Study on vortex flow control of inlet distortion

Anderson, Bernhard H.; Huang, Pao S.; Paschal, William A.; Cavatorta, Enrico

doi:10.2514/3.11472

Cited by 20 publications

(14 citation statements)

References 3 publications

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“…The use of vortex generators as a global method of secondary ow control was rst proposed in Anderson et al, 3 for the re-engining program on the 727-100 center inlet duct using the TAY650 series engine, and in Anderson and Gibb, 4 for the Defence Research Agency (DRA ) M2129 inlet S-duct. As a consequence of this concept, vortexgenerator installations can be optimized in terms of the inlet total pressure recovery and engine-face distortion level over a wide range of inlet operating conditions.…”

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confidence: 99%

Vortex-Generator Installation Studies on Steady-State and Dynamic Distortion

Anderson

Gibb²

1998

Journal of Aircraft

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The theoretical and experimental work carried out under the NASA /MOD joint aeronautical program has shown that computational uid dynamics (CFD) vortex-generator installation designs successfully managed inlet-duct ow distortion and that signi cant bene ts in ow unsteadiness at the engine face were also present. The main conclusions to date from the collaborative effort between the NASA Lewis Research Center and the Defence Research Agency in Bedford are as follows: 1) Vortex-generator installations can be designed to be effective over a wide range of inlet operating conditions using CFD and formal optimization procedures, 2) reductions in steady-state engine face distortion of up to 80% have been measured in the M2129 inlet S-duct using CFD-designed vortex-generator installations, 3) reductions in ow unsteadiness of up to 80% have been measured in the M2129 inlet S-duct using CFD-designed vortex-generator installations, and 4) the reduced Navier-Stokes code RNS3D is a useful tool to design vortex-generator installations to manage engine-face distortions over a wide range of inlet operating conditions. NomenclatureA = ow area c = vortex-generator chord length D = diameter DC60 = circumferential total-pressure distortion descriptor d = vortex-generator lateral spacing h = vortex-generator blade height M = Mach number Pt = total pressure Pt av = average total pressure Pt max = maximum ring total pressure Pt min = 60 deg-sector minimum ring total pressure Pt 0 = freestream or reference total pressure Q = face-average dynamic pressure R = radial distance X = axial distance from inlet throat vg = vortex-generator spacing angle vg = vortex-generator incidence angle ef = dimensionless engine-face radial distance * = displacement thickness s = installation sector angle Subscripts ef = engine face i = inlet-throat station ring = ring rms = total pressure RMS value sep = separation Received April 3, 1996; presented as Paper 96-3279 at the AIAA / ASME /SAE/

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confidence: 99%

Vortex-Generator Installation Studies on Steady-State and Dynamic Distortion

Anderson

Gibb²

1998

Journal of Aircraft

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“…However, this result was highly affected by the initial boundary-layer thickness and could be applicable only for thin incoming boundary layers. In addition, a method of reenergizing the boundary layer by locating surface protrusions within the internal duct was also studied [14][15][16][17][18]. These protrusions were usually small wing sections, sized to the local boundary-layer height and used in groups of two or more.…”

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confidence: 99%

Computational Study of a High-Performance Submerged Inlet with Bleeding Vortex

Dai-shu

Tan

Sun

et al. 2012

Journal of Aircraft

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Previous investigations on the submerged inlets show that the counter-rotating vortex pair originated from the side edge is helpful to inhale the external flow into the duct but increases the mixing loss of the inlet. To improve the performance of this type of inlet, a flow-control method based on a bleeding vortex is brought forward in this paper that is expected to use the positive effect of the vortex pair and to reduce the accompanied disadvantages.Computational results indicate that the control method is effective, with the total pressure recovery coefficient increased by 2.8% and the distortion index decreased by 51.0% at the design condition as compared with the baseline case. Furthermore, the impacts of slot location are also obtained, which underline the fact that it should be chosen carefully according to the transmitting path of the vortex pair. In addition, the drag analysis for the submerged inlet with flow control shows that it is promising for practical use with no extra drag penalty.of the inlet entrance impulse flux I in;y = y component of the inlet entrance impulse flux I out1 = inlet exit impulse flux I out1;x = x component of the inlet exit impulse flux I out1;y = y component of the inlet exit impulse flux I out2 = slot exit impulse flux I out2;x = x component of the slot exit impulse flux I out2;y = y component of the slot exit impulse flux L = distance between the slot and the aft lip M e = Mach number at the exit M 0 = freestream Mach number p = static pressure p b = back pressure p 0 = freestream static pressure P e = mass-averaged total pressure at the engine face P 0 = freestream total pressure P min 60 = minimum area-averaged total pressure over any 60 deg pie around the centroid of the engine face q avg = the area-averaged dynamic pressure over the entire engine face area v 0 = freestream velocity = angle of attack = boundary layer thickness at the entrance of the inlet 0 = freestream density = total pressure recovery coefficient Subscripts Avg = average value e = exit 0 = freestream Superscript = total or stagnation condition

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“…In the present study, the first grid point of y+ ≈1.4 and the number cells around 25 cell within the inner layer of wall. The flow field was predicted by solving the set of equations from (1) to (4). The boundary conditions were used for simulations as summarized in Table1.…”

Section: Governing Equations and Boundary Conditionsmentioning

confidence: 99%

“…Ref. [4] have been conducted experiments to study the effect of fences and VGs in terms of reducing exit flow distortion and improving total pressure recovery in two-dimensional, rectangular S-duct diffusers with different radius ratios. Ref.…”

Section: Introductionmentioning

confidence: 99%

“…One of the important technique is the passive flow control, vortex generators (VGs), which modifies the boundary layer fluid motion by bringing momentum from the outer flow region into the inner flow region of the wall bounded flow. Use of a set of VGs located on the outer and inner surfaces has been proposed for restructures the flow field [3]. Ref.…”

Section: Introductionmentioning

confidence: 99%

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Flow control in s-shaped air intake diffuser of gas turbine using proposed energy promoters

2017

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Abstract. This paper presents an experimental and numerical investigation of the flow control in an air intake S-shaped diffuser with and without energy promoters. The S-shaped diffuser had an area ratio 3.1and turning angle of 45°/45°. The proposed energy promoter was named as stream line sheet energy promoter. Computational Fluid Dynamics simulation was performed through commercial ANSYS-FLUENT 16.2 software. The measurements were made inside annular subsection, 45° from 360 o of the complete annular shape of the diffuser, at Reynolds number 5.8×10 4 and turbulence intensity 4.1%. Results for the bare S-shaped diffuser (without energy promoters) showed the flow structures within the S-shaped diffuser were dominated by counter-rotating vortices and boundary layer separation especially in the outer surface. The combination of the adverse pressure gradient at the first bend of outer surface and upstream low momentum wakes caused the boundary layer to separate early. The combinations of proposed energy promoters were installed on the inner and outer surfaces at three installation planes. The use of energy promoters resulting in significantly decreased the outer surface boundary layer separation with consequential improving the static pressure coefficient and reduction of total pressure losses.

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Study on vortex flow control of inlet distortion

Cited by 20 publications

References 3 publications

Vortex-Generator Installation Studies on Steady-State and Dynamic Distortion

Vortex-Generator Installation Studies on Steady-State and Dynamic Distortion

Computational Study of a High-Performance Submerged Inlet with Bleeding Vortex

Flow control in s-shaped air intake diffuser of gas turbine using proposed energy promoters

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