scholarly journals The Data Driven Surrogate Model Based Dynamic Design of Aero-Engine Fan Systems

2020 ◽  
Author(s):  
Yun-Peng Zhu ◽  
Jie Yuan ◽  
Z. Q. Lang ◽  
C. W. Schwingshackl ◽  
Loic Salles ◽  
...  
Keyword(s):  
Surrogate Model ◽  
System Analysis ◽  
Data Driven ◽  
Design Parameters ◽  
Contact Friction ◽  
Test Case ◽  
Arx Model ◽  
Analysis And Design ◽  
Aero Engine ◽  
Aero Engines

Abstract High cycle fatigue failures of fan blade systems due to vibrational loads are of great concern in the design of aero engines, where energy dissipation by the relative frictional motion in the dovetail joints provides the main damping to mitigate the vibrations. The performance of such a frictional damping can be enhanced by suitable coatings. However, the analysis and design of coated joint roots of gas turbine fan blades are computationally expensive due to strong contact friction nonlinearities and also complex physics involved in the dovetail. In this study, a data driven surrogate model, known as the Nonlinear in Parameter AutoRegressive with eXegenous input (NP-ARX) model, is introduced to circumvent the difficulties in the analysis and design of fan systems. The NP-ARX model is a linear input-output model, where the model coefficients are nonlinear functions of the design parameters of interest, such that the Frequency Response Function (FRF) can be directly obtained and used in the system analysis and design. A simplified fan bladed disc system is considered as the test case. The results show that by using the data driven surrogate model, an efficient and accurate design of aero-engine fan systems can be achieved. The approach is expected to be extended to solve the analysis and design problems of many other complex systems.

scholarly journals The Data Driven Surrogate Model Based Dynamic Design of Aero-Engine Fan Systems

2021 ◽  
Author(s):  
Yunpeng Zhu ◽  
Jie Yuan ◽  
Zi-Qiang Lang ◽  
Christoph W. Schwingshackl ◽  
Loic Salles ◽  
...  
Keyword(s):  
Surrogate Model ◽  
System Analysis ◽  
Data Driven ◽  
Design Parameters ◽  
Contact Friction ◽  
Test Case ◽  
Arx Model ◽  
Analysis And Design ◽  
Aero Engine ◽  
Aero Engines

Abstract High cycle fatigue failures of fan blade systems due to vibrational loads are of great concern in the design of aero engines, where energy dissipation by the relative frictional motion in the dovetail joints provides the main damping to mitigate the vibrations. The performance of such a frictional damping can be enhanced by suitable coatings. However, the analysis and design of coated joint roots of gas turbine fan blades are computationally expensive due to strong contact friction nonlinearities and also complex physics involved in the dovetail. In this study, a data driven surrogate model, known as the Nonlinear in Parameter AutoRegressive with eXegenous input (NP-ARX) model, is introduced to circumvent the difficulties in the analysis and design of fan systems. The NP-ARX model is a linear input-output model, where the model coefficients are nonlinear functions of the design parameters of interest, such that the Frequency Response Function (FRF) can be directly obtained and used in the system analysis and design. A simplified fan bladed disc system is considered as the test case. The results show that by using the data driven surrogate model, an efficient and accurate design of aero-engine fan systems can be achieved. The approach is expected to be extended to solve the analysis and design problems of many other complex systems.

Low Order Modeling for Fan and Outlet Guide Vanes in Aero-Engines

2019 ◽  
Vol 141 (3) ◽  
Author(s):  
Jiahuan Cui ◽  
Rob Watson ◽  
Yunfei Ma ◽  
Paul Tucker
Keyword(s):  
Detailed Analysis ◽  
Immersed Boundary Method ◽  
Low Cost ◽  
Immersed Boundary ◽  
Test Case ◽  
Guide Vanes ◽  
Compression System ◽  
Aero Engine ◽  
Aero Engines ◽  
Low Order

