Parallel solution of lifting rotors in hover and forward flight

An implicit unsteady, multiblock, multigrid, upwind solver including mesh deformation capability, and structured multiblock grid generator, are presented and applied to lifting rotors in both hover and forward flight. To allow the use of very fine meshes and, hence, better representation of the flow physics, a parallel version of the code has been developed. It is demonstrated that once the grid density is sufficient to capture enough turns of the tip vortices, hover exhibits oscillatory behaviour of the wake, even using a steady formulation. An unsteady simulation is then presented, and detailed analysis of the time‐accurate wake history is performed and compared to theoretical predictions. Forward flight simulations are also presented and, again, grid density effects on the wake formation investigated. Parallel performance of the code using up to 1024 CPU's is also presented. Copyright © 2006 John Wiley & Sons, Ltd.     

A framework for CFD analysis of helicopter rotors in hover and forward flight

A framework is described and demonstrated for CFD analysis of helicopter rotors in hover and forward flight. Starting from the Navier–Stokes equations, the paper describes the periodic rotor blade motions required to trim the rotor in forward flight (blade flapping, blade lead‐lag and blade pitching) as well as the required mesh deformation. Throughout, the rotor blades are assumed to be rigid and the rotor to be fully articulated with separate hinges for each blade. The employed method allows for rotors with different numbers of blades and with various rotor hub layouts to be analysed. This method is then combined with a novel grid deformation strategy which preserves the quality of multi‐block structured, body‐fitted grids around the blades. The coupling of the CFD method with a rotor trimming approach is also described and implemented. The complete framework is validated for hovering and forward flying rotors and comparisons are made against available experimental data. Finally, suggestions for further development are put forward. For all cases, results were in good agreement with experiments and rapid convergence has been obtained. Comparisons between the present grid deformation method and transfinite interpolation were made highlighting the advantages of the current approach. Copyright © 2006 John Wiley & Sons, Ltd.     

On self-excited whirl of rotors

Summary The paper presents a study of the non-synchronous, self-excited whirl of continuous rotors caused by internal damping forces and by hydrodynamic bearing-film forces. Taking into account gyroscopic effects, the effect of shear on bending, and external damping, the equations of motion are derived by the variational principle. By means of two mode expansions simple expressions are obtained for the limit of stability and the corresponding whirling frequency that are valid for small values of the velocity dependent forces.Numerical methods are used to obtain better approximations to the limits of stability and the whirling frequencies. The results show that for large values of internal and external damping forces and gyroscopic moments, the widely used two-mode approximation may be greatly in error. It is found that if the limit of stability is raised by adding external damping to the rotor system, then even a small amount of internal damping may considerably reduce the limit of stability. In accordance with experimental work done by other authors, it is found that for certain damping conditions a second stability region exists.

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Übersicht Der Artikel enthält eine Untersuchung von nicht synchronen selbsterregten Kreiselbewegungen eines kontinuierlichen Rotors, die durch innere Dämpfungskräfte und hydrodynamische Schmierfilmkräfte verursacht werden. Unter Berücksichtigung des Kreiseleffektes, des Einflusses der Schubspannung auf die Biegung und der äußeren Dämpfung werden die Bewegungsgleichungen nach dem Variationsprinzip abgeleitet. Mit Hilfe einer Annäherung mit zwei Koordinatenfunktionen erhält man einfache Ausdrücke für die Stabilitätsgrenze und für die entsprechende Kreiselfrequenz, die für kleine Werte der von der Geschwindigkeit abhängigen Kräfte gelten.Um bessere Näherungen für die Stabilitätsgrenzen und die Kreiselfrequenzen zu erhalten, werden numerische Methoden angewandt. Die Ergebnisse zeigen, daß die oft benutzte Annäherung mit zwei Koordinatenfunktionen für große Werte der inneren und äußeren Dämpfung sowie bei Gegenwart von Kreiselmomenten zu großen Fehlern führen kann. Es wird gezeigt, daß schon ein kleiner Beitrag an innerer Dämpfung die Stabilitätsgrenze merkbar reduzieren kann, wenn man die Stabilitätsgrenze durch Hinzufügung äußerer Dämpfung zum Rotorsystem hinauszuschieben sucht. In Übereinstimmung mit den experimentellen Ergebnissen anderer Autoren wird gezeigt, daß ein zweiter Stabilitätsbereich für gewisse Dämpfungsbedingungen existiert.

