Aerodynamic analysis of an installed thrust reverser

Strash, Daniel J.; Summa, J. Michael; Frank, J. Howard; Standish, Robert

doi:10.2514/6.1997-3153

Cited by 5 publications

(4 citation statements)

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“…hexahedron meshes are adopted to generate the grids. The purpose of this paper is to search the reverse flow distribution, so it is enough to adopt exponential dense technique near the wall [5] [7] . Figure 4 shows the perspective view of the grid indicating the flow direction.…”

Section: Numerical Simulation Methodsmentioning

confidence: 99%

3D numerical simulation of clamshell thrust reverser with flap deployed while landing

Liu

Wang

Jiaqi

et al. 2010

2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics

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The flow field distribution characteristic of a clamshell thrust reverser with flap deployed while landing is investigated based on Computational Fluid Dynamics (CFD) technology. The mesh was generated with unstructured tetrahedron and unstructured hexahedron meshes and S-A turbulent model in solving Reynolds averaged N-S equations is adopted. The results show, in the range of landing speed between 136.1m/s and 17.0m/s, the hot reverse exhaust flow from the clamshell thrust reverser is not re-injected into the engine inlet; and it impinges on part of the aerofoil and pylon. As landing speed decreases, the hot reverse exhaust flow spreads forward and laterally deeper, so it may be re-injected by near engine inlet if the aerofoil sweepback is large enough, which will result in inlet distortion. When landing speed decreases down to 34m/s, the hot reverse exhaust flow starts to impinge on the ground, which may wind up some dross to the inlet. At last, the reverse thrust decreases as landing speed decreases. Key words: clamshell thrust reverser, flap, hot reverse exhaust flow, inlet distortion, reverse thrust 978-1-4244-6044-1/10/$26.00 ©2010 IEEE

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Section: Numerical Simulation Methodsmentioning

confidence: 99%

3D numerical simulation of clamshell thrust reverser with flap deployed while landing

Liu

Wang

Jiaqi

et al. 2010

2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics

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“…Around a Thrust Reverser I. Introduction A IRCRAFT engine thrust can be redirected by thrust reverser (TR) devices to rapidly decrease the aircraft speed at landing, after touchdown [1,2]. During aircraft operations, the behavior of the TR is critical; when the flow is reversed, the exhaust flow may be reingested, i.e., the circumstance whereby the engine exhaust flow is redirected upstream of the engine and captured again at its inlet.…”

Section: Three-dimensional Quantitative Flow Visualizationmentioning

confidence: 99%

“…Most research works that report quantitative measurements of TRs in wind tunnels make use of more traditional techniques, namely, force balance [1][2][3], pressure [3][4][5], and temperature measurements. The latter are used as a way to assess the conditions leading to reingestion by (moderate) heating of the jet plume and measurement of the intake flow temperature [4].…”

Section: Three-dimensional Quantitative Flow Visualizationmentioning

confidence: 99%

Three-Dimensional Quantitative Flow Visualization Around a Thrust Reverser

Hysa,

Tuinstra,

Sciacchitano

et al. 2023

AIAA Journal

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Volumetric particle tracking velocimetry measurements are performed in a low-speed wind tunnel to study the flow around a 1:12-scale aircraft model with jet engines operating with thrust reversers. The engine jet and freestream flow velocity are varied to yield a jet to freestream velocity ratio of [Formula: see text] ranging from 1.5 to 6. Measurements at such scale ([Formula: see text]) require the use of strongly scattering helium-filled soap bubbles as flow tracers, which are introduced in both the jet and the freestream flow. The tracer’s three-dimensional motion is determined using an array of cameras and a Lagrangian particle tracking algorithm. The mean velocity field reveals the jet inner structure as well as its interaction with the freestream, the ground board, the nacelle, the fuselage, and the horizontal and vertical tails. The experiments allow detection of exhaust reingestion as well as the aerodynamic interference with control surfaces at the tail segments in a single measurement volume. The results are in good agreement with conventional temperature rake measurements while adding details of the flow topology and of the large-scale unsteady flow fluctuations. Finally, the jet reversal characteristics with varying freestreams and nozzle pressure ratios are assessed, demonstrating the feasibility and versatility of volumetric velocimetry measurements for industrial aerodynamics.

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“…12 moves the blocker doors to block the flow of air between the fan duct assembly and the thrust reverser sleeve assemblies [5], then exposes the cascade vanes. The air then flows out through the cascade vanes which direct the air forward to create reverse thrust [6].…”

Section: Imeti 2016mentioning

confidence: 99%

Analysis and simulation on two types of thrust reversers in an aircraft engine

Tao

Xiong

et al. 2017

MATEC Web Conf.

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Abstract. With rapid development of new composite material and manufacturing , innovative engineering solutions are supplied to the advanced nacelle, such as integrated propulsion system(IPS) , carbon-fiber composite inner skin by single-piece molding processǴwhich offers a reduction in fuel burn and less noise produced by engines. The advanced nacelle has an O-duct thrust reverser demonstrator whose composite structure is in the form of an "O" as opposed to the traditional "D-duct". A comparative study is to be conducted to investigate the differences between the latest O-duct and conventional D-duct in numerical approaches. To focus on the quantitative analysis of thrust reverser's operation, this paper mainly uses CATIA/Digital Mock Up(DMU) to simulate under deployment and stowed conditions of two different thrust reverser. After comparing the structural weight, the design models of blocker door are built for kinematic analysis of relevant mechanism and simulation. The results show that simplified design and elimination of multiple interfaces generates weight saving, O-duct improves airflows within the engine, meanwhile D-duct has excellent cost effective and maintainability.

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Aerodynamic analysis of an installed thrust reverser

Cited by 5 publications

References 0 publications

3D numerical simulation of clamshell thrust reverser with flap deployed while landing

3D numerical simulation of clamshell thrust reverser with flap deployed while landing

Three-Dimensional Quantitative Flow Visualization Around a Thrust Reverser

Analysis and simulation on two types of thrust reversers in an aircraft engine

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