Separation safety analysis using CFD simulation and remeshing

Olejnik, Aleksander; Dziubiński, Adam; Kiszkowiak, Łukasz

doi:10.1016/j.ast.2020.106190

Cited by 11 publications

(3 citation statements)

References 11 publications

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“…The numerical strength analysis of a high pressure turbine blade was performed using the finite element method (FEM) implemented in specialized software ANSYS, which is one of the most recognized codes for solving various types of problems in mechanics, especially in the field of strength analysis or fluid flow [ 25 , 26 ]. Moreover, the FEM is one of the most commonly used methods for solving engineering problems in the field of strength analysis.…”

Section: Resultsmentioning

confidence: 99%

A Novel Method for High Temperature Fatigue Testing of Nickel Superalloy Turbine Blades with Additional NDT Diagnostics

et al. 2021

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In this paper, a novel method for high temperature fatigue strength assessment of nickel superalloy turbine blades after operation at different times (303 and 473 h) was presented. The studies included destructive testing (fatigue testing at temperature 950 °C under cyclic bending load), non-destructive testing (Fluorescent Penetrant Inspection and Eddy Current method), and finite element modelling. High temperature fatigue tests were performed within load range from 5200 to 6600 N using a special self-designed blade grip attached to the conventional testing machine. The experimental results were compared with the finite element model generated from the ANSYS software. It was found that failure of turbine blades occurred in the area with the highest stress concertation, which was accurately predicted by the finite element (FE) model.

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Section: Resultsmentioning

confidence: 99%

A Novel Method for High Temperature Fatigue Testing of Nickel Superalloy Turbine Blades with Additional NDT Diagnostics

et al. 2021

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“…Additionally, different aerodynamic configurations of embedded missiles affect their separation compatibility. Olejnik et al [17] simulated the separation process of a GBU-31 bomb and a 370 gallon empty fuel tank from an aircraft based on a 6-DOF program and CFD code. Their results closely matched wind tunnel tests and offered suggestions for safe separation.…”

Section: Introductionmentioning

confidence: 99%

Safety Analysis of Initial Separation Phase for AUV Deployment of Mission Payloads

Wang,

Gu,

Lang

et al. 2024

JMSE

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This study verifies the effects of deployment parameters on the safe separation of Autonomous Underwater Vehicles (AUVs) and mission payloads. The initial separation phase is meticulously modeled based on computational fluid dynamics (CFD) simulations employing the cubic constitutive Shear Stress Transport (SST) k-ω turbulence model and overset grid technologies. This phase is characterized by a 6-degree-of-freedom (6-DOF) framework incorporating Dynamic Fluid-Body Interaction (DFBI), supported by empirical validation. The SST k-ω turbulence model demonstrates superior performance in managing flows characterized by adverse pressure gradients and separation. DFBI entails computationally modeling fluid–solid interactions during motion or deformation. The utilization of overset grids presents several advantages, including enhanced computational efficiency by concentrating computational resources solely on regions of interest, simplified handling of intricate geometries and moving bodies, and adaptability in adjusting grids to accommodate changing simulation conditions. This research analyzes mission payloads’ trajectories and attitude adjustments after release from AUVs under various cruising speeds and initial release dynamics, such as descent and angular velocities. Additionally, this study evaluates the effects of varying ocean currents at different depths on separation safety. Results indicate that the interaction between AUVs and mission payloads during separation increases under higher navigational speeds, reducing the separation speed and degrading the stability. As the initial drop velocities increase, fast transition through the AUV’s immediate flow field promotes separation. The core of this process is the initial pitch angle management upon deployment. Optimizing initial pitching angular velocity prolongs the time for mission payloads to reach their maximum pitch angle, thus decreasing horizontal displacement and improving separation safety. Deploying AUVs at greater depths alleviates the influence of ocean currents, thereby reducing disturbances during payload separation.

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“…Although the version of software is slightly obsolete, it was kept along the whole project duration due to the results comparability. Various science papers [3,4,5,6] show the possibilities of using this type of software to solve similar problems or simulate of many phenomena occurring during the flow of liquid around a solid body. Cooling of the aircraft engine was already undertaken in the literature.…”

Section: Introductionmentioning

confidence: 99%

Ventilation Analysis of Simplified Engine Nacelle for Pusher Aircraft

Olejnik

Kiszkowiak

Dziubmski

2022

IOP Conf. Ser.: Mater. Sci. Eng.

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The paper contains the results of CFD analysis of flow inside the simplified engine nacelle, containing the engine in a pusher configuration. The authors have tested a set of solutions to increase an efficiency of the cooling system of this type of engine. Unfortunately, all the positive effects of the fact, that the aircraft engine appears in the wake of the propeller during taxiing and waiting for takeoff, are nonexistent in this type of configuration. An engine overheating is here a problem, because an airflow has to be pulled through the nacelle to cool down the engine block and radiators of cylinder heads. That design demands to analyze the cover shape of the nacelle, to properly use the main propeller pressure jump on the one hand, and rather adequate and complicated flow inside the nacelle to be modelled on the other. The aircraft CAD geometry has been simplified to allow for simple changes of the nacelle cover shape and easily introducing new inlets and outlets. The results prove, that the proper application of scoops gives even better result, than simply removing the cover and baffles from the engine. The exhaust scoops should be placed near the propeller plane in such pusher configuration, because the engine is not covered by the propeller wake.

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Separation safety analysis using CFD simulation and remeshing

Cited by 11 publications

References 11 publications

A Novel Method for High Temperature Fatigue Testing of Nickel Superalloy Turbine Blades with Additional NDT Diagnostics

A Novel Method for High Temperature Fatigue Testing of Nickel Superalloy Turbine Blades with Additional NDT Diagnostics

Safety Analysis of Initial Separation Phase for AUV Deployment of Mission Payloads

Ventilation Analysis of Simplified Engine Nacelle for Pusher Aircraft

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