Intakes of reduced length have been proposed with the aim of producing aero-engines with higher efficiency and reduced weight. As the intake length decreases, it is expected that stronger effects of the fan on the flow over the intake lip will be seen. If the effects of the fan cannot be ignored, a low-cost but still accurate fan model is of great importance for designing a short-intake. In this paper, a low order rotor/stator model, the immersed boundary method with smeared geometry (IBMSG), has been further developed and validated on a rig test case. The improved IBMSG is more robust than the original. The rig test case used for validation features a low-pressure compression system with a nonaxisymmetric inflow, which is representative of the inlet condition of an aero-engine at its cruise condition. Both the fan and the outlet guide vanes (OGVs) are modeled using IBMSG. A detailed analysis is carried out on the flow both upstream and downstream of the fan. After validating the IBMSG method against the rig test case, a short-intake case, coupled with a fan designed for the next generation of aero-engines, is further investigated. It is found that compared with the intake-alone case, the inflow distortion at the fan face is significantly reduced by the presence of fan. Due to this increased interaction between the fan and the flow over the intake lip, accounting for the effects of the downstream fan is shown to be essential when designing a short intake.

Computer Based Optimisation and Automation of Analysis and Design Processes in Aero Engine Development

2002 ◽  
Author(s):  
Alexander Karl ◽  
Roland Hansen ◽  
Michael Pfitzner
Keyword(s):  
Loose Coupling ◽  
Analysis And Design ◽  
Repetitive Tasks ◽  
Engine Design ◽  
Aero Engine ◽  
Computer Based ◽  
Aero Engines ◽  
Engine Components ◽  
Engine Development

Many variants of designs of different engine components have to be analysed in detail during the design and subsequent optimisation of modern aero engines. This often involves repetitive tasks and even today this process still contains a considerable amount of manual work for the majority of the tasks in the design process. Experts from different technical disciplines are involved and several different analysis tools are used. An automation of this process not only saves a lot of time during the design phase; it also increases the quality of the design since many more design variants can be screened. In the present paper the integration of different analysis codes and optimisation tools into an automated process using off-the-shelf software is described. A mix of commercial and in-house codes is integrated in a loose coupling way. Several applications from different areas of aero engine design are described. It is shown that in all cases the computer based optimisation and the process automation yields results of equal or better technical quality compared to the original hand optimised ones or improves the understanding of the design space. In addition, the necessary wall-clock time to reach the results was in all cases a fraction of that of the manual process.

scholarly journals The Data Driven Surrogate Model Based Dynamic Design of Aero-Engine Fan Systems

2021 ◽  
Author(s):  
Yun-Peng Zhu ◽  
Jie Yuan ◽  
Z Q Lang ◽  
C W Schwingshackl ◽  
Loic Salles ◽  
...  
Keyword(s):  
Surrogate Model ◽  
Data Driven ◽  
Dynamic Design ◽  
Model Based ◽  
Aero Engine

scholarly journals Low Order Modelling for Fan and Outlet Guide Vanes in Aero-Engines

2018 ◽  
Author(s):  
Jiahuan Cui ◽  
Rob Watson ◽  
Paul Tucker ◽  
Mark Wilson
Keyword(s):  
Detailed Analysis ◽  
Immersed Boundary Method ◽  
Low Cost ◽  
Immersed Boundary ◽  
Test Case ◽  
Guide Vanes ◽  
Compression System ◽  
Aero Engine ◽  
Aero Engines ◽  
Low Order

Intakes of reduced length have been proposed with the aim of producing aero-engines with higher efficiency and reduced weight. As the intake length decreases, it is expected that stronger effects of the fan on the flow over the intake lip will be seen. If the effects of the fan cannot be ignored, a low-cost but still accurate fan model is of great importance for designing a short-intake. In this paper, a low order rotor/stator model — the immersed boundary method with smeared geometry (IBMSG), has been further developed and validated on a rig test case. The improved IBMSG is more robust than the original. The rig test case used for validation features a low-pressure compression system with a non-axisymmetric inflow, which is representative of the inlet condition of an aero-engine at its cruise condition. Both the fan and the Outlet Guide Vanes (OGV) are modelled using IBMSG. Detailed analysis is carried out on the flow both upstream and downstream of the fan. After validating the IBMSG method against the rig test case, a short-intake case, coupled with a fan designed for the next generation of aero-engines, is further investigated. It is found that, compared with the intake-alone case, the inflow distortion at the fan face is significantly reduced by the presence of fan. Due to this increased interaction between the fan and the flow over the intake lip, accounting for the effects of the downstream fan is shown to be essential when designing a short intake.

Design Optimization of Heat Exchangers for Aero Engines With the Use of a Surrogate Model Incorporating Performance Characteristics and Geometrical Constraints

2018 ◽  
Author(s):  
Christina Salpingidou ◽  
Dimitrios Misirlis ◽  
Zinon Vlahostergios ◽  
Michael Flouros ◽  
Fabian Donus ◽  
...  
Keyword(s):  
Fuel Consumption ◽  
Surrogate Model ◽  
Design Space ◽  
Specific Fuel Consumption ◽  
Performance Characteristics ◽  
Tubular Heat Exchanger ◽  
Geometrical Features ◽  
Aero Engine ◽  
Geometrical Constraints ◽  
Aero Engines

The present work is focused on the optimization of the performance characteristics of a recuperator specifically designed for aero engine applications, targeting the reduction of specific fuel consumption and taking into consideration aero engine geometrical constraints and limitations. The recuperator design was based on the elliptically profiled tubular heat exchanger which was developed and invented by MTU Aero Engines AG. For the specific fuel consumption investigations the Intercooled Recuperated Aero engine cycle, combining both intercooling and recuperation, was considered. The optimization was performed with the development of a recuperator surrogate model, capable to incorporate major recuperator geometrical features. A large number of recuperator design scenarios was assessed, in which additional design criteria and constraints were applied. Thus, a significantly large recuperator design space was covered resulting to the identification of feasible recuperator designs providing beneficial effect on the Intercooled Recuperated Aero engine leading to reduced specific fuel consumption and weight.

A Simplified Design Model for Modular Steel Buildings Subject to Vapor Cloud Explosions (VCEs)

2020 ◽  
Vol 14 ◽  
Author(s):  
Osama Bedair
Keyword(s):  
Dynamic Response ◽  
Minimum Cost ◽  
Design Parameters ◽  
Front Wall ◽  
Steel Buildings ◽  
Element Analysis ◽  
Analysis And Design ◽  
Vapor Cloud ◽  
Building Components ◽  
Analytical Expressions

Background: Modular steel buildings (MSB) are extensively used in petrochemical plants and refineries. Limited guidelines are available in the industry for analysis and design of (MSB) subject to accidental vapor cloud explosions (VCEs). Objectives: The paper presents simplified engineering model for modular steel buildings (MSB) subject to accidental vapor cloud explosions (VCEs) that are extensively used in petrochemical plants and refineries. Method: A Single degree of freedom (SDOF) dynamic model is utilized to simulate the dynamic response of primary building components. Analytical expressions are then provided to compute the dynamic load factors (DLF) for critical building elements. Recommended foundation systems are also proposed to install the modular building with minimum cost. Results: Numerical results are presented to illustrate the dynamic response of (MSB) subject to blast loading. It is shown that (DLF)=1.6 is attained at (td/t)=0.4 for front wall (W1) with (td/T)=1.25. For side walls (DLF)=1.41 and is attained at (td/t)=0.6. Conclusions: The paper presented simplified tools for analysis and design of (MSB) subject accidental vapor cloud blast explosions (VCEs). The analytical expressions can be utilized by practitioners to compute the (MSB) response and identify the design parameters. They are simple to use compared to Finite Element Analysis.

scholarly journals Versatility of constrained CRB for system analysis and design

2014 ◽  
Vol 50 (3) ◽  
pp. 1841-1863 ◽  
Author(s):  
Tarek Menni ◽  
Jerome Galy ◽  
Eric Chaumette ◽  
Pascal Larzabal
Keyword(s):  
System Analysis ◽  
System Analysis And Design ◽  
Analysis And Design
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