Details
| Original language | English |
|---|---|
| Pages (from-to) | 1305-1316 |
| Number of pages | 12 |
| Journal | Aircraft Engineering and Aerospace Technology |
| Volume | 90 |
| Issue number | 9 |
| Early online date | 12 Oct 2018 |
| Publication status | Published - 22 Nov 2018 |
Abstract
The purpose of this study a fast procedure for the structural analysis of gas turbine blades in aircraft engines. In this connection, investigations on the behavior of gas turbine blades concentrate on the analysis and evaluation of starting dynamics and fatigue strength. Besides, the influence of structural mistuning on the vibration characteristics of the single blade is analyzed and discussed.
Design/methodology/approach
A basic computation cycle is generated from a flight profile to describe the operating history of the gas turbine blade properly. Within an approximation approach for high-frequency vibrations, maximum vibration amplitudes are computed by superposition of stationary frequency responses by means of weighting functions. In addition, a two-way coupling approach determines the influence of structural mistuning on the vibration of a single blade. Fatigue strength of gas turbine blades is analyzed with a semi-analytical approach. The progressive damage analysis is based on MINER’s damage accumulation assuming a quasi-stable behavior of the structure.
Findings
The application to a gas turbine blade shows the computational capabilities of the approach presented. Structural characteristics are obtained by robust and stable computations using a detailed finite element model considering different load conditions. A high quality of results is realized while reducing the numerical costs significantly.
Research limitations/implications
The method used for analyzing the starting dynamics is based on the assumption of a quasi-static state. For structures with a sufficiently high stiffness, such as the gas turbine blades in the present work, this procedure is justified. The fatigue damage approach relies on the existence of a quasi-stable cyclic stress condition, which in general occurs for isotropic materials, as is the case for gas turbine blades.
Practical implications
Owing to the use of efficient analysis methods, a fast evaluation of the gas turbine blade within a stochastic analysis is feasible.
Originality/value
The fast numerical methods and the use of the full finite element model enable performing a structural analysis of any blade structure with a high quality of results.
Keywords
- Efficient approaches, Fatigue strength, Gas turbine blade, Starting dynamics, Stochastic analysis, Structural mistuning
ASJC Scopus subject areas
- Engineering(all)
- Aerospace Engineering
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In: Aircraft Engineering and Aerospace Technology, Vol. 90, No. 9, 22.11.2018, p. 1305-1316.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Efficient structural analysis of gas turbine blades
AU - Rogge, Timo
AU - Berger, Ricarda
AU - Pohle, Linus
AU - Rolfes, Raimund
AU - Wallaschek, Jörg
N1 - © Emerald Publishing Limited
PY - 2018/11/22
Y1 - 2018/11/22
N2 - PurposeThe purpose of this study a fast procedure for the structural analysis of gas turbine blades in aircraft engines. In this connection, investigations on the behavior of gas turbine blades concentrate on the analysis and evaluation of starting dynamics and fatigue strength. Besides, the influence of structural mistuning on the vibration characteristics of the single blade is analyzed and discussed.Design/methodology/approachA basic computation cycle is generated from a flight profile to describe the operating history of the gas turbine blade properly. Within an approximation approach for high-frequency vibrations, maximum vibration amplitudes are computed by superposition of stationary frequency responses by means of weighting functions. In addition, a two-way coupling approach determines the influence of structural mistuning on the vibration of a single blade. Fatigue strength of gas turbine blades is analyzed with a semi-analytical approach. The progressive damage analysis is based on MINER’s damage accumulation assuming a quasi-stable behavior of the structure.FindingsThe application to a gas turbine blade shows the computational capabilities of the approach presented. Structural characteristics are obtained by robust and stable computations using a detailed finite element model considering different load conditions. A high quality of results is realized while reducing the numerical costs significantly.Research limitations/implicationsThe method used for analyzing the starting dynamics is based on the assumption of a quasi-static state. For structures with a sufficiently high stiffness, such as the gas turbine blades in the present work, this procedure is justified. The fatigue damage approach relies on the existence of a quasi-stable cyclic stress condition, which in general occurs for isotropic materials, as is the case for gas turbine blades.Practical implicationsOwing to the use of efficient analysis methods, a fast evaluation of the gas turbine blade within a stochastic analysis is feasible.Originality/valueThe fast numerical methods and the use of the full finite element model enable performing a structural analysis of any blade structure with a high quality of results.
AB - PurposeThe purpose of this study a fast procedure for the structural analysis of gas turbine blades in aircraft engines. In this connection, investigations on the behavior of gas turbine blades concentrate on the analysis and evaluation of starting dynamics and fatigue strength. Besides, the influence of structural mistuning on the vibration characteristics of the single blade is analyzed and discussed.Design/methodology/approachA basic computation cycle is generated from a flight profile to describe the operating history of the gas turbine blade properly. Within an approximation approach for high-frequency vibrations, maximum vibration amplitudes are computed by superposition of stationary frequency responses by means of weighting functions. In addition, a two-way coupling approach determines the influence of structural mistuning on the vibration of a single blade. Fatigue strength of gas turbine blades is analyzed with a semi-analytical approach. The progressive damage analysis is based on MINER’s damage accumulation assuming a quasi-stable behavior of the structure.FindingsThe application to a gas turbine blade shows the computational capabilities of the approach presented. Structural characteristics are obtained by robust and stable computations using a detailed finite element model considering different load conditions. A high quality of results is realized while reducing the numerical costs significantly.Research limitations/implicationsThe method used for analyzing the starting dynamics is based on the assumption of a quasi-static state. For structures with a sufficiently high stiffness, such as the gas turbine blades in the present work, this procedure is justified. The fatigue damage approach relies on the existence of a quasi-stable cyclic stress condition, which in general occurs for isotropic materials, as is the case for gas turbine blades.Practical implicationsOwing to the use of efficient analysis methods, a fast evaluation of the gas turbine blade within a stochastic analysis is feasible.Originality/valueThe fast numerical methods and the use of the full finite element model enable performing a structural analysis of any blade structure with a high quality of results.
KW - Efficient approaches
KW - Fatigue strength
KW - Gas turbine blade
KW - Starting dynamics
KW - Stochastic analysis
KW - Structural mistuning
UR - http://www.scopus.com/inward/record.url?scp=85064352849&partnerID=8YFLogxK
U2 - 10.1108/AEAT-05-2016-0085
DO - 10.1108/AEAT-05-2016-0085
M3 - Article
AN - SCOPUS:85064352849
VL - 90
SP - 1305
EP - 1316
JO - Aircraft Engineering and Aerospace Technology
JF - Aircraft Engineering and Aerospace Technology
SN - 1748-8842
IS - 9
ER -