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Chana Goldberg

Bio: Chana Goldberg is an academic researcher from Cranfield University. The author has contributed to research in topics: Propulsion & Boundary layer. The author has an hindex of 5, co-authored 6 publications receiving 48 citations.

Papers
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Journal ArticleDOI
TL;DR: This research presents a work flow to simulate a boundary layer ingesting propulsion system at design and off-design and is intended as a tool for design space exploration and the rapid analysis of concepts at the conceptualisation phase.

18 citations

Proceedings ArticleDOI
31 Jul 2016
TL;DR: In this paper, an analytical method for preliminary design studies which evaluates the installed performance of a boundary layer ingesting system has been presented, which is applied to a case study of the distributed propulsor array of a blended wing body aircraft.
Abstract: Boundary layer ingesting systems have been proposed as a concept with great potential for reducing the fuel consumption of conventional propulsion systems and the overall drag of an aircraft. These studies have indicated that if the aerodynamic and efficiency losses were minimised, the propulsion system demonstrated substantial power consumption benefits in comparison to equivalent propulsion systems operating in freestream flow. Previously assessed analytical methods for BLI simulation have been from an uninstalled perspective. This research will present the formulation of an rapid analytical method for preliminary design studies which evaluates the installed performance of a boundary layer ingesting system. The method uses boundary layer theory and one dimensional gas dynamics to assess the performance of an integrated system. The method was applied to a case study of the distributed propulsor array of a blended wing body aircraft. There was particular focus on assessment how local flow characteristics influence the performance of individual propulsors and the propulsion system as a whole. The application of the model show that the spanwise flow variation has a significant impact on the performance of the array as a whole. A clear optimum design point is identified which minimises the power consumption for an array with a fixed configuration and net propulsive force requirement. In addition, the sensitivity of the system to distortion related losses is determined and a point is identified where a conventional free-stream propulsor is the lower power option. Power saving coefficient for the configurations considered is estimated to lie in the region of 15%.

16 citations

Proceedings ArticleDOI
12 Jun 2017
TL;DR: In this article, a case study of NASA's N3-X aircraft, a blended wing body concept with a distributed propulsor array ingesting the airframe boundary layer, is presented.
Abstract: As research on boundary layer ingesting aircraft concepts progresses, it becomes important to develop methods that may be used to model such propulsion systems not only at design point, but also over the full flight envelope. This research presents a methodology and framework for simulating the performance of boundary layer ingesting propulsion systems at off-design conditions. The method is intended for use as a preliminary design tool that may be used to explore the design space and identify design challenges or potential optimum configurations. The method presented in this research enables the rapid analysis of novel BLI configurations at a preliminary design stage. The method was applied to a case study of NASA’s N3-X aircraft, a blended wing body concept with a distributed propulsor array ingesting the airframe boundary layer. The performance of two propulsor in the array was compare, one at the airframe centreline and one at the extreme edge of the array. Due to difference in flow conditions, the centreline propulsor was shown to be more efficient at off-design than the end propulsor. However, this difference in efficiency disappeared at sea level static where the boundary layer thickness is negligible and mass flow ratio is high. Difference in thrust produce by the two propulsors was instead due their different sizes. Performance of the propulsor array as a whole was also presented both independently and including a link to a pair of turbogenerators to provide power. At off design, it was found that there was a discrepancy between the maximum power available from the turbogenerators at off-design operating points and that demanded by the propulsor array operating at 100% fan rotational speed. This discrepancy means that the propulsor array’s performance is limited by the turbogenerators at off-design, particularly for low speed, low altitude operation.

10 citations

Journal ArticleDOI
TL;DR: An increase in environmental awareness in both the aviation industry and the wider global setting has led to large bodies of research dedicated to developing more sustainable technology with a lowe... as discussed by the authors.

9 citations

Proceedings ArticleDOI
12 Jul 2017
TL;DR: In this paper, the authors performed an economic viability assessment of NASA's N3-X aircraft, a blended wing body aircraft with a distributed boundary layer ingesting propulsion system, and the sensitivity of the aircraft's direct operating cost to changes in acquisition price and maintenance cost was predicted to establish maximum cost margins for the aircraft.
Abstract: Numerous novel aircraft concepts are under development that aim to achieve dramatic increases in efficiency and reductions in emissions in comparison to current aircraft. Research into these concepts typically focuses on performance aspects to establish whether the aircraft will be capable of meeting developmental goals. However, the final goal of such concepts is to progress to viable commercial products. Economic viability assessments are therefore an integral part of the development process to ensure a sustainable industry. The key question to address is whether a high efficiency aircraft concept can translate into an attractive product from an economic perspective. This research performed an economic viability assessment of NASA’s N3-X aircraft, a blended wing body aircraft with a distributed boundary layer ingesting propulsion system. The sensitivity of the aircraft’s direct operating cost to changes in acquisition price and maintenance cost was predicted to establish maximum cost margins for the aircraft. In a May 2017 fuel price scenario, the N3-X could be no more than 25% more expensive than the baseline aircraft to remain economically viable. Introducing a carbon tax or fuel price jump widens the margin for increased costs. Aircraft cost estimates for the aircraft predict an acquisition cost from 11–37% more expensive than the baseline. In combination with the direct operating cost sensitivity analysis, the N3-X is predicted to need to capture 30% of the aircraft market up to 2035.