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The author wish to thank Professor Frithiof I. Niordson, lic. techn. Pauli Pedersen and lic. techn. Viggo Tvergaard for their stimulating criticism of this work.     

On the acceleration of rotors through their critical speed

Summary In extension to previous studies on the influence of external viscous damping and elastic hysteresis on the transient motion of a rotor as it passes through its critical velocity, this paper reports diagrams of the deflection and of its angular velocity obtained from new IBM7040 tabulations. The theoretical results are compared with the experimental results observed on a model.

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Sommario Nel presente lavoro vengono esposti i risultati di una trattazione analitica del problema dell'avviamento di un rotore con passaggio attraverso la velocità critica flessionale, che tiene conto degli smorzamenti esterni e dell'isteresi elastica dell'albero, e che è stata oggetto di precedenti ricerche. Vengono forniti diagrammi dell'ampiezza della freccia e della sua velocità angolare ottenuti mediante nuove tabulazioni effettuate con calcolatore IBM7040. Da ultimo si confrontano i risultati analitici con quelli sperimentali osservati su un modello appositamente realizzato.

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Study conducted under the auspices of the Consiglio Nazionale delle Ricerche.     

On the balancing of flexible rotors independent on boundary conditions

Summary Very well elaborated recent methods for balancing flexible rotors are based on the approximation of the deflection brought about by its unbalance, by the normal modes of the rotor. Since normal modes depend on boundary conditions, the so performed balancing of the rotor also depends on them. This fact may lead to some difficulties if the stiffness of the rotor bearings is considerably unisotropic in various radial directions or if the rotor has been balanced on the balancing machine with stiffness characteristics of bearing mounting essentially other under actual operation. — A method is suggested in the paper that removes the mentioned dependence of flexible rotor balancing on its boundary conditions. It is based on the approximation of the deflection by a complete system of coordinate functions independent on the stiffness of supporting its ends. Hence the flexible rotor, one balanced according to this method, will continue to be balanced even under an arbitrary stiffness of its bearings.

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Übersicht Die bisherigen, sehr gut bearbeiteten Methoden zum Auswuchten elastischer Rotoren basieren auf der Approximation der durch ihre Unwucht hervorgerufenen Durchbiegung durch die Normalformen des Rotors. Da die Normalformen von den Randbedingungen abhängen, hängt von ihnen auch die auf diese Weise ausgeführte Auswuchtung des Rotors ab. Diese Tatsache kann zu gewissen Schwierigkeiten führen, falls die Lagerungssteifigkeit der Rotorlager in verschiedenen Radialrichtungen beträchtlich anisotrop ist, oder falls der Rotor an einer Auswuchtmaschine ausgewuchtet wurde mit wesentlich verschiedenen Steifheitscharakteristiken des Lagersitzes als dies im Istbetrieb der Fall ist. — In der Arbeit wird eine Methode entwickelt, die die genannte Abhängigkeit der Auswuchtung des elastischen Rotors von deren Randbedingungen aufhebt. Sie basiert auf der Approximation der Durchbiegung durch ein vollständiges System von Koordinatenfunktionen, die von der Lagerungssteifheit seiner Enden unabhängig sind. Somit bleibt der nach dieser Methode einmal ausgewuchtete elastische Rotor auch bei einer beliebigen Steifheit seiner Lager ausgewuchtet.

     

A high‐order backward forward sweep interpolating algorithm for semi‐Lagrangian method

Conventional semi‐Lagrangian methods often suffer from poor accuracy and imbalance problems of advected properties because of low‐order interpolation schemes used and/or inability to reduce both dissipation and dispersion errors even with high‐order schemes. In the current work, we propose a fourth‐order semi‐Lagrangian method to solve the advection terms at a computing cost of third‐order interpolation scheme by applying backward and forward interpolations in an alternating sweep manner. The method was demonstrated for solving 1‐D and 2‐D advection problems, and 2‐D and 3‐D lid‐driven cavity flows with a multi‐level V‐cycle multigrid solver. It shows that the proposed method can reduce both dissipation and dispersion errors in all regions, especially near sharp gradients, at a same accuracy as but less computing cost than the typical fourth‐order interpolation because of fewer grids used. The proposed method is also shown able to achieve more accurate results on coarser grids than conventional linear and other high‐order interpolation schemes in the literature. Copyright © 2017 John Wiley & Sons, Ltd.     

