Details
| Original language | English |
|---|---|
| Pages (from-to) | 256-262 |
| Number of pages | 7 |
| Journal | Procedia CIRP |
| Volume | 22 |
| Issue number | 1 |
| Publication status | Published - 17 Apr 2014 |
| Event | 3rd International Conference in Through-life Engineering Services, 2014 - , United Kingdom (UK) Duration: 4 Nov 2013 → 5 Nov 2013 |
Abstract
The regeneration process of jet engines is a highly complex, expensive and time-consuming. Especially the regeneration of high pressure turbine blades and compressor blisks are at the border of what is technically feasible. These components are highly loaded and thus substantial wear occurs. The blades and blisks must be overhauled or replaced regularly. The existing repair methods for these parts are inflexible and cannot be applied in many cases, resulting in a large number of scrapped parts. Therefore a new turbine blade regeneration process is presented. The goal of the improved process is to reduce the scrap rate and cost. This process includes an early evaluation of the condition of the hot-gas path components before disassembly, new detection methods for defects on the turbine blades surfaces, and more flexible manufacturing processes. The process is supported by production process simulations and functional simulations to predict the optimal regeneration path depending on the blade condition and the business model of the customer. The paper also presents a new approach for compressor blisk regeneration. This process will be developed and validated in the next years. New challenges in structural mechanics, aerodynamics, and manufacturing must be addressed due to the complexity of blisks. As part of the ongoing research, three new blisks will be designed and subjected to the complete regeneration path, which is also supported by simulations. In order to validate the simulations, their results will be compared to experimental results of the regenerated components on a compressor test rig.
Keywords
- Compressor blisks, Jet-engine overhaul, Regeneration, Turbine blade repair
ASJC Scopus subject areas
- Engineering(all)
- Control and Systems Engineering
- Engineering(all)
- Industrial and Manufacturing Engineering
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In: Procedia CIRP, Vol. 22, No. 1, 17.04.2014, p. 256-262.
Research output: Contribution to journal › Conference article › Research › peer review
}
TY - JOUR
T1 - Recent Progress in Turbine Blade and Compressor Blisk Regeneration
AU - Aschenbruck, Jens
AU - Adamczuk, Rafael
AU - Seume, Joerg R.
N1 - Funding information: The authors kindly thank the German Research Foundation (DFG) for the financial support of the Collaborative Research Center (SFB) 871 “Regeneration of Complex Capital Goods”.
PY - 2014/4/17
Y1 - 2014/4/17
N2 - The regeneration process of jet engines is a highly complex, expensive and time-consuming. Especially the regeneration of high pressure turbine blades and compressor blisks are at the border of what is technically feasible. These components are highly loaded and thus substantial wear occurs. The blades and blisks must be overhauled or replaced regularly. The existing repair methods for these parts are inflexible and cannot be applied in many cases, resulting in a large number of scrapped parts. Therefore a new turbine blade regeneration process is presented. The goal of the improved process is to reduce the scrap rate and cost. This process includes an early evaluation of the condition of the hot-gas path components before disassembly, new detection methods for defects on the turbine blades surfaces, and more flexible manufacturing processes. The process is supported by production process simulations and functional simulations to predict the optimal regeneration path depending on the blade condition and the business model of the customer. The paper also presents a new approach for compressor blisk regeneration. This process will be developed and validated in the next years. New challenges in structural mechanics, aerodynamics, and manufacturing must be addressed due to the complexity of blisks. As part of the ongoing research, three new blisks will be designed and subjected to the complete regeneration path, which is also supported by simulations. In order to validate the simulations, their results will be compared to experimental results of the regenerated components on a compressor test rig.
AB - The regeneration process of jet engines is a highly complex, expensive and time-consuming. Especially the regeneration of high pressure turbine blades and compressor blisks are at the border of what is technically feasible. These components are highly loaded and thus substantial wear occurs. The blades and blisks must be overhauled or replaced regularly. The existing repair methods for these parts are inflexible and cannot be applied in many cases, resulting in a large number of scrapped parts. Therefore a new turbine blade regeneration process is presented. The goal of the improved process is to reduce the scrap rate and cost. This process includes an early evaluation of the condition of the hot-gas path components before disassembly, new detection methods for defects on the turbine blades surfaces, and more flexible manufacturing processes. The process is supported by production process simulations and functional simulations to predict the optimal regeneration path depending on the blade condition and the business model of the customer. The paper also presents a new approach for compressor blisk regeneration. This process will be developed and validated in the next years. New challenges in structural mechanics, aerodynamics, and manufacturing must be addressed due to the complexity of blisks. As part of the ongoing research, three new blisks will be designed and subjected to the complete regeneration path, which is also supported by simulations. In order to validate the simulations, their results will be compared to experimental results of the regenerated components on a compressor test rig.
KW - Compressor blisks
KW - Jet-engine overhaul
KW - Regeneration
KW - Turbine blade repair
UR - http://www.scopus.com/inward/record.url?scp=84936160178&partnerID=8YFLogxK
U2 - 10.1016/j.procir.2014.07.016
DO - 10.1016/j.procir.2014.07.016
M3 - Conference article
AN - SCOPUS:84936160178
VL - 22
SP - 256
EP - 262
JO - Procedia CIRP
JF - Procedia CIRP
SN - 2212-8271
IS - 1
T2 - 3rd International Conference in Through-life Engineering Services, 2014
Y2 - 4 November 2013 through 5 November 2013
ER -