in preliminary design
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
2019 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [sv]

Som en del av Aerospace Engineering masterprogrammet som jag följde på KTH från augusti 2017 till juni 2018, fick jag slutligen en självständig studie i form av ett avhandlingsprojekt. Jag fick möjlighet att slutföra mitt 6-månaders examensprojekt på Safran Aircraft Engines i Villaroche, Frankrike. 

Safran är en internationell högteknologisk grupp som arbetar inom flygplanets framdrivning och utrustning, rymd- och försvarsmarknader.

Som en del av de mekaniska aktiviteter som genomförs vid Produkt Innovation Lab är genomförandet av en för-dimensioneringsmetod för motorkonstruktioner nödvändiga för att få en uppfattning om för-dimensionering tidigare inom projektet och inom en rimlig tidsrymd.

Huvudsyftet med detta projekt är att utveckla metoden som gör det möjligt att göra viktstatus och genomförbarhetsbedömningar av motorramkomponenterna i en preliminär konstruktionsfas och inom en begränsad tid. Detta papper fokuserar mer exakt på en äldre kommersiell motor mellanram. Denna metod måste leda till att en konsekvent modell skapas som ligger närmare kraven och specifikationerna.

Slutsatsen av rapporten är att den implementerade pre-designmetoden möjliggör resultat med avseende på viktstatus och genomförbarhet som överensstämmer med specifikationerna. Vidare är beräkningstiden i linje med förväntningarna. Detta projekt har äntligen tillåtit att skapa en modell som kommer att tas som referens för att utveckla och designa nya motorer som har en konfiguration som liknar äldre kommersiella motorer.

Abstract [en]

This paper aims to develop and to validate a methodology to realize pre-sizing studies on aircraft engine structural frames for Safran Aircraft Engines Product Innovation Lab activities. The members of this team are in charge of creating new propulsion systems architectures in accordance with product strategy guidelines or airframer needs. Aerospace industry being highly competitive, the Product Innovation Lab must be able to respond quickly and precisely to any demand emerging from aircraft manufacturers or strategy team.The main purpose of this project is to improve the methodology permitting to make weight status and feasibility estimations of the engine frame components in a preliminary design phase and in a limited amount of time. This methodology must lead to the creation of a consistent model that is closer to the requirements and specifications imposed. This paper more precisely focus on legacy commercial engine structural frame. Reflection has been conducted on the creation of a simplified parametrized model of an existing commercial engine structural frame and on the way to mesh it in order to find a good compromise between results fidelity and computation time. Regarding the weight status and feasibility results obtained with a first model, an optimization of the model configuration has finally been conducted in order to get results that fit with the specifications.Conclusion of the report is that the pre-sizing methodology can be adapted to existing commercial engine structural frame configuration. Results obtained in terms of weight status and feasibility are in accordance with the specifications and the computation time is in agreement with the expectations. It has permitted to create a model that will be taken as a reference to develop and design new engines having a configuration similar to the legacy commercial engine considered in this study. For that purpose, iterations and optimizations will be conducted on the simplified model implemented during the project in order to determine a new configuration of the pre-sized intermediate frame model which sticks with reality i.e. that respects the provided feasibility specifications.Note that due to the public nature of this report, sensitive information and data used and obtained during the project have been removed from the present paper. Nevertheless, the methodology followed has been presented and discussed in detail. Relative deviations between the results obtained and reference values have also been exposed in order to give the reader an idea of implemented model consistency.

Place, publisher, year, edition, pages
2019. , p. 72
Series
TRITA-SCI-GRU ; 2019:040
National Category
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-261216OAI: oai:DiVA.org:kth-261216DiVA, id: diva2:1357321
External cooperation
SAFRAN
Examiners
Available from: 2019-10-03 Created: 2019-10-03 Last updated: 2019-10-03Bibliographically approved

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