Computational Analysis of Blended Winglet Model Performance by Varying Cant Angle

2019 ◽  
Vol 16 (2) ◽  
pp. 467-471
Author(s):  
Bino Prince D. Raja ◽  
G. Ramanan ◽  
Diju G. Samuel
Keyword(s):  
Fuel Consumption ◽  
Computational Analysis ◽  
Model Performance ◽  
Aircraft Engine ◽  
Modeling And Analysis ◽  
Engine Thrust ◽  
Ansys Cfx ◽  
Inclination Angles ◽  
Important Challenge ◽  
Control Surfaces

This work focuses on structural modeling and analysis of aircraft winglet control surfaces. In aerodynamic engineering, reducing drag is an important challenge. To reduce drag a fin device that is placed vertically in the angle set in the wing of the plane. Winglet design reduces fuel consumption by reducing the drag of the aircraft and will make the aircraft more stable during the flight, will also give the aircraft engine more time to reduce the load on the engine thrust life. The goal is to design and simulate a winglet aircraft model using software such as CATIA V5-which is used to build fin models and ANSYS CFX solver is used to test and simulate model fins. With winglets without fins it analyzes change the inclination angles, the results are compared and plotted. Fins are an important part of an aircraft that reduces the amount of drag and fuel consumption by using less energy while reducing wing vortexes.

Impact of Air System Bleeding on Aircraft Engine Performance

2011 ◽  
Author(s):  
Bin Zhao ◽  
Shaobin Li ◽  
Qiushi Li ◽  
Sheng Zhou
Keyword(s):  
Fuel Consumption ◽  
Negative Impact ◽  
Pressure Ratio ◽  
Engine Performance ◽  
Thermodynamic Cycle ◽  
Aircraft Engine ◽  
Engine Model ◽  
Engine Thrust ◽  
Air System ◽  
Compressor Performance

Air system bleeding is indispensable to aircraft engines despite its negative impact on the engine thrust and the fuel consumption. However, the compressor performance can be improved if the bleeding design is optimized. The model in this paper is a one-dimensional engine model based on air system bleeding. The relation between the compressor performance and the engine thermodynamic cycle caused by bleeding is analyzed to explore the potential of air system bleeding in improving compressor and engine performance. The results show that if bleeding brings an increase the pressure ratio of compressor, the negative impact on engine specific fuel consumption can be inhibited. If the efficiency of compressor is increased after bleeding, the negative impact on engine thrust can be alleviated. With proper bleeding flow rates, if both the pressure ratio and the efficiency increase at the same time, the negative impact on the engine performance can be eliminated.

scholarly journals Quality control stress test for deep learning-based diagnostic model in digital pathology

2021 ◽  
Author(s):  
Birgid Schömig-Markiefka ◽  
Alexey Pryalukhin ◽  
Wolfgang Hulla ◽  
Andrey Bychkov ◽  
Junya Fukuoka ◽  
...  
Keyword(s):  
Deep Learning ◽  
Cancer Detection ◽  
Stress Testing ◽  
Computational Analysis ◽  
Stress Test ◽  
Digital Pathology ◽  
Model Performance ◽  
Diagnostic Model ◽  
Model Accuracy ◽  
Diagnostic Models

AbstractDigital pathology provides a possibility for computational analysis of histological slides and automatization of routine pathological tasks. Histological slides are very heterogeneous concerning staining, sections’ thickness, and artifacts arising during tissue processing, cutting, staining, and digitization. In this study, we digitally reproduce major types of artifacts. Using six datasets from four different institutions digitized by different scanner systems, we systematically explore artifacts’ influence on the accuracy of the pre-trained, validated, deep learning-based model for prostate cancer detection in histological slides. We provide evidence that any histological artifact dependent on severity can lead to a substantial loss in model performance. Strategies for the prevention of diagnostic model accuracy losses in the context of artifacts are warranted. Stress-testing of diagnostic models using synthetically generated artifacts might be an essential step during clinical validation of deep learning-based algorithms.

Modeling and Analysis of Anti-Icing Power of Aircraft Engine Inlet Based on Symmetric Algorithms

2021 ◽  
Vol 7 (6) ◽  
pp. 6361-6374
Author(s):  
Hui Peng
Keyword(s):  
Flow Field ◽  
Evaluation Method ◽  
Learning Strategy ◽  
Aircraft Engine ◽  
Absolute Error ◽  
Civil Aviation ◽  
Particle Swarm Algorithm ◽  
Intake Port ◽  
Experimental Conditions ◽  
Modeling And Analysis

To evaluate the capability of engine inlet, inlet components and power plant anti ICER under low temperature, this paper introduces the evaluation method of anti icing system for civil aviation engine room, and analyzes the anti icing power of the aircraft intake based on the symmetric algorithm. The realizable k-cube model and wall function method are used to analyze the flow field in the inlet of an aircraft engine. Based on the analysis of the flow field of the intake port of an aircraft engine, the anti ice power of the intake port is calculated according to the heat balance relationship of the intake port surface. The symmetrical particle swarm algorithm is adopted to optimize the calculation process of inlet anti-ice power, and the particle wide area learning strategy is used to promote the calculation of inlet anti-ice power. In this way, the computational complexity is significantly reduce and the accuracy of the power analysis of the inlet anti-ice is enhanced. The simulation results show that the absolute error of the proposed method is less than 1% in 1000 iterations. Through the analysis of the surface temperature changes of the inlet deflector under different experimental conditions, it can be known that the method can effectively analyze the anti-icing power of aircraft engine inlet.

scholarly journals Redesigning a compressor inlet guide vane for 0 to 60 degree stagger angles

2021 ◽  
Author(s):  
Stephanie Waters
Keyword(s):  
Fuel Consumption ◽  
Guide Vane ◽  
Leading Edge ◽  
Aircraft Engine ◽  
Inlet Guide Vane ◽  
Pressure Loss Coefficient ◽  
Compressor Inlet ◽  
Curvature Distribution ◽  
Stagger Angle ◽  
Total Pressure Loss Coefficient

This report's objective is to reduce the total pressure loss coefficient of an inlet guide vane (IGV) at high stagger angles and to therefore reduce the overall fuel consumption of an aircraft engine. IGVs are usually optimized for cruise where the stagger angle is approximately 0 degrees. To reduce losses, four different methodologies were tested: increasing the leading edge radius, increasing the camber, creating a "drooped nose", and creating an "S" curvature distribution. A baseline IGV was chosen and modified using these methodologies to create 10 new IGV designs. CFX was used to perform a CFD analysis on all 11 IGV designs at 5 stagger angles from 0 to 60 degrees. Typical missions were analyzed and it was discovered that the new designs decreased the fuel consumption of the engine. The IGV with the "S" curvature and thicker leading edge was the best and decreased the fuel consumption by 0.24%.

The Effect of Blade Count on Body Force Model Performance for Axial Fans

2020 ◽  
Author(s):  
Palak Saini ◽  
Jeff Defoe
Keyword(s):  
Body Force ◽  
Computational Cost ◽  
Model Performance ◽  
Aircraft Engine ◽  
The Body ◽  
Force Model ◽  
Cooling Flows ◽  
Cooling Fans ◽  
Axial Fans ◽  
Spanwise Flow

Abstract Body force models enable inexpensive numerical simulations of turbomachinery. The approach replaces the blades with sources of momentum/energy. Such models capture a “smeared out” version of the blades’ effect on the flow, reducing computational cost. The body force model used in this paper has been widely used in aircraft engine applications. Its implementation for low speed, low solidity (few blades) turbomachines, such as automotive cooling fans, enables predictions of cooling flows and component temperatures without calibrated fan curves. Automotive cooling fans tend to have less than 10 blades, which is approximately 50% of blade counts for modern jet engine fans. The effect this has on the body force model predictions is unknown and the objective of this paper is to quantify how varying blade count affects the accuracy of the predictions for both uniform and non-uniform inflow. The key findings are that reductions in blade metal blockage combined with spanwise flow redistribution drives the body force model to more accurately predict work coefficient as the blade count decreases, and that reducing the number of blades is found to have negligible impacts on upstream influence and distortion transfer in non-uniform inflow until extremely low blade counts (such as 2) are applied.

Modeling and Analysis of a Digital Hydraulic Actuator for Flight Control Surfaces

2021 ◽  
Author(s):  
R. S. Lopes ◽  
M. P. Nostrani ◽  
L. A. Carvalho ◽  
A. Dell’Amico ◽  
P. Krus ◽  
...  
Keyword(s):  
Performance Analysis ◽  
Flight Control ◽  
Data Model ◽  
Flight Performance ◽  
Hydraulic Actuator ◽  
Hydraulic Power ◽  
Fighter Aircraft ◽  
Modeling And Analysis ◽  
Modeling Process ◽  
Control Surfaces

Abstract This paper presents the design and modeling process of a flight control actuator using digital hydraulics and a performance analysis that compares the proposed solution and the Servo Hydraulic Actuator (SHA) on a fighter aircraft model. The proposed solution is named Digital Hydraulic Actuator (DHA) and comprises the use of a multi-chamber cylinder controlled by on/off valves and different pressures sources provided by a centralized hydraulic power unit, as proposed in the Fly-by-Wire (FbW) concept. The analyses were carried out using the Aero-Data Model in a Research Environment (ADMIRE), which was developed for flight performance analysis. The actuators were modeled using the software Matlab/Simulink® and Hopsan. They were applied to control the aircraft elevons in a flight mission close to the aircraft limits, to evaluate the actuator’s behavior and energy efficiency. The results show a reduction in energy dissipation up to 22.3 times when comparing the DHA with the SHA, and despite the overshooting and oscillations presented, the aircraft flight stability was not affected.

