Optimality considerations for propulsive fuselage power savings

Seitz, Arne; Habermann, Anaïs Luisa; Sluis, Martijn van

doi:10.1177/0954410020916319

Cited by 12 publications

(23 citation statements)

References 24 publications

(30 reference statements)

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“…Since the fluid is modeled to be compressible, energy is added to the fluid based on the local work of the momentum source in axial direction. Verification and validation of the actuator disc model is discussed in brief in [50].…”

Section: Methodsmentioning

confidence: 99%

“…A detailed discussion of the PSC application to PFC aircraft performance evaluation is presented by [50]. An analytical formulation of the PSC coefficient for PFC aircraft in cruise is provided in Section 7.1.…”

Section: Performance Bookkeeping and Efficiency Metricsmentioning

confidence: 99%

“…Both setups featured an axisymmetric fuselage (fineness ratio L fus /2r fus = 11.1) with a shape representative of the CENTRELINE PFC design Rev03 [50]. The fuselage aftsection was equipped with an integrated shrouded fan model.…”

Section: Overall Configuration Wind Tunnel Testingmentioning

confidence: 99%

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Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion

et al. 2021

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Key results from the EU H2020 project CENTRELINE are presented. The research activities undertaken to demonstrate the proof of concept (technology readiness level—TRL 3) for the so-called propulsive fuselage concept (PFC) for fuselage wake-filling propulsion integration are discussed. The technology application case in the wide-body market segment is motivated. The developed performance bookkeeping scheme for fuselage boundary layer ingestion (BLI) propulsion integration is reviewed. The results of the 2D aerodynamic shape optimization for the bare PFC configuration are presented. Key findings from the high-fidelity aero-numerical simulation and aerodynamic validation testing, i.e., the overall aircraft wind tunnel and the BLI fan rig test campaigns, are discussed. The design results for the architectural concept, systems integration and electric machinery pre-design for the fuselage fan turbo-electric power train are summarized. The design and performance implications on the main power plants are analyzed. Conceptual design solutions for the mechanical and aero-structural integration of the BLI propulsive device are introduced. Key heuristics deduced for PFC conceptual aircraft design are presented. Assessments of fuel burn, NOx emissions, and noise are presented for the PFC aircraft and benchmarked against advanced conventional technology for an entry-into-service in 2035. The PFC design mission fuel benefit based on 2D optimized PFC aero-shaping is 4.7%.

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Section: Methodsmentioning

confidence: 99%

Section: Performance Bookkeeping and Efficiency Metricsmentioning

confidence: 99%

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Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion

et al. 2021

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“…Even a small increase in P shaft is significant for a BLI fan driven by a turboelectric power source, such as the investigated configuration. Due to efficiency losses in the electric system, an increased power demand of the FF leads to an even higher power generation demand from the main engines [8]. Hence, it is imperative to limit the increase in P shaft .…”

Section: Fuselage Upsweep Studymentioning

confidence: 99%

“…Prominent examples include the boundary layer ingesting aft-fuselage fan concept Fuse Fan by NASA [1], the Bauhaus Luftfahrt Propulsive Fuselage [2], the propulsive fuselage concepts (PFC) investigated in the European research projects DisPURSAL [3] and CENTRELINE [4], the NASA STARC-ABL [5], and the embedded BLI configuration SAX-40 [6], and the N3-X blended wing body (BWB) [7]. The expected fuel burn reduction potential of these concepts varies in the one digit range between 2 and 10% [3,[8][9][10] and even a predicted increase in fuel burn of 1.7% [11]. Toplevel aircraft requirements (TLAR) as well as the aircraft and power train configuration and geometry of the concepts differ significantly.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the effects of fuselage upsweep in a propulsive fuselage concept

2021

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In recent years, aircraft concepts employing wake-filling devices to reduce mission fuel burn have gained increasing attention. The study presented here aims at a detailed physical understanding of the effects of integrating a propulsive fuselage device on a commercial aircraft. Compared to an isolated, axisymmetric fuselage-propulsor configuration, a propulsive fuselage device experiences an increased circumferential inlet distortion due to three-dimensional geometric features of the aircraft. This study uses three-dimensional CFD simulations to investigate the effect of fuselage upsweep on the aero-propulsive performance of an aircraft configuration featuring a boundary layer ingestion device. It is shown that fuselage upsweep has a negative impact on the performance of a propulsive fuselage device as compared to an axisymmetric configuration. Increasing the upsweep angle by $$\Delta \alpha _{{{\text{SW}},{\text{PFC}}}} = 3.5^\circ$$ Δ α SW , PFC = 3 . 5 ∘ leads to an increase in required fuselage fan shaft power by 19%. Furthermore, it is demonstrated that the negative effects of fuselage upsweep on the propulsor’s performance can be effectively mitigated by a circumferential variation in the propulsor nacelle thickness.

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