A Numerical Simulation Capability for Analysis of Aircraft Inlet – Engine Compatibility

Hale, Alan; Davis, Milt; Sirbaugh, J. R.

doi:10.1115/gt2004-53473

Cited by 15 publications

(10 citation statements)

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“…Turner et al [2] have dealt with gas turbine engine simulation, producing hybrid tools aiming to reduce computational load, while retaining an acceptable accuracy level. Alexiou et al [3], [4], have also been very active in the research field of engine flow simulation Additionally Alan Hale et al [5], have developed hybrid tools for effective gas turbine engine simulation. Finally the author of the current chapter working in conjunction with Cranfield University research team and in particular with Dr. Vasilios Pachidis has contributed substantially to the research field under context [6], [7], [8].…”

Section: Literature Reviewmentioning

confidence: 99%

Synthesis of Flow Simulation Methods for Fast and Accurate Gas Turbine Engine Performance Estimation

Templalexis¹

2013

Progress in Gas Turbine Performance

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Section: Literature Reviewmentioning

confidence: 99%

Synthesis of Flow Simulation Methods for Fast and Accurate Gas Turbine Engine Performance Estimation

Templalexis¹

2013

Progress in Gas Turbine Performance

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“…In terms of separation due to the high angle of attack, their results were consistent with experimental tests. In 2006, Hale et al [9] have used it to model the interaction between the fan and upstream distortion. The application involves an F-16 fighter jet.…”

Section: Fan Modeling Under Distortionmentioning

confidence: 99%

Development and Validation of a New Boundary Condition for Intake Analysis with Distortion

Zadeh

Trépanier

Petro

2013

International Journal of Aerospace Engineering

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The design of an intake for a gas turbine engine involves CFD-based investigation and experimental assessment in an intake test rig. In both cases, the engine is represented by a mass flux sink, usually positioned a few fan radii aft of the real fan face. In general, this approach is sufficient to analyze intake geometry for low distortion at the fan face, because in this case the interaction of the fan with the inlet flow can be neglected. Where there are higher levels of distortion at the fan face, the interaction could become more significant and a different approach would be preferable. One alternative that takes into account the interaction in such cases includes the fan in the analysis of the intake, using either a steady or unsteady flow model approach. However, this solution is expensive and too computationally intensive to be useful in design mode. The solution proposed in this paper is to implement a new boundary condition at the fan face which better represents the interaction of the fan with the flow in the air intake in the presence of distortion. This boundary condition includes a simplified fan model and a coupling strategy applied between the fan and the inlet. The results obtained with this new boundary condition are compared to full 3D unsteady CFD simulations that include the fan.

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“…The method was later used to assess the performance of a three-stage fan coupled to a forebody and inlet of an advanced military fighter aircraft [53].…”

Section: Foundational Work On Body Force Approaches In Turbomachinerymentioning

confidence: 99%

Ultra-Short Nacelles for Low Fan Pressure Ratio Propulsors

Peters¹,

Spakovszky²,

Lord³

et al. 2014

Volume 1A: Aircraft Engine; Fans and Blowers

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This thesis addresses the uncharted inlet and nacelle design space for low pressure ratio fans for advanced aeroengines. A key feature in low fan pressure ratio (FPR) propulsors with short inlets and nacelles is the increased coupling between fan and inlet. The thesis presents an integrated fan-nacelle design framework, combining a spline-based tool for the definition of inlet and nacelle surfaces with a fast and reliable body-force-based approach for the fan rotor and stator blade rows. The new capability captures the inlet-fan and fan-exhaust interactions and the flow distortion at the fan face and enables the parametric exploration of the short-inlet design territory. The interaction of the rotor with a region of high streamwise Mach number at the fan face is identified as the key aerodynamic mechanism limiting the design of short inlets. The local increase in streamwise Mach number is due to flow acceleration along the inlet internal surface coupled with a reduction in effective flow area. For a candidate short-inlet design with inlet length to fan diameter ratio L/D = 0.19, the streamwise Mach number at the fan face near the shroud increases by up to 0.16 at cruise and by up to 0.36 at off-design conditions relative to a long-inlet baseline propulsor with L/D = 0.5. As a consequence, the rotor locally operates close to choke, resulting in fan efficiency penalties of up to 1.6 % at cruise and 3.9 % at off-design. For inlets with L/D < 0.25, the benefit from reduced nacelle drag is offset by the reduction in fan efficiency, resulting in propulsive efficiency penalties. Based on a parametric inlet study, the recommended inlet L/D for engine propulsive efficiency benefits is suggested to be between 0.25 and 0.4. A candidate design with L/D = 0.25 maintains the cruise propulsive efficiency of the baseline case without jeopardizing fan and LPC stability at off-design conditions. On the aircraft system level, fuel burn benefits are conjectured to be feasible due to the reductions in nacelle weight and drag compared to an aircraft powered by the long-inlet baseline propulsor.

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A Numerical Simulation Capability for Analysis of Aircraft Inlet – Engine Compatibility

Cited by 15 publications

References 0 publications

Synthesis of Flow Simulation Methods for Fast and Accurate Gas Turbine Engine Performance Estimation

Synthesis of Flow Simulation Methods for Fast and Accurate Gas Turbine Engine Performance Estimation

Development and Validation of a New Boundary Condition for Intake Analysis with Distortion

Ultra-Short Nacelles for Low Fan Pressure Ratio Propulsors

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