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On the performance of common-core turboprops
Mälardalen University, School of Business, Society and Engineering, Future Energy Center. Institute of Propulsion Technology, German Aerospace Center (DLR), Cologne, Germany.ORCID iD: 0000-0001-9922-3690
Mälardalen University, School of Business, Society and Engineering, Future Energy Center.
Institute of Propulsion Technology, German Aerospace Center (DLR), Cologne, Germany.
Institute of Propulsion Technology, German Aerospace Center (DLR), Cologne, Germany.
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2025 (English)In: Proceedings of the ASME Turbo Expo, ASME International , 2025Conference paper, Published paper (Refereed)
Abstract [en]

Turboprops offer a promising pathway for sustainable aviation, as they can achieve high levels of propulsive efficiency and reduced installed drag compared to high bypass ratio turbofans. Turboprop engine cores, though, are rarely designed from scratch; instead, they remain geometrically similar and can be used across several engine variants, which is known as the concept of growth engines or core commonality. This paper investigates the impact of core commonality on the installed performance of the next generation small-core turboprops. Firstly, a turboprop cycle design optimization is carried out based on a multi-point synthesis approach for 2035 entry into service assumptions. The propeller, nozzle and engine core are individually designed and analyzed. Preliminary design studies of the core compressor are performed using a 2D streamline curvature algorithm, providing insights into the aerodynamic trade-offs of highly loaded all-Axial multistage compressors. The second part of this study examines the performance of growth engine variants by applying the common-core approach to the designed 2035 baseline turboprop engine. In this context, "growth"refers to increasing equivalent shaft power to meet the thrust demands of a derivative aircraft designed for higher passenger capacity and/or extended range. A common-core design methodology is developed and proposed, enabling power growth through zero-staging of the core compressor and power off-Take from the free-power turbine to drive electric motors, which in turn power additional e-propellers in electrified turboprop variants. Three optimal growth engine designs are identified, achieving up to 34.8% power growth relative to the baseline turboprop while maintaining design constraints, including high-pressure spool overspeed limits, a fixed propeller design, and considerations for cooled or uncooled free-power turbines. Overall, this study systematically analyzes the common-core concept, reflecting the approach followed by engine manufacturers over the years.

Place, publisher, year, edition, pages
ASME International , 2025.
Keywords [en]
Aerodynamics, Aircraft Engines, Bypass Ratio, Compressors, Fighter Aircraft, Gas Turbines, Machine Design, Propellers, Turboprop Engines, Design Optimization, Design Studies, Engine Variants, Free Power Turbines, High Bypass Ratio, Multi-points, Performance, Power, Preliminary Design, Propulsive Efficiencies, Economic And Social Effects
National Category
Vehicle and Aerospace Engineering
Identifiers
URN: urn:nbn:se:mdh:diva-73219DOI: 10.1115/GT2025-153200ISI: 001562098200033Scopus ID: 2-s2.0-105014501346ISBN: 9780791888773 (print)ISBN: 9780791888766 (print)ISBN: 9780791887929 (print)OAI: oai:DiVA.org:mdh-73219DiVA, id: diva2:1996622
Conference
70th ASME Turbo Expo 2025: Turbomachinery Technical Conference and Exposition, GT 2025, Memphis, USA, 16-20 June, 2025
Available from: 2025-09-10 Created: 2025-09-10 Last updated: 2025-11-24Bibliographically approved
In thesis
1. On the Design and Analysis of Electrified Aero-engine Families
Open this publication in new window or tab >>On the Design and Analysis of Electrified Aero-engine Families
2026 (English)Doctoral thesis, comprehensive summary (Other academic)
Abstract [en]

Rather than designing a new engine from scratch for every aircraft application, manufacturers often develop families of engines that share a common core; typically comprising the high-pressure compressor, combustor, and high-pressure turbine. This strategy reduces cost, shortens development time, and mitigates technical risk, making it an attractive option in today’s evolving aerospace landscape. Common-core variants are always associated with performance penalties compared to individually optimized clean-sheet engines because the initial core design is compromised to allow for adjustment of its component map entry points, but there is a high potential for better economics of the entire engine program.

To address these challenges, this thesis introduces a simulation methodology for assessing both conventional and electrified aero-engine architectures, including turbofans, turboprops, and distributed electric propulsion systems. Based on a multi-point synthesis approach, the framework supports performance evaluation across multiple fidelity levels: from 0D thermodynamic cycle modeling, to 1D mean-line design, and up to 2D throughflow component analysis.A particular focus is placed on electrically driven propulsors, evaluated both as standalone units and within turbo-electric configurations. These include variants featuring variable geometry, such as variable pitch fans and variable area nozzles, when necessary.

Building on the standalone engine modeling foundation, a novel methodology is introduced for simulating common-core engine variants within an aero-engine family. This extends the multi-point synthesis approach by treating the design point of each variant as an additional off-design condition of the baseline (first-to-enter-the-market) engine. To demonstrate its application, an electrified turboprop engine family is designed and analyzed across a range of power growth scenarios. Clean-sheet engine designs are developed in parallel to serve as benchmarks, enabling quantification of the performance penalties associated with enforcing commonality across various levels of power growth.

Place, publisher, year, edition, pages
Västerås: Mälardalens universitet, 2026
Series
Mälardalen University Press Dissertations, ISSN 1651-4238 ; 455
National Category
Environmental Engineering Vehicle and Aerospace Engineering
Research subject
Energy- and Environmental Engineering
Identifiers
urn:nbn:se:mdh:diva-74488 (URN)978-91-7485-738-2 (ISBN)
Public defence
2026-01-23, Delta, Mälardalen University, Västerås, 09:00 (English)
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Supervisors
Available from: 2025-11-25 Created: 2025-11-24 Last updated: 2026-01-02Bibliographically approved

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Bermperis, DimitiosKyprianidis, Konstantinos

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