Aero-propulsive Design Optimization of a Turboelectric Boundary Layer Ingestion Propulsion System

Gray, Justin S.; Kenway, Gaetan K.; Mader, Charles A.; Martins, Joaquim R. R. A.

doi:10.2514/6.2018-3976

Cited by 27 publications

(18 citation statements)

References 32 publications

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“…The 2D aerodynamic analysis used here does not accurately capture inlet distortion, so the impact of distortion is not modelled in this work. Ongoing work with 3D aerodynamic models will account for this impact (30) .…”

Section: Propulsion Modelmentioning

confidence: 99%

Coupled aeropropulsive design optimisation of a boundary-layer ingestion propulsor

Gray

Martins

2018

Aeronaut. j.

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Airframe–propulsion integration concepts that use boundary-layer ingestion (BLI) have the potential to reduce aircraft fuel burn. One concept that has been recently explored is NASA’s STARC-ABL aircraft configuration, which offers the potential for fuel burn reduction by using a turboelectric propulsion system with an aft-mounted electrically driven BLI propulsor. So far, attempts to quantify this potential fuel burn reduction have not considered the full coupling between the aerodynamic and propulsive performance. To address the need for a more careful quantification of the aeropropulsive benefit of the STARC-ABL concept, we run a series of design optimisations based on a fully coupled aeropropulsive model. A 1D thermodynamic cycle analysis is coupled to a Reynolds-averaged Navier–Stokes simulation to model the aft propulsor at a cruise condition and the effects variation in propulsor design on overall performance. A series of design optimisation studies are performed to minimise the required cruise power, assuming different relative sizes of the BLI propulsor. The design variables consist of the fan pressure ratio, static pressure at the fan face, and 311 variables that control the shape of both the nacelle and the fuselage. The power required by the BLI propulsor is compared with a podded configuration. The results show that the BLI configuration offers 6–9% reduction in required power at cruise, depending on assumptions made about the efficiency of power transmission system between the under-wing engines and the aft propulsor. Additionally, the results indicate that the power transmission efficiency directly affects the relative size of the under-wing engines and the aft propulsor. This design optimisation, based on computational fluid dynamics, is shown to be essential to evaluate current BLI concepts and provides a powerful tool for the design of future concepts.

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Section: Propulsion Modelmentioning

confidence: 99%

Coupled aeropropulsive design optimisation of a boundary-layer ingestion propulsor

Gray

Martins

2018

Aeronaut. j.

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“…Drag and thrust were calculated as net forces integrated over aircraft and propulsion system surfaces, respectively. The overall net force in axial direction was determined as the sum of the integrated pressure and viscous forces over all body surfaces and the pressure and momentum flux contributions on the fan face and fan exit [65][66][67][68]. In a similar manner, Ordaz et al carried out an adjoint-based numerical design and optimization of BLI concepts (NASA STARC-ABL and MTA450-business jet with aft fan) with the objective of minimized flow distortion at the propulsor [69,70].…”

Section: Integral Momentum Methodsmentioning

confidence: 99%

Performance bookkeeping for aircraft configurations with fuselage wake-filling propulsion integration

et al. 2019

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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.

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“…pyCycle uses chemical equilibrium analysis [20] for its underlying thermodynamic library and uses a system of nested Newton solvers to converge complex engine cycles efficiently. pyCycle has been used for propulsion-mission optimization [21] and boundary layer ingestion studies [22,23,13].…”

Section: B Pycyclementioning

confidence: 99%

Multipoint Variable Cycle Engine Design Using Gradient-Based Optimization

Jasa

Gray

Seidel

et al. 2019

AIAA Scitech 2019 Forum

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Supersonic aircraft are challenging to optimally design due to the widely varying constraints and flight conditions they experience. Additionally, a large number of disciplinary subsystems must be considered due to highly complex design requirements. One subsystem that has a major effect on overall performance is the engine. In this work, we construct a supersonic mixed-flow variable cycle engine and perform multipoint gradient-based optimization using this model. We see that the operational variables allow the optimizer to tailor performance at each individual flight condition, leading to better overall performance. To simulate airframe integration constraints, we run successive optimizations with increasingly restrictive inlet areas and see decreases in engine performance. This work is part of a larger effort to incorporate engine design into aero-thermal-mission optimization of a supersonic aircraft.

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Aero-propulsive Design Optimization of a Turboelectric Boundary Layer Ingestion Propulsion System

Cited by 27 publications

References 32 publications

Coupled aeropropulsive design optimisation of a boundary-layer ingestion propulsor

Coupled aeropropulsive design optimisation of a boundary-layer ingestion propulsor

Performance bookkeeping for aircraft configurations with fuselage wake-filling propulsion integration

Multipoint Variable Cycle Engine Design Using Gradient-Based Optimization

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