A Study of External Fuel Vaporization

1981 ◽  
Author(s):  
E. J. Szetela ◽  
L. Chiappetta ◽  
C. E. Baker
Keyword(s):  
Thermal Stability ◽  
Gas Turbine ◽  
Conceptual Design ◽  
Energy Efficient ◽  
Weight Ratio ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Performance Control ◽  
Engine Thrust ◽  
Fuel Vaporization

A conceptual design study was conducted to devise and evaluate techniques for the external vaporization of fuel for use in an aircraft gas turbine with characteristics similar to the Energy Efficient Engine (E3). A second purpose of the study was to select the most favorable fuel vaporization concept. In the study, three candidate concepts were analyzed from the standpoint of fuel thermal stability, integration of the vaporizer system into the aircraft engine, engine and vaporizer dynamic response, startup and altitude restart, engine performance, control requirements, safety, and maintenance. The results of the study indicate that an external vaporization system can be devised for an E3 -type engine with hardware of reasonable size. The hardware can be packaged without increasing the total engine volume and the system is not unduly complex. The selected concept offers potential gains in engine performance in terms of reduced specific fuel consumption and improved engine thrust/weight ratio. The thrust/weight improvement can be traded against vaporization system weight. However, the vaporizer is subject to fouling with deposits formed at the walls exposed to heated fuel.

scholarly journals Optimizing Aircraft Performance With Adaptive, Integrated Flight/Propulsion Control

1990 ◽  
Author(s):  
R. H. Smith ◽  
J. D. Chisholm ◽  
J. F. Stewart
Keyword(s):  
Fuel Consumption ◽  
Control Algorithm ◽  
Aircraft Engine ◽  
Inlet Temperature ◽  
Operating Characteristics ◽  
Engine Operation ◽  
Engine Model ◽  
Life Mode ◽  
Aircraft Performance ◽  
Propulsion Control

An adaptive, integrated flight/propulsion control algorithm called Performance Seeking Control (PSC) has been developed to optimize total aircraft performance during steady state engine operation. The multi-mode algorithm will minimize fuel consumption at cruise conditions; maximize excess thrust (thrust minus drag) during aircraft accelerations, climbs, and dashes; and extend engine life by reducing Fan Turbine Inlet Temperature (FTIT) when the extended life mode is engaged. On-board models of the inlet, engine, and nozzle are optimized to compute a set of control trims, which are then applied as increments to the nominal engine and inlet control schedules. The on-board engine model is continually updated to match the operating characteristics of the actual engine cycle through the use of a Kalman filter, which accounts for anomalous engine operation. The PSC algorithm will be flight demonstrated on an F-15 test aircraft under the direction of the NASA Ames/Dryden Flight Research Facility. This paper discusses the PSC design strategy, describes the control algorithm, and presents results from high fidelity, nonlinear aircraft/engine simulations. Simulation results indicate that thrust increases as high as 15% and specific fuel consumption reductions up to 3% are realizable by the PSC system.

Convex Fuel Consumption Model for Diesel and Hybrid Buses

2017 ◽  
Vol 2647 (1) ◽  
pp. 50-60 ◽  
Author(s):  
Jinghui Wang ◽  
Hesham A. Rakha
Keyword(s):  
Fuel Consumption ◽  
Motor Vehicle ◽  
Model Performance ◽  
Field Measurements ◽  
Convex Model ◽  
Motor Vehicle Emissions ◽  
Vehicle Load ◽  
Wide Range ◽  
Consumption Model ◽  
Full Throttle

The concave fuel consumption model may generate unrealistic driving recommendations in a control system; for instance, the model may recommend higher cruise speed to achieve lower fuel consumption levels on steeper roads. To improve the model performance with regard to driving control, the study developed a convex second-order polynomial fuel consumption model for conventional diesel and hybrid-electric buses. The model simultaneously circumvents the bang-bang type of control that implies that drivers would have to accelerate at full throttle or brake at full braking to minimize their fuel consumption levels. Six bus series (four diesel series and two hybrid series), covering a wide range of bus properties, were modeled. The model was developed on the basis of the Virginia Tech comprehensive power fuel-based model (VT-CPFM) framework and, given a lack of readily available data, calibrated by conducting empirical measurements. The model was validated by comparing its estimates against in-field measurements and predictions from the comprehensive modal emissions model, the Motor Vehicle Emissions Simulator model, and the concave VT-CPFM model. The results demonstrate that the convex model generates estimates consistent with field measurements and the predictions of the other models and can provide realistic driving recommendations without significantly sacrificing accuracy relative to the concave model. Optimum fuel economy cruise speed ranges from 39 to 47 km/h for all tested buses on grades ranging from 0% to 8% and decreases with the increase of grade and vehicle load.

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