Aircraft Thrust Reverser Cascade Configuration Evaluation Through CFD

Trapp, Luis Gustavo; Oliveira, Guilherme Lara

doi:10.2514/6.2003-723

Cited by 18 publications

(10 citation statements)

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“…Similar CFD studies were carried out for the cascade type reverser in ref [3] [4] and [5], and a clamshell type reverser in [6]. The CAD models in all these studies comprise of fuselage, wing, pylon and TR assembly.…”

Section: Mesh Generationmentioning

confidence: 96%

“…However, the CFD analyses performed in this paper found that approximately 8.1 million mesh elements are required to satisfy the mesh sensitivity criteria. One justification for the high number of mesh elements is that the studies in ref [3] [4] and [5] have used simplified versions of TR CAD models i.e. instead of using the actual CAD geometries for the cascade reverser blocks, Ref [3] [4] and [5] have simply drawn small rectangular surfaces on the outer nacelle.…”

Section: Mesh Generationmentioning

confidence: 99%

“…One justification for the high number of mesh elements is that the studies in ref [3] [4] and [5] have used simplified versions of TR CAD models i.e. instead of using the actual CAD geometries for the cascade reverser blocks, Ref [3] [4] and [5] have simply drawn small rectangular surfaces on the outer nacelle. This means that no internal bypass and core sections were constructed, therefore the number of mesh elements must have reduced significantly.…”

Section: Mesh Generationmentioning

confidence: 99%

“…Pressure based solver, with segregated algorithm was selected and applied, which solves the governing equations sequentially [7]. The preferred turbulence model to support the analyses was k-ε realizable; it is best suited for applications where separation and complex secondary flow features are found; previous studies carried out in academia and industry have also employed the same model [3] [4] [5].…”

Section: Cfd Setupmentioning

confidence: 99%

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Computational Fluid Dynamics Investigation of a Core-Mounted Target-Type Thrust Reverser—Part 2: Reverser Deployed Configuration

Mahmood

Jackson

Sethi

et al. 2018

Journal of Engineering for Gas Turbines and Power

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Core-mounted target-type thrust reverser (CMTTTR) design was proposed by NASA in the second half of the 90 s. NASA carried out several experiments at static conditions, and their acquired results suggested that the performance characteristics of the CMTTTR design fall short to comply with the mandatory thrust reverser (TR) performance criteria, and were therefore regarded as an infeasible design. However, the authors of this paper believe that the results presented by NASA for the CMTTTR design require further exploration to facilitate the complete understanding of its true performance potential. This part 2 paper is a continuation from Part 1 (reverser stowed configuration) and presents a comprehensive three-dimensional (3D) computational fluid dynamics (CFD) analyses of the CMTTTR in deployed configuration. The acquired results are extensively analyzed for aforementioned TR configuration operating under the static operating conditions at sea level, i.e., sea-level static, International Standard Atmosphere (ISA); the analyses at forward flight conditions will be covered in part 3. The key objectives of this paper are: First, to validate the acquired CFD results with the experimental data provided by NASA; this is achieved by measuring the static pressure values on various surfaces of the deployed CMTTTR model. The second objective is to estimate the performance characteristics of the CMTTTR design and corroborate the results with experimental data. The third objective is to estimate the pressure thrust (i.e., axial thrust generated due to the pressure difference across various reverser surfaces) and discuss its significance for formulating the performance of any TR design. The fourth objective is to investigate the influence of kicker plate installation on overall TR performance. The fifth and final objective is to examine and discuss the overall flow physics associated with the thrust reverse under deployed configuration.

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Section: Mesh Generationmentioning

confidence: 96%

Section: Mesh Generationmentioning

confidence: 99%

Section: Mesh Generationmentioning

confidence: 99%

Section: Cfd Setupmentioning

confidence: 99%

See 2 more Smart Citations

Computational Fluid Dynamics Investigation of a Core-Mounted Target-Type Thrust Reverser—Part 2: Reverser Deployed Configuration

Mahmood

Jackson

Sethi

et al. 2018

Journal of Engineering for Gas Turbines and Power

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show abstract

“…As to numerical simulation, Trapp and Oliveira [6] numerically simulated the water spray of the EMB-170 with deployed thrust reverser. Their results were in good agreement with the test results in computing the spray shape and the particle distribution around the EMB-170.…”

Section: Introductionmentioning

confidence: 99%

Aircraft Engine Water Ingestion Generated by Tire Spray on Water-Contaminated Runways

Zhao¹,

Liu²,

Qu³

2017

Proceedings of the 2017 6th International Conference on Energy and Environmental Protection (ICEEP 2017)

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Abstract. Aircraft water ingestion tests on water-contaminated runways is of great significance in the civil aircraft airworthiness certification. It is a very complex strongly nonlinear multi-physics process involving tire-generated water spray and engine spray ingestion. An integrated simulation platform, which combines the Smooth Particle Hydrodynamics (SPH) method and the Discrete Phase Model (DPM) in a finite volume framework, is developed to predict the complex physical interactions and processes. The effects of nose gear chine tires are studied in alleviating or eliminating the engine spray ingestion problem.

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Flow Separation Control of Nacelle in Crosswind by Microsecond Pulsed Surface Dielectric Barrier Discharge Plasma Actuator

Jia

Liang

et al. 2021

Flow Turbulence Combust

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Flow separation under crosswind conditions seriously jeopardizes the quality of the nacelle's ow eld. In this paper, microsecond pulsed surface dielectric barrier discharge (µSDBD) is used to suppress the ow separation and reduce the crosswind distortion of the nacelle. The ow structure induced by the µSDBD is rst explored by a high-speed schlieren system. The pressure waves composed of a cylindrical wave surrounding the electrodes and a at wave at the top of the cylindrical one can be perceived, which indicates the fast gas heating produced by the µSDBD. A set of wind tunnel tests are then conducted to verify the ability of µSDBD to suppress the nacelle ow separation and study the in uence laws of pulse frequency, coverage area, and the actuator layout on the ow control effects. Results show that plasma actuation can not only improve the total pressure at the exit of the nacelle but also suppress the ow distortion caused by the crosswind. The best ow control effect can be achieved at the pulse frequency of 500Hz, with the value of sectional distortion coe cient reduced by 57.76% compared with the baseline condition. The ow control effect with the plasma actuator covering 120° of the nacelle perimeter is better than that of 60° and 180° coverage, showing the highest ow control e ciency in the 120°c ondition. The µSDBD can improve mixing between the boundary layer and the main ow, enhancing the ability of the boundary layer to resist the adverse pressure gradient, which is bene cial to ow separation control.

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Aircraft Thrust Reverser Cascade Configuration Evaluation Through CFD

Cited by 18 publications

References 0 publications

Computational Fluid Dynamics Investigation of a Core-Mounted Target-Type Thrust Reverser—Part 2: Reverser Deployed Configuration

Computational Fluid Dynamics Investigation of a Core-Mounted Target-Type Thrust Reverser—Part 2: Reverser Deployed Configuration

Aircraft Engine Water Ingestion Generated by Tire Spray on Water-Contaminated Runways

Flow Separation Control of Nacelle in Crosswind by Microsecond Pulsed Surface Dielectric Barrier Discharge Plasma Actuator

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