Special Issue "Boundary Layer Ingesting Turbo-Electric Distributed Propulsion Systems—Innovations and Challenges"

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

Deadline for manuscript submissions: closed (31 January 2018)

Special Issue Editors

Guest Editor
Dr. Panagiotis Laskaridis

Centre for Propulsion Engineering, Cranfield University, Cranfield MK43 0AL, UK
Website | E-Mail
Interests: gas turbines and propulsion; power systems and turbines
Guest Editor
Dr. Devaiah Nalianda

Centre for Propulsion Engineering, Cranfield University, Cranfield MK43 0AL, UK
Website | E-Mail
Interests: energy and the environment; environmental impacts; gas turbines and propulsion; power systems and turbines

Special Issue Information

Dear Colleagues,

To achieve the next level of performance improvements, the aerospace industry is shifting its focus towards highly integrated propulsion systems. This will necessarily entail a significant change in aerodynamic design and system integration aspects of the technology. With an impetus on “clean green technology”, great strides are today being made in the incorporation and adaptation of more distributed hybrid electric propulsion concepts with additional benefits, through integrated boundary layer ingesting systems.

Given the highly integrated nature of these systems, a significant number of new design innovations and integration concepts have evolved in the recent past. Through the introduction of this Special Issue, we are hoping to bring to the fore some of the latest propulsion concepts and system integration aspects, while touching upon the key innovations required and the challenges that we may face in realising the technology and its potential. The breadth of coverage will range from aerodynamics of integrated propulsion systems to the design of turbo-electric/hybrid system architecture.

Authors are encouraged to submit manuscripts relating to analytical and/or experimental work in the field of distributed hybrid/turbo-electric and boundary layer ingesting propulsion systems research. The topics of interest may include propulsion system integration aerodynamics; the effects of distortion on fan performance; inlet duct design and boundary layer flow control; the design and integration of distributed propulsor/propeller to improve wing performance through the introduction of novel concepts (e.g., diverted slip stream and flap blowing concepts); and the influence of boundary layer ingesting propulsors on aircraft performance and design. This Special Issue also invites papers on topics related to system design and engineering. These may include designs and assessments of hybrid architectures (parallel/serial), electric motor and energy storage solutions, hybrid power generation, distribution and management on-board aircraft.

Dr. Panagiotis Laskaridis
Dr. Devaiah Nalianda
Guest Editors

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 papers will be 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 550 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

  • distributed propulsion
  • hybrid/turbo-electric propulsion
  • boundary layer ingesting systems
  • propulsion system integration
  • electric system design
  • electric system architecture

Published Papers (1 paper)

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Research

Open AccessArticle
Hybrid Electric Aircraft Propulsion Case Study for Skydiving Mission
Received: 30 June 2017 / Revised: 14 August 2017 / Accepted: 15 August 2017 / Published: 18 August 2017
Cited by 4 | PDF Full-text (6139 KB) | HTML Full-text | XML Full-text
Abstract
This paper describes a case study for applying innovative architectures related to electrified propulsion for aircraft. Electric and hybrid electric propulsion for aircraft has gained widespread and significant attention over the past decade. The driver for industry interest has principally been the need [...] Read more.
This paper describes a case study for applying innovative architectures related to electrified propulsion for aircraft. Electric and hybrid electric propulsion for aircraft has gained widespread and significant attention over the past decade. The driver for industry interest has principally been the need to reduce emissions of combustion engine exhaust products and noise, but increasingly studies revealed potential for overall improvement in energy efficiency and mission flexibility of new aircraft types. In this work, a conceptual new type for a skydiver lift mission aircraft is examined. The opportunities which electric hybridisation offers for this role is analysed in comparison with conventional legacy type propulsion systems. For a conventional commercial skydiving mission, an all-electric propulsion system is shown as viable, and a hybrid-electric system is shown to reduce aircraft fuel costs and CO2 emissions whilst maintaining conventional aero-engine operational benefits. The new paradigm for aircraft development which hybrid electric propulsion enables has highlighted significant issues with aircraft certification practices as they exist today. The advancement of aircraft design and production to harness the value of new propulsion systems may require adaption and development of certification standards to cater for these new technologies. Full article
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