8 citations


Cited by
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Journal ArticleDOI
TL;DR: In this article, the authors present a survey of electric aircraft propulsion, including all-electric, hybrid electric, and turboelectric architectures, and present an overview of electrical components and electric propulsion architectures.

317 citations

Journal ArticleDOI
13 Apr 2020
TL;DR: In this paper, the authors surveyed several scholarly articles to get an insight into the current landscape of research endeavors and the formulated derivations related to electric aircraft developments, and also included detailed assessments of the implications and other needs pertaining to future technology, regulation, certification, and infrastructure developments.
Abstract: Electrification of the propulsion system has opened the door to a new paradigm of propulsion system configurations and novel aircraft designs, which was never envisioned before. Despite lofty promises, the concept must overcome the design and sizing challenges to make it realizable. A suitable modeling framework is desired in order to explore the design space at the conceptual level. A greater investment in enabling technologies, and infrastructural developments, is expected to facilitate its successful application in the market. In this review paper, several scholarly articles were surveyed to get an insight into the current landscape of research endeavors and the formulated derivations related to electric aircraft developments. The barriers and the needed future technological development paths are discussed. The paper also includes detailed assessments of the implications and other needs pertaining to future technology, regulation, certification, and infrastructure developments, in order to make the next generation electric aircraft operation commercially worthy.

103 citations

Journal ArticleDOI
13 Aug 2020
TL;DR: A survey of the available studies on solid particles erosion effects on GTEs and surface protective coatings can be found in this paper, where an in-depth focus on the parameters associated with the SPE, such as particles properties and impingement conditions, is introduced.
Abstract: Gas turbines (GTEs) are often utilised in harsh environments where the GT components, including compressor vanes and rotor blades, are subject to erosion damage by sand and dust particles. For instance, in a desert environment, the rate of damage made by solid particles erosion (SPE) becomes severe, and therefore results in degradation to the GTE parts, lowering the cycle efficiency, reducing the device lifetime, and increasing the overall cost of the operation. As such, understanding the erosion mechanism caused by solid particles and the effects associated with it is crucial for selecting the appropriate countermeasures and maintaining the system performance. This review paper provides a survey of the available studies on SPE effects on GTEs and surface protective coatings. Firstly, the ductile and brittle SPE mechanism is presented, as well as the ductile-brittle transition region. Then, an in-depth focus on the parameters associated with the SPE, such as particles properties and impingement conditions, is introduced. Furthermore, the existing theoretical models are shown and discussed. Afterwards, erosion resistant coating materials for surface protection and their selection criteria are covered in the review. Finally, the gap in knowledge and future research direction in the field of SPE on GTEs are provided.

34 citations

Journal ArticleDOI
TL;DR: In this article, three driving aircraft concepts have been identified, namely propulsive fuselage concept (PFC), rear engines concept (REC), and distributed fans concept (DFC).
Abstract: The present paper focuses on the numerical modeling approaches adopted in boundary layer ingestion (BLI) studies. Three driving aircraft concepts have been identified, namely propulsive fuselage concept (PFC), rear engines concept (REC), and distributed fans concept (DFC). The affiliation to relevant research projects has been considered. Specifically, European projects DisPURSAL and CENTRELINE, NASA projects STARC-ABL, D8, and N3-X, as well as ONERA projects NOVA and DRAGON have been examined, together with other significant works. The methodologies adopted by the reviewed analyses have been investigated and summarized for each concept, in order to assess the main trends of BLI modeling strategies.

23 citations

Journal ArticleDOI
TL;DR: The aim of this research is the identification of a unified bookkeeping and evaluation scheme for the integrated performance analysis of a boundary layer ingesting (BLI) concept in the conceptual design phase.
Abstract: The aim of this research is the identification of a unified bookkeeping and evaluation scheme for the integrated performance analysis of a boundary layer ingesting (BLI) concept in the conceptual design phase. A thorough review and classification of existing performance bookkeeping schemes suits as a basis for the derivation of a bookkeeping scheme suitable for the initial sizing as well as detailed design analysis during the conceptual phase of a BLI concept. Figures of merit for the concept performance assessment are evaluated with regard to the requirements of aircraft multidisciplinary conceptual design. Based on the survey, the most practical integral momentum conservation approach is deduced and its application to integrated conceptual sizing and a subsequent design analysis is evaluated. The proposed scheme is universally applicable to coupled airframe–propulsion aircraft concepts, compatible with standard aircraft and propulsion system sizing tools and, under certain assumptions, deployable for low- and high-fidelity evaluation methods. Finally, several figures of merit are selected to cover a range of design aspects in the BLI evaluation.

21 citations