Sensitivity Analysis of a Highly Loaded Turboprop S-Duct Intake by CFD Methods

Atalayer, Çağlar; Wulff, Detlev; Friedrichs, Jens

doi:10.2514/6.2014-3596

Cited by 5 publications

(3 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The first test mainly focused on the conventional inlet duct, while the second concept consisted of a novel dual inlet with turning diffusing ducts, and the predicted results showed that the transmission loss of the second concept was lower than that of the first one at the same frequencies. Atalayer et al [17] simulated the performance of an isolated, uninstalled S-duct of a high power turboprop with unconventional integration types to determine the geometric design limitations and trade-offs on the intake. Based on the full application of a sensitivity analysis and design methods, the effects of fundamental geometric features, such as the intake aspect ratio, duct lengths and spread angle, were deeply investigated in the study.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation on Rigid Foreign Object Exclusion in the Turboprop Engine Intake System With a Bypass Duct

2019

IEEE Access

View full text Add to dashboard Cite

By considering the exclusion characteristics of foreign objects in a new intake system with a bypass duct for turboprop engines, two kinds of common rigid foreign objects, the grains, and metal pieces, are modeled based on airworthiness standards and reference reports. On the assumption that only a perfect elastic collision occurs without any structural damage to the objects or intake walls, a numerical method based on single high-fidelity computational fluid dynamics (CFD) and dynamic unstructured mesh techniques to simulate the 6DOF motion and impacts of the rigid foreign objects is presented. A practical used intake system with a bypass duct is employed to validate the method. According to the tolerance size of the intake, two spherical grains with the radius of 0.037 m and 0.0555 m and a regular hexahedron aluminum metal piece with the dimension of 0.20 m×0.11 m×0.01 m are built to test the exclusion ability of the intake and analyze their effects on the intake performance. The simulation results indicate that, in the cases of a symmetrical flow field, geometry, and initial states, all the rigid foreign objects will move in the intake without lateral motions. The spherical grains without an initial angular velocity only translate in the intake, and the small one finally enters into the bypass duct after four impacts, while the larger one flies into the inner part of the engine after six impacts. The larger grain can lead to a more apparent loss on the intake performance due to the greater shielding effect on the flow field, and the maximum decrements of the total pressure recovery coefficient and mass flow can reach to 2% and 4.1%, respectively; the total pressure distortion rate increases 116%. A coupled motion of translation and rotation occurs for the regular hexahedron aluminum piece, and after four impacts on the intake, it finally excludes to the outer space of the nacelles from the bypass duct. Compared to the spherical grains, the aluminum piece has more significant actions on the intake performance. The maximum losses of the total pressure recovery coefficient and mass flow can be 2.3% and 1.54%, respectively, while the distortion rate increases 518%. Although the numerical method in this study is simple and ideal, it can help researchers to obtain quick and effective evaluation results in the initial design stage of the new intake system with a bypass duct for the turboprop engine to improve the design efficiency and level.INDEX TERMS Turboprop aircraft, intake, bypass duct, foreign object, perfect elastic collision, dynamic mesh, computational fluid dynamics (CFD).

show abstract

Section: Introductionmentioning

confidence: 99%

Numerical Simulation on Rigid Foreign Object Exclusion in the Turboprop Engine Intake System With a Bypass Duct

2019

IEEE Access

View full text Add to dashboard Cite

show abstract

“…The radius of the first bend was kept as half of the second bend radius at r / D = 0.71 for both types. The length aspect ratio was set to L / D = 3, based on the results of the previous isolated intake analysis (14) . The inlet width was kept equal to AIP diameter D with a highlight spread angle of α = 32.71°.…”

Section: Model Set-upmentioning

confidence: 99%

Aerodynamic investigation of S-duct intake for high power turboprop installed on a channel wing

2017

View full text Add to dashboard Cite

Installation effects on the S-duct intakes of a high power turboprop were investigated by comparing three different nacelle configurations as the channel wing, over-the-wing and conventional tractor wing using computational fluid dynamic methods. The interaction of the propeller, the wing, and the nacelle on the scoop type turboprop intakes were identified in terms of recovery and distortion on the aerodynamic interface planes. An actuator disc model was used to simulate the propeller downstream effects. The channel wing installation of S-ducts showed approximately 2% higher total pressure recovery than the other configurations. The channel wing configuration with a wrap-around S-duct experienced a 2% lower circumferential distortion intensity, whereas over-the-wing had an increase by 3% in comparison to the tractor wing. It was also observed that the S-duct type had a greater influence on the radial distortion intensity than the installation type. The swirl coefficient distribution showed that multiple peaks occurred as opposed to swirl results based on a single sector of the aerodynamic interface plane. The difference between swirl peaks of shaft penetration S-duct was reduced by 14% when installed on channel wing, whereas the peaks of wrap-around experienced 90° phase shift, and their difference showed 10% increase on channel wing.

show abstract

“…Atalayer et al 10 have investigated S-duct inlet of a turboprop engine. The flow simulations were performed without propeller and particle separator effects.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Performance of the Adaptive Nacelle Inlet

Majić

Efraimsson

O’Reilly

2015

33rd AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

The numerical aerodynamic investigations of an adaptive turbofan-engine inlet is performed. The adaptation is made on the front inner part of the inlet by changing positions of two contour knots, which mimic the possible inlet structure morphing. The numerical calculations are performed using Reynolds Averaged Navier-Stokes (RANS) simulations for the climb condition. The evaluation of the aerodynamic performance is based on the inlet total pressure recovery, DC60 parameter and standard deviation of the normal velocity at the fan plane. The results exhibit common trend which is a shift of the evaluated parameters towards beneficial level by increasing the radial position of the first knot at the inlet shape region which is close to the leading edge. Alteration of second knot, which is more distant from leading edge, results in beneficial performance for several inlet shapes. For all parameters, the same group of inlet shapes was isolated as a group of best performance. Nomenclature(r, x) Cylindrical coordinate system coordinates, m D FAN Fan diameter, m D MAX Nacelle maximum diameter, m D EXIT Nacelle exit diameter, m D SPIN Spinner diameter, m DC60 Distortion parameter, -L Nacelle length, m Ma Mach number, -p Pressure, Pa p tFAN Mass flow averaged total pressure at the fan plane, Pa p t∞ Mass flow averaged total pressure of the free stream, Pa Q m Mass flow, kg/s σ vn Surface standard deviation of normal velocity, m/s T Temperature, K α Angle of attack, • η Total pressure recovery, -

show abstract

Sensitivity Analysis of a Highly Loaded Turboprop S-Duct Intake by CFD Methods

Cited by 5 publications

References 1 publication

Numerical Simulation on Rigid Foreign Object Exclusion in the Turboprop Engine Intake System With a Bypass Duct

Numerical Simulation on Rigid Foreign Object Exclusion in the Turboprop Engine Intake System With a Bypass Duct

Aerodynamic investigation of S-duct intake for high power turboprop installed on a channel wing

Aerodynamic Performance of the Adaptive Nacelle Inlet

Contact Info

Product

Resources

About