Dynamics and stability of turbocharger rotors

The paper discusses the bifurcation and stability behavior of (automotive) turbochargers with full-floating ring bearings. Turbocharger rotors exhibit a highly nonlinear behavior due to the nonlinearities introduced by the floating ring bearings. A flexible multibody model of the rotor/bearing system is presented. Numerical run-up simulations are compared with corresponding test rig measurements. The nonlinear oscillation effects are thoroughly investigated by means of simulated and measured rotor vibrations. The influence of various system parameters on the bifurcation behavior of the rotor/bearing system is analyzed. The article examines rotors supported in full-floating ring bearings with plain circular bearing geometry in the inner and outer oil gap. By recapitulating the well-known oil whirl and oil whip phenomena for single and double oil film bearings, the paper gives an overview on the fundamental dynamic effects occurring in turbocharger systems.     

On the precession of a standing wave in a string with fixed ends

Nonlinear differential equations of motion of a string are derived. In the single-mode approximation, the evolution of a transverse standing wave is studied. The dependence of the precession velocity and the correction to the vibration frequency on the semiaxes of the ellipse along which the string midpoint moves is determined.     

Solution for plane strain forward and backward extrusions with a fractional reductionR=0.5 by the integartion depending on a parameter

A parameter t is introduced to boundary slip line of rigid regions for plane strain and indirect extrusions with a fractional reduction R=0.5. Integration by substitution has been used along the boundary slip line in order to obtain the extrusion pressure. By the integration depending on a parameter, the following results are obtained, and die pressure is 5.14k for backward extrusion; and pad average pressure is 2.57k for forward extrusion. All the results from this method are the same as those of the conventional solution.     

Static divergence of self-twisting composite rotors

Hydroelastic instabilities, such as static divergence and flutter, are major concerns for the safe operation of next-generation self-twisting composite marine rotors. In this paper, an efficient theoretical model was developed to obtain a first-order estimation of the static divergence speed of such rotors. The model was inspired by classical aeroelasticity theory and furnished with advanced numerical modeling. Its application to the marine environment was illustrated via a self-twisting composite propeller. The methodology is equally applicable to other structures, such as tidal and wind turbines.     

On two classes of precession motions of a gyrostat under the action of potential and gyroscopic forces

We find two new classes of precession motions of a gyrostat with fixed point. The motions are described by the Kirchhoff differential equations. For the first class, the velocities of precession and free rotation are equal and given in the form of a trigonometric polynomial of the first degree in the angle of free rotation. For the second class, the precession and rotation velocities do not coincide and are defined by special functions of the angle of free rotation. These classes are described in terms of new solutions of the Kirchhoff equations.     

On the backward Lamb waves near thickness resonances in anisotropic plates

A closed-form expression for the leading-order dispersion coefficient, describing the trend of Lamb-wave branches at their onset from thickness resonances, is derived for an arbitrary anisotropic plate. The sign of this coefficient and hence of the in-plane group velocity near cutoffs decides the existence or non-existence of the backward Lamb waves without a necessity to calculate the dispersion branches. A link between the near-cutoff dispersion of Lamb waves and the curvature of bulk-wave slowness curves in a sagittal plane is analyzed. It is established that a locally concave slowness curve of a bulk mode entails the backward Lamb waves at the onset of branches emerging from this bulk mode resonances of high enough order. A simple sufficient condition for no backward Lamb waves near the resonances associated with a convex slowness curve is also noted. Two special cases are discussed: the first involves the coupled resonances of degenerate bulk waves, and the second concerns quasi-degenerate resonances which give rise to pairs of dispersion branches with a quasilinear positive and negative onset. Occasions of the backward Lamb waves in isotropic plate materials are tabulated.     

On post-resonance backward whirl in an overhung rotor with snubbing contact

Nonlinear Dynamics - Rotordynamic systems are central to many aerospace and heavy-duty industrial applications. The vibrational response of such systems is usually associated with forward whirl...     

