Methodologies for Structural Optimisation of a Thrust Reverser Cascade Using a Multidisciplinary Approach

Butterfield, Joseph; Price, Mark; Armstrong, Cecil; Raghunathan, Srinivasan; Riordan, David; Cathers, G.I.

doi:10.2514/6.2003-107

Cited by 7 publications

(5 citation statements)

References 3 publications

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“…The data in this file was then re-formatted to the NASTRAN neutral file format which is compatible with the FLUENT CFD solver. Earlier work showed that higher levels of geometric idealisation used with shell and beam element representations of the cascade, meant that the outputs from these element types was not as suitable for translation to a form that could be used in the CFD model (8) . Having examined the aerodynamic and structural performance of the original cascade section, known as Design 1 (Fig.…”

Section: Methodology and Proceduresmentioning

confidence: 99%

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Enhancement of thrust reverser cascade performance using aerodynamic and structural integration

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This paper focuses on the design of a cascade within a cold stream thrust reverser during the early, conceptual stage of the product development process. A reliable procedure is developed for the exchange of geometric and load data between a two dimensional aerodynamic model and a three dimensional structural model. Aerodynamic and structural simulations are carried out using realistic operating conditions, for three different design configurations with a view to minimising weight for equivalent or improved aerodynamic and structural performance. For normal operational conditions the simulations show that total reverse thrust is unaffected when the performance of the deformed vanes is compared to the un-deformed case. This shows that for the conditions tested, the minimal deformation of the cascade vanes has no significant affect on aerodynamic efficiency and that there is scope for reducing the weight of the cascade. The pressure distribution through a two dimensional thrust reverser section is determined for two additional cascade vane configurations and it is shown that with a small decrease in total reverse thrust, it is possible to reduce weight and eliminate supersonic flow regimes through the nacelle section. By increasing vane sections in high pressure areas and decreasing sections in low pressure areas the structural performance of the cascade vanes in the weight reduced designs, is improved with significantly reduced levels of vane displacement and stress.

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Section: Methodology and Proceduresmentioning

confidence: 99%

“…Static pressure loadings on the vanes are determined using realistic operating conditions in a two dimensional CFD simulation. Methodologies for structural analysis have been examined showing that beam, shell and solid elements can effectively determine displacement levels on the cascade vanes (8) .…”

Section: Introductionmentioning

confidence: 99%

Enhancement of thrust reverser cascade performance using aerodynamic and structural integration

et al. 2004

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“…When compared with a steady jet system a pulse jet anti-icing system could produce an enhancement in heat transfer of 10-20% or reduce the bleed air requirements by 10-20%. (60)(61)(62)(63)(64)(65)(66)(67)(68)(69)(70)(71)(72)(73)(74)(75)(76)(77) Typically on modern aircraft the thrust reverser is built into the engine nacelle ( Fig. 15).…”

Section: Effect Of Pulsing the Jets On Heat Transfermentioning

confidence: 99%

Key aerodynamic technologies for aircraft engine nacelles

et al. 2006

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“…The purpose of this was to determine changes in aerodynamic performance when the vanes were displaced by the operational pressures. Higher levels of geometric idealization used with the shell and beam element representations of the cascade meant that the outputs from these models were not as suitable for translation to a form that could be used in the CFD model [15]. The structural analysis of Design 1 revealed that vane deformations were greatest in the areas of high pressure predicted by the aerodynamic analysis, around vanes 9 to 11 (see Fig.…”

Section: Weight Reduction Exercisementioning

confidence: 99%

“…Static pressure loadings on the vanes are determined using realistic operating conditions in a two-dimensional CFD simulation. Methodologies for structural analysis are examined, showing that beam, shell and solid elements can effectively determine displacement levels on the cascade vanes [15]. Vane displacements are transferred back into the CFD model to examine the effects of deformed vane geometry on aerodynamic performance of the cascade.…”

Section: Introductionmentioning

confidence: 99%

Weight reduction methodologies for a thrust reverser cascade using aerodynamic and structural integration

Butterfield

Price

Armstrong

et al. 2004

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper focuses on the aerodynamic and structural design of the cascade within a cold stream thrust reverser. Methodologies are established for improving the efficiency of the design process. Aerodynamic and structural simulations are carried out using realistic operating conditions for idealized cascade models representing three design options. The aim of this work is to minimize weight while maintaining or improving aerodynamic and structural performance. Total reverse thrust decreases by 0.28 per cent when the aerodynamic performance of the deformed cascade is compared with the undeformed case. This shows that, for the conditions tested, the displacement of the cascade vanes has a minimal affect on aerodynamic performance, and that there is scope for weight reduction. When cascade weight is reduced by 5 per cent and then 10 per cent by modifying the vane configurations, the structural performance of the cascade improves, with significantly reduced levels of vane displacement. Although reverse thrust is reduced by 9 per cent for both of the reduced-weight designs, the maximum airspeed within the thrust reverser is subsonic. The maximum airspeed is above Mach 1 for the original design. This reduces the risk of the structure being subjected to the complex loading conditions associated with the shock waves due to supersonic air flow.

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Methodologies for Structural Optimisation of a Thrust Reverser Cascade Using a Multidisciplinary Approach

Cited by 7 publications

References 3 publications

Enhancement of thrust reverser cascade performance using aerodynamic and structural integration

Enhancement of thrust reverser cascade performance using aerodynamic and structural integration

Key aerodynamic technologies for aircraft engine nacelles

Weight reduction methodologies for a thrust reverser cascade using aerodynamic and structural integration

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