Application of a Panel Method (QUADPAN) to the Prediction of Propeller Blade Loads

1986 ◽  
Author(s):  
R. E. Donham ◽  
J. D. Dupcak ◽  
F. Conner
Keyword(s):  
Panel Method ◽  
Propeller Blade ◽  
Blade Loads

Numerical Prediction of Model Podded Propeller-Ice Interaction Loads

2006 ◽  
Author(s):  
Jungyong Wang ◽  
Ayhan Akinturk ◽  
Neil Bose
Keyword(s):  
Prediction Model ◽  
National Research Council ◽  
Model Tests ◽  
Numerical Prediction ◽  
Panel Method ◽  
Operating Conditions ◽  
Propeller Blade ◽  
Hydrodynamic Loads ◽  
Hydrodynamic Calculations ◽  
Ice Loads

As the interest in arctic shipping and arctic exploration of oil and gas is increasing in recent years, the number of ice class vessels is increasing rapidly. Also the choices for propulsion devices are getting wider and these include podded propulsion systems. This study is a framework for the numerical prediction of the ice interaction loads acting on a podded propeller blade. The results of this study will help us to understand the propeller-ice interaction problem more comprehensively. Several studies for propeller-ice interaction have been carried out in the past few decades. Propeller-ice interaction, however, is a complicated process with a high level of uncertainties due to ice properties, ship operating conditions, and environmental conditions. Full-scale measurements involve high costs. In order to overcome these difficulties, model tests were carried out with model ice in an ice tank. The model tests provide well-controlled ice properties and interaction conditions to reduce the uncertainties. The tests were carried out in the ice tank with scaled down model ice at the National Research Council of Canada’s Institute for Ocean Technology. The ice loads acting on the propeller blade were measured with a six-component force and moment load cell fitted to the shaft and one of the propeller blades. Based on the experimental results, a numerical prediction model was developed to estimate the ice loads on the propeller blade. The numerical prediction is composed of three parts: the hydrodynamic calculations including separable and inseparable hydrodynamic loads, and the ice milling loads calculation. The separable and inseparable hydrodynamic loads can be obtained from clear water and blocked flow respectively. The hydrodynamic calculations were done by a low order panel method. The subroutines for calculating the ice milling loads are implemented into the panel method. The numerical prediction model for ice milling loads is described and the results are compared with those of experiments.

Measurements of Controllable Pitch Propeller Blade Loads in Turns

2009 ◽  
Author(s):  
Stuart D. Jessup ◽  
Martin Donnelly ◽  
David Fry ◽  
Ali Etebari ◽  
Josh Burton ◽  
...  
Keyword(s):  
Detailed Analysis ◽  
Propeller Blade ◽  
Blade Loading ◽  
Blade Loads

To improve the prediction of the alternating blade loading under ship turning conditions, a test was conducted in a rotating arm facility, where propeller hub loads were measured on a combatant propeller/hull configuration. To obtain the alternating blade forces, three propeller configurations were tested: the baseline five bladed prop, a one bladed version, and a four bladed version (one blade removed). Care was taken to account for propeller imbalance, and centrifugal effects on loads. PIV was also used to measure the propeller inflow. The measured alternating blade forces were analyzed relative to the earlier tests of Boswell1. Also the measured inflow was used to compare load predictions to the measured results. Detailed analysis was performed to validate the use of both a single bladed and a four bladed prop to derive the single bladed forces.

An Analytical–Numerical Aerodynamic Formulation for Efficient Aeroacoustics Analysis of Rotorcraft

2012 ◽  
Author(s):  
Massimo Gennaretti ◽  
Claudio Testa ◽  
Giovanni Bernardini ◽  
Alessandro Anobile
Keyword(s):  
External Source ◽  
Solution Procedure ◽  
Panel Method ◽  
Multidisciplinary Optimization ◽  
Computationally Efficient ◽  
Unsteady Panel Method ◽  
Method Formulation ◽  
Time Marching ◽  
Frequency Changes ◽  
Blade Loads

This paper presents an analytical-numerical aerodynamic/aeroacoustic formulation for the analysis of the tonal noise emitted by helicopter rotors and propellers. It is particularly suited for those configurations dominated by local high-frequency changes (both in time and space) of blades inflow velocity. The solution of the Ffowcs Williams-Hawkings equation for noise radiation prediction is combined with the frequency-domain Küssner-Schwarz formulation that yields the sectional, unsteady aerodynamic loads, starting from the knowledge of the downwash on the airfoil due to blade motion and inflow induced on it by any external source of perturbation. Here, the blade inflow is assumed to be evaluated through a 3D, unsteady, panel method formulation suited for the analysis of rotors operating in a complex aerodynamic environment. This aerodynamic/aeroacoustic model gives a computationally efficient solution procedure that may be conveniently applied in preliminary design/multidisciplinary optimization applications. The proposed approach is validated through comparison with the (accurate, but computationally expensive) acoustic field obtained through the blade pressure loads directly evaluated by the time-marching panel-method solver. The results are provided in terms of blade loads, noise signatures and sound pressure level contours.

FEATURES OF CONSTRUCTION OF ON-BOARD HELICOPTER RADAR ICE EXPLORATION ON BASIS OF CIRCULAR GROUND SURFACE WITH SYNTHESIS OF APERTURE ROTATING ANTENNA

2019 ◽  
pp. 31-37
Author(s):  
I. G. Antсev ◽  
A. P. Aleshkin ◽  
V. V. Vladimirov ◽  
E. O. Kudrina ◽  
O. L. Polonchik ◽  
...  
Keyword(s):  
Remote Sensing ◽  
Ground Surface ◽  
Rotor Blades ◽  
Navigation Systems ◽  
Propeller Blade ◽  
Antenna Aperture ◽  
Sensing System ◽  
Radar Systems ◽  
Simulation Results ◽  
Circular Antenna Array

The results of modeling the processes of receiving and processing the signals of remote sensing of the Earth’s surface using helicopter radar and synthesizing the antenna aperture due to its placement on the rotating rotor blades are presented. The mathematical correctness of the application of the developed algorithms for processing probing signals, as well as the uniqueness of the measurements, was confirmed. At the same time, the dimensions of the synthesized aperture due to the rotation of the radiator placed at the end of the propeller blade are equivalent to a circular antenna array with a diameter of tens of meters. The functionality of the remote sensing system based on this radar meets the requirements for ice observation and navigation systems for seagoing ships off the coast. The simulation results confirm the promise of further research in this direction and can be used in the development of radar systems with synthesized antenna aperture mounted on rotating rotor blades.

Coupled Pitch Links for Multiharmonic Isolation Using Fluidic Circuits

2014 ◽  
Vol 59 (4) ◽  
pp. 1-11
Author(s):  
Lloyd H. Scarborough III ◽  
Christopher D. Rahn ◽  
Edward C. Smith ◽  
Kevin L. Koudela
Keyword(s):  
Experimental Validation ◽  
Analytical Models ◽  
Main Rotor ◽  
Fluidic Devices ◽  
Simulation Results ◽  
Fluidic Circuits ◽  
Blade Loads

Replacing stiff pitch links on rotorcraft with coupled fluidic devices has the potential to reduce the aerodynamic blade loads transmitted through the pitch links to the swashplate. Analytical models of two fluidic devices coupled with three different fluidic circuits are derived. These passive fluidlastic systems are tuned, by varying the fluid inertances and capacitances of each fluidic circuit, to reduce the transmitted pitch-link loads. The different circuit designs result in transmitted pitch-link loads reduction at up to three main rotor harmonics. The simulation results show loads reduction at the targeted out-of-phase and in-phase harmonics of up to 88% and 93%, respectively. Experimental validation of two of the fluidic circuits demonstrates loads reduction of up to 89% at the out-of-phase isolation frequencies and up to 81% at the in-phase isolation frequencies.

scholarly journals Aspects of the Application of a Three Dimensional Panel Method Tool in the Design of a Light Aircraft

2005 ◽  
Author(s):  
Paulo Henriques Iscold Andrade De Oliveira ◽  
Marcos Vinícius Bortolus
Keyword(s):  
Three Dimensional ◽  
Panel Method
Sign in / Sign up

Export Citation Format

Share Document