Flow visualization and analysis of aerodynamically detuned supersonic rotors

The effect of aerodynamic detuning on the supersonic steady and unsteady blade passage flow field is experimentally investigated on a free surface water table by means of color Schlieren and shadowgraph flow visualization techniques. Two aerodynamic detuning mechanisms are considered: (1) alternate circumferential spacing of adjacent airfoils; (2) the replacement of alternate airfoils with splitters. The steady flow visualization demonstrates the significant effect of aerodynamic detuning on the passage flow field and, in particular, the shock wave-airfoil surface intersection locations. The unsteady flow visualization studies show the importance of the interblade phase angle. A mathematical model is also described and utilized to demonstrate the enhanced aeroelastic stability associated with the altered cascade passage shock wave structure due to these aerodynamic detuning mechanisms.List of symbols a dimensionless perturbation sonic velocity - C airfoil chord - I _x mass moment of inertia - k reduced frequency, k = C/2 - K spring constant - M _R dimensionless unsteady aerodynamic moment - M Mach number - P _split split splitter circumferential spacing - P _start splitter leading edge location - R reference full chord airfoil - R _s reference splitter - Sp _chord splitter chord length - u dimensionless perturbation chordwise velocity - v dimensionless perturbation normal velocity - amplitude of oscillation - interblade phase angle - level of aerodynamic detuning - undamped natural torsional frequency - ₀ reference frequency - flutter frequency     

Vibrations of asymmetric rotors supported by asymmetric bearings

Summary In this paper the vibrations of an asymmetric flexible rotor supported by asymmetric bearings is theoretically analyzed by using Galerkin's method and the perturbation method, and numerically calculated. The effects of the asymmetries of the rotor and the bearings and the changes of the main instability regions and the ultraharmonic resonance due to the external and internal dampings are investigated. The experimental tests are performed on a smaller laboratory model in order to verify the validity of the theoretical results.The following results are obtained; the instability regions divide into two ones by the lack of the symmetries in the rotor and the bearings. The ultraharmonic resonances appear at fractional values of the main critical speed. The character of the internal damping is changed by the magnitude of the asymmetries of the rotor and the bearings.

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Übersicht Es werden die Schwingungen eines unsymmetrischen Rotors in unsymmetrischen Lagern analysiert. Dabei wird sowohl das Galerkin-Verfahren als auch eine Störungs-Methode angewendet. Untersucht werden die durch die Unsymmetrien von Rotor und Lagerung entstehenden Effekte sowie die durch äußere und innere Dämpfung entstehenden Änderungen der wichtigsten Instabilitätsbereiche und der ultraharmonischen Resonanzen. Zur Stützung der theoretischen Ergebnisse wurden Versuche an einem Laboratoriumsmodell durchgeführt.Die wichtigsten Ergebnisse sind folgende: Die Instabilitätsbereiche werden durch die Unsymmetrie von Rotor und Lagerung aufgespalten; ultraharmonische Resonanzen treten bei gebroochenen Werten der Hauptkritischen auf; der Charakter der inneren Dämpfung wird durch die Größe der Unsymmetrien von Rotor und Lagerung verändert.

     

Conditions for noncircular whirling of nonlinear isotropic rotors

Nonlinear rotors are often considered as potential sources of chaotic vibrations. The aim of the present paper is that of studying in detail the behaviour of a nonlinear isotropic Jeffcott rotor, representing the simplest nonlinear rotor. The restoring and damping forces have been expanded in Taylor series obtaining a Duffing-type equation. The isotropic nature of the system allows circular whirling to be a solution at all rotational speeds. However there are ranges of rotational speed in which this solution is unstable and other, more complicated, solutions exist.The conditions for stability of circular whirling are first studied from closed form solutions of the mathematical model and then the conditions for the existence of solutions of other type are studied by numerical experimentation. Although attractors of the limit cycle type are often found, chaotic attractors were identified only in few very particular cases. An attractor supposedly of the last type reported in the literature was found, after a detailed analysis, to be related to a nonchaotic polyharmonic solution.As the typical unbalance response of isotropic nonlinear rotors has been shown to be a synchronous circular whirling motion, the convergence characteristics of Newton-Raphson algorithm applied to the solution of the set of nonlinear algebraic equations obtained from the differential equations of motion are studied in some detail. c damping coefficient i imaginaty unit (i=% MathType!MTEF!2!1!+-% feaafiart1ev1aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbqfgBHr% xAU9gimLMBVrxEWvgarmWu51MyVXgaruWqVvNCPvMCG4uz3bqefqvA% Tv2CG4uz3bIuV1wyUbqee0evGueE0jxyaibaieYlf9irVeeu0dXdh9% vqqj-hEeeu0xXdbba9frFf0-OqFfea0dXdd9vqaq-JfrVkFHe9pgea% 0dXdar-Jb9hs0dXdbPYxe9vr0-vr0-vqpWqaaeaabiGaciaacaqabe% aadaabauaaaOqaamaakaaabaGaeyOeI0IaaGymaaWcbeaaaaa!3E66!\[\sqrt { - 1}\]) k stