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Aerospace
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Progress in Jet Engine Technology II
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Progress in Jet Engine Technology II

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (31 January 2022) | Viewed by 24468

Special Issue Editor

Prof. Dr. Ernesto Benini

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Padova, Via Venezia 1, 35131 Padova, Italy
Interests: CFD of flows in industrial and energy systems: optimal design methods; performance analysis in design and off-design conditions; full-annulus uRANS methods; aerothermodynamics of propulsion machines; CFD of supersonic and hypersonic flows
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear colleagues,

In the past decade, the need for more efficient, low-noise, and environmentally friendly propulsors has brought innovative engine concepts and configurations to the attention of researchers within both academia and industry. Noticeable examples include but not limited to ultra-high by-pass ratio turbofans in podded configurations, distributed propulsion, boundary layer ingestion engines, and hybrid turbo/electric engines. Although such configurations are characterized by non-negligible technology readiness levels, they still require huge research efforts, both theoretical and experimental, to be validated.

This Special Issue aims to provide an overview of recent advances in jet engine technology for the civil sector, with special emphasis on new design configurations and performance assessment. Authors are invited to submit full research articles and review manuscripts addressing (but not limited to) the following topics:

  • Concurrent design methodologies for high-efficiency, low-noise jet engines;
  • Numerical/experimental analyses of jet engines at system and component levels;
  • Integrated propulsor/airframe configurations;
  • Very large/ultra-high by-pass ratio engines;
  • Turbo/electric engines;
  • Jet engines under boundary layer ingestion;
  • Open rotors.

Prof. Dr. Ernesto Benini
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

  • jet engines
  • jet propulsion
  • jet engine architectures
  • turbofans
  • civil aviation

Related Special Issue

Published Papers (6 papers)

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Research

Jump to: Review

21 pages, 5420 KiB  
Article
A Novel Performance Adaptation and Diagnostic Method for Aero-Engines Based on the Aerothermodynamic Inverse Model
by Sangwei Lu, Wenxiang Zhou, Jinquan Huang, Feng Lu and Zhongguang Chen
Aerospace 2022, 9(1), 16; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace9010016 - 29 Dec 2021
Cited by 9 | Viewed by 1873
Abstract
Aero-engines are faced with severe challenges of availability and reliability in the increasing operation, and traditional gas path filtering diagnostic methods have limitations restricted by various factors such as strong nonlinearity of the system and lack of critical sensor information. A method based [...] Read more.
Aero-engines are faced with severe challenges of availability and reliability in the increasing operation, and traditional gas path filtering diagnostic methods have limitations restricted by various factors such as strong nonlinearity of the system and lack of critical sensor information. A method based on the aerothermodynamic inverse model (AIM) is proposed to improve the adaptation accuracy and fault diagnostic dynamic estimation response speed in this paper. Thermodynamic mechanisms are utilized to develop AIM, and scaling factors are designed to be calculated iteratively in the presence of measurement correction. In addition, the proposed method is implemented in combination with compensation of the nonlinear filter for real-time estimation of health parameters under the hypothesis of estimated dimensionality reduction. Simulations involved experimental datasets revealed that the maximum average simulated error decreased from 13.73% to 0.46% through adaptation. It was also shown that the dynamic estimated convergence time of the improved diagnostic method reached 2.183 s decrease averagely without divergence compared to the traditional diagnostic method. This paper demonstrates the proposed method has the capacity to generalize aero-engine adaptation approaches and to achieve unbiased estimation with fast convergence in performance diagnostic techniques. Full article
(This article belongs to the Special Issue Progress in Jet Engine Technology II)
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18 pages, 11008 KiB  
Article
FMI-Based Multi-Domain Simulation for an Aero-Engine Control System
by Juan Fang, Maochun Luo, Jiqiang Wang and Zhongzhi Hu
Aerospace 2021, 8(7), 180; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8070180 - 2 Jul 2021
Cited by 5 | Viewed by 4026
Abstract
The simulation of an aero-engine control system involves numerous disciplines due to its complex functions and architecture, which generally consist of mechanical, hydraulic and electrical, and electronic systems. For each discipline, the modeling and simulation are usually dependent on different commercial software and [...] Read more.
The simulation of an aero-engine control system involves numerous disciplines due to its complex functions and architecture, which generally consist of mechanical, hydraulic and electrical, and electronic systems. For each discipline, the modeling and simulation are usually dependent on different commercial software and tools, which makes the simulation, integration, and verification of system-level models very difficult. To meet this challenge, a multi-domain co-simulation method based on the Functional Mock-up Interface (FMI) standard is proposed to integrate models developed by different software or tools. The simulation and testing results demonstrate that multi-disciplinary model integration and cross-platform simulation based on the FMI standard can be realized for an aero-engine control system, which lays a foundation for high-fidelity control system design, simulation, integration, and testing. Full article
(This article belongs to the Special Issue Progress in Jet Engine Technology II)
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20 pages, 5138 KiB  
Article
Novel Aero-Engine Multi-Disciplinary Preliminary Design Optimization Framework Accounting for Dynamic System Operation and Aircraft Mission Performance
by Alexios Alexiou, Nikolaos Aretakis, Ioannis Kolias and Konstantinos Mathioudakis
Aerospace 2021, 8(2), 49; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8020049 - 12 Feb 2021
Cited by 6 | Viewed by 4819
Abstract
This paper presents a modular, flexible, extendable and fast-computational framework that implements a multidisciplinary, varying fidelity, multi-system approach for the conceptual and preliminary design of novel aero-engines. In its current status, the framework includes modules for multi-point steady-state engine design, aerodynamic design, engine [...] Read more.
This paper presents a modular, flexible, extendable and fast-computational framework that implements a multidisciplinary, varying fidelity, multi-system approach for the conceptual and preliminary design of novel aero-engines. In its current status, the framework includes modules for multi-point steady-state engine design, aerodynamic design, engine geometry and weight, aircraft mission analysis, Nitrogen Oxide (NOx) emissions, control system design and integrated controller-engine transient-performance analysis. All the modules have been developed in the same software environment, ensuring consistent and transparent modeling while facilitating code maintainability, extendibility and integration at modeling and simulation levels. Any simulation workflow can be defined by appropriately combining the relevant modules. Different types of analysis can be specified such as sensitivity, design of experiment and optimization. Any combination of engine parameters can be selected as design variables, and multi-disciplinary requirements and constraints at different operating points in the flight envelope can be specified. The framework implementation is exemplified through the optimization of an ultra-high bypass ratio geared turbofan engine with a variable area fan nozzle, for which specific aircraft requirements and technology limits apply. Although the optimum design resulted in double-digit fuel-burn benefits compared to current technology engines, it did not meet engine-response requirements, highlighting the need to include transient-performance assessments as early as possible in the preliminary engine design phase. Full article
(This article belongs to the Special Issue Progress in Jet Engine Technology II)
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19 pages, 3226 KiB  
Article
Axial Flow Compressor Stability Enhancement: Circumferential T-Shape Grooves Performance Investigation
by Marco Porro, Richard Jefferson-Loveday and Ernesto Benini
Aerospace 2021, 8(1), 12; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8010012 - 4 Jan 2021
Cited by 3 | Viewed by 3744
Abstract
This work focuses its attention on possibilities to enhance the stability of an axial compressor using a casing treatment technique. Circumferential grooves machined into the case are considered and their performances evaluated using three-dimensional steady state computational simulations. The effects of rectangular and [...] Read more.
This work focuses its attention on possibilities to enhance the stability of an axial compressor using a casing treatment technique. Circumferential grooves machined into the case are considered and their performances evaluated using three-dimensional steady state computational simulations. The effects of rectangular and new T-shape grooves on NASA Rotor 37 performances are investigated, resolving in detail the flow field near the blade tip in order to understand the stall inception delay mechanism produced by the casing treatment. First, a validation of the computational model was carried out analysing a smooth wall case without grooves. The comparisons of the total pressure ratio, total temperature ratio and adiabatic efficiency profiles with experimental data highlighted the accuracy and validity of the model. Then, the results for a rectangular groove chosen as the baseline case demonstrated that the groove interacts with the tip leakage flow, weakening the vortex breakdown and reducing the separation at the blade suction side. These effects delay stall inception, improving compressor stability. New T-shape grooves were designed keeping the volume as a constant parameter and their performances were evaluated in terms of stall margin improvement and efficiency variation. All the configurations showed a common efficiency loss near the peak condition and some of them revealed a stall margin improvement with respect to the baseline. Due to their reduced depth, these new configurations are interesting because they enable the use of a thinner light-weight compressor case as is desirable in aerospace applications. Full article
(This article belongs to the Special Issue Progress in Jet Engine Technology II)
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19 pages, 4702 KiB  
Article
Evolution of Emission Species in an Aero-Engine Turbine Stator
by André A. V. Perpignan, Stella Grazia Tomasello and Arvind Gangoli Rao
Aerospace 2021, 8(1), 11; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8010011 - 4 Jan 2021
Cited by 5 | Viewed by 3083
Abstract
Future energy and transport scenarios will still rely on gas turbines for energy conversion and propulsion. Gas turbines will play a major role in energy transition and therefore gas turbine performance should be improved, and their pollutant emissions decreased. Consequently, designers must have [...] Read more.
Future energy and transport scenarios will still rely on gas turbines for energy conversion and propulsion. Gas turbines will play a major role in energy transition and therefore gas turbine performance should be improved, and their pollutant emissions decreased. Consequently, designers must have accurate performance and emission prediction tools. Usually, pollutant emission prediction is limited to the combustion chamber as the composition at its outlet is considered to be “chemically frozen”. However, this assumption is not necessarily valid, especially with the increasing turbine inlet temperatures and operating pressures that benefit engine performance. In this work, Computational Fluid Dynamics (CFD) and Chemical Reactor Network (CRN) simulations were performed to analyse the progress of NOx and CO species through the high-pressure turbine stator. Simulations considering turbulence-chemistry interaction were performed and compared with the finite-rate chemistry approach. The results show that progression of some relevant reactions continues to take place within the turbine stator. For an estimated cruise condition, both NO and CO concentrations are predicted to increase along the stator, while for the take-off condition, NO increases and CO decreases within the stator vanes. Reaction rates and concentrations are correlated with the flow structure for the cruise condition, especially in the near-wall flow field and the blade wakes. However, at the higher operating pressure and temperature encountered during take-off, reactions seem to be dependent on the residence time rather than on the flow structures. The inclusion of turbulence-chemistry interaction significantly changes the results, while heat transfer on the blade walls is shown to have minor effects. Full article
(This article belongs to the Special Issue Progress in Jet Engine Technology II)
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Review

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22 pages, 1659 KiB  
Review
A Review of Computational Methods and Reduced Order Models for Flutter Prediction in Turbomachinery
by Marco Casoni and Ernesto Benini
Aerospace 2021, 8(9), 242; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8090242 - 2 Sep 2021
Cited by 7 | Viewed by 4882
Abstract
Aeroelastic phenomena in turbomachinery are one of the most challenging problems to model using computational fluid dynamics (CFD) due to their inherent nonlinear nature, the difficulties in simulating fluid–structure interactions and the considerable computational requirements. Nonetheless, accurate modelling of self-sustained flow-induced vibrations, known [...] Read more.
Aeroelastic phenomena in turbomachinery are one of the most challenging problems to model using computational fluid dynamics (CFD) due to their inherent nonlinear nature, the difficulties in simulating fluid–structure interactions and the considerable computational requirements. Nonetheless, accurate modelling of self-sustained flow-induced vibrations, known as flutter, has proved to be crucial in assessing stability boundaries and extending the operative life of turbomachinery. Flutter avoidance and control is becoming more relevant in compressors and fans due to a well-established trend towards lightweight and thinner designs that enhance aerodynamic efficiency. In this paper, an overview of computational techniques adopted over the years is first presented. The principal methods for flutter modelling are then reviewed; a classification is made to distinguish between classical methods, where the fluid flow does not interact with the structure, and coupled methods, where this interaction is modelled. The most used coupling algorithms along with their benefits and drawbacks are then described. Finally, an insight is presented on model order reduction techniques applied to structure and aerodynamic calculations in turbomachinery flutter simulations, with the aim of reducing computational cost and permitting treatment of complex phenomena in a reasonable time. Full article
(This article belongs to the Special Issue Progress in Jet Engine Technology II)
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