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Aerospace
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Aero-Engine Design
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Aero-Engine Design

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: closed (31 October 2023) | Viewed by 3191

Special Issue Editor

Prof. Dr. Shuiting Ding

E-Mail Website
Guest Editor
1. Aircraft & Engine Integrated System Safety Beijing Key Laboratory, School of Energy and Power Engineering, Beihang University, Beijing 100191, China
2. Department of Aviation Engineering, Civil Aviation University of China, Tianjin 300300, China
Interests: aero-engine system safety and airworthiness; thermal protection of aero-engine

Special Issue Information

Dear Colleagues,

This Special Issue on “Aero-Engine Design” will cover a broad range of contemporary issues and research conducted in the field of aero-engine design, both in civil and military aviation. This Special Issue offers an opportunity for academics, researchers, and industry practitioners working in the broader aero-engine field to publish their original research and review articles.

Particular emphasis will be placed on state-of-the-art review works and theoretical, experimental, computational research, as well as applied engineering work conducted on aero-piston engines, aero-turbine engines, and new technology engines in relation to the following topics:

Entire Aero-Engine and System Design

  • General performance design and dynamics analysis of aero-engines;
  • General structure and material design of aero-engines;
  • Air system design and optimization;
  • Drive, transmission, and control design and verification;
  • System safety design and airworthiness design;
  • Model-based aero-engine design and safety assessment;
  • Advanced design methods in multi-physical coupled analysis;
  • Collaborative and multidisciplinary design for aero-engines;
  • Intelligent and information-aided design in aero-engines;
  • Novel aero-engine design, i.e., electric and hybrid propulsion aero-engines, etc.;
  • Reliability engineering methodologies and practice in aero-engine design;
  • Human factor considerations in system design.

Aero-Engine Component and Subsystem Design

  • Design and additional design requirements for the life assessment of aero-engine subsystems and components;
  • Simulation and optimization of structural reliability and robustness design of safe/non-safety critical aero-engine parts;
  • Emissions and noise airworthiness design and verification;
  • Probabilistic design and the risk assessment of life-limited parts;
  • Dynamics design techniques of aero-engine installation systems;
  • Data-driven and model-based technology for the efficient design of aero-engines;
  • Integrated inspection system and bench test design for aero-engines.

This Special Issue on “Aero-Engine Design” offers the opportunity for academics and research and industry practitioners to contribute their work to this highly important aeronautical engineering and aviation practice field.

Prof. Dr. Shuiting Ding
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • system safety design
  • airworthiness design
  • design and verification
  • air system design
  • multi-physical
  • collaborative design
  • emission and noise
  • probabilistic design
  • probabilistic risk assessment
  • model-based design and safety assessment

Published Papers (3 papers)

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Research

22 pages, 10925 KiB  
Article
Accuracy Investigations of Dynamic Characteristic Predictions of Tip Leakage Flow Using Detached Eddy Simulation
by Shiyan Lin, Ruiyu Li, Limin Gao and Ning Ge
Aerospace 2024, 11(1), 29; https://doi.org/10.3390/aerospace11010029 - 28 Dec 2023
Cited by 1 | Viewed by 864
Abstract
The accurate prediction of tip leakage flow is the premise for flow mechanism analysis and compressor performance optimization. The detached eddy simulation (DES) method, which compromises cost and accuracy, has excellent potential for a high Reynolds flow, like a compressor.However, in the case [...] Read more.
The accurate prediction of tip leakage flow is the premise for flow mechanism analysis and compressor performance optimization. The detached eddy simulation (DES) method, which compromises cost and accuracy, has excellent potential for a high Reynolds flow, like a compressor.However, in the case of tip leakage flow, especially when there are multiple wall boundary layers and strong shear between the mainstream and leakage flow, the DES method exhibits accuracy deficiencies. This paper explores the resolution of the critical detailed structures using the DES method and its correlation with the accuracy of time-averaged aerodynamic parameter predictions. Based on this, we propose the necessary conditions for the DES method to accurately predict the leakage flow from the perspective of the detailed structure of the flow field. A simplified model is proposed to emphasize the characteristics of tip leakage flow with “multiple walls + narrow tip gap”, and the high-fidelity flow field of the WALE LES method is used as a benchmark. With the main fluctuation structures obtained by the SPOD method, it is concluded that the DES method is unable to resolve the Kelvin–Helmholtz instability at the initial position of the leakage, which leads to the generation of the secondary leakage vortex upstream of the leakage and the breakdown of the induced vortex, two critical flow structures, being incorrectly estimated. This can lead to misestimationsof the force direction on the tip leakage vortex and the main fluctuation on the flow field. As a result, the tip leakage vortex trajectory evolves toward the middle of the passage along the tangential direction and away from the upper wall downstream of the leakage compared with the LES results. Predictions of losses in the upstream and midstream regions are underestimated, whereas they are overestimated downstream of the leakage and outside the passage.Therefore, the accurate resolution of these two critical detailed structures is an essential prerequisite for the precise prediction of tip leakage flow using DES series methods. Full article
(This article belongs to the Special Issue Aero-Engine Design)
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27 pages, 11707 KiB  
Article
Critical Sample-Size Analysis for Uncertainty Aerodynamic Evaluation of Compressor Blades with Stagger-Angle Errors
by Haohao Wang, Limin Gao and Baohai Wu
Aerospace 2023, 10(12), 990; https://doi.org/10.3390/aerospace10120990 - 25 Nov 2023
Viewed by 945
Abstract
Many probability-based uncertainty quantification (UQ) schemes require a large amount of sampled data to build credible probability density function (PDF) models for uncertain parameters. Unfortunately, the amounts of data collected as to compressor blades of aero-engines are mostly limited due to the expensive [...] Read more.
Many probability-based uncertainty quantification (UQ) schemes require a large amount of sampled data to build credible probability density function (PDF) models for uncertain parameters. Unfortunately, the amounts of data collected as to compressor blades of aero-engines are mostly limited due to the expensive and time-consuming tests. In this paper, we develop a preconditioner-based data-driven polynomial chaos (PDDPC) method that can efficiently deal with uncertainty propagation of limited amounts of sampled data. The calculation accuracy of a PDDPC method is closely related to the sample size of collected data. Therefore, the influence of sample size on this PDDPC method is investigated using a nonlinear test function. Subsequently, we consider the real manufacturing errors in stagger angles for compressor blades. Under three different operating conditions, the PDDPC method is applied to investigate the effect of stagger-angle error on UQ results of multiple aerodynamic parameters of a two-dimensional compressor blade. The results show that as the sample-size of measured data increases, UQ results regarding aerodynamic performance obtained by the PDDPC method gradually converge. There exists a critical sample size that ensures accurate UQ analysis of compressor blades. The probability information contained in the machining error data is analyzed through Kullback–Leibler divergence, and the critical sample size is determined. The research results can serve as a valuable reference for the fast and cheap UQ analysis of compressor blades in practical engineering. Full article
(This article belongs to the Special Issue Aero-Engine Design)
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26 pages, 8724 KiB  
Article
Modified Method for Surface Probabilistic Risk Assessment of Aero Engine Compressor Disks Considering Shot Peening
by Guo Li, Yida Teng and Huimin Zhou
Aerospace 2023, 10(7), 621; https://doi.org/10.3390/aerospace10070621 - 8 Jul 2023
Cited by 1 | Viewed by 917
Abstract
Aero engine compressor disks are typically life-limited parts and it is necessary to secure them through the implementation of an engineering plan and a manufacturing plan. Specifically, the engineering plan recommends the quantification of the safety of life-limited parts on the basis of [...] Read more.
Aero engine compressor disks are typically life-limited parts and it is necessary to secure them through the implementation of an engineering plan and a manufacturing plan. Specifically, the engineering plan recommends the quantification of the safety of life-limited parts on the basis of probabilistic risk assessment (PRA). However, the direct correlation between plans is limited, and the effect of manufacturing parameters on the safety of life-limited parts remains to be investigated. Shot peening, as a typical method of surface manufacturing, can significantly improve the safety of life-limited parts. Therefore, a modified mathematical surface PRA method considering shot peening parameters is developed in this paper to further bridge the design and manufacturing processes. Additionally, a general database is established using the response surface method to overcome the simulation complexity. On the basis of this method and the general database, an innovative direct and efficient determination of key shot peening parameters through failure risk in the design stage is proposed. The results indicate that failure risk decreased by 3.26%, 11.31%, and 9.71%, respectively, with increasing number, diameter, and velocity of shots, with the effect of diameter being the greatest. In addition, the method improves the efficiency of determining the key parameters by 75.80%, thus satisfying the requirements of abundant and efficient iterations during the design stage. Full article
(This article belongs to the Special Issue Aero-Engine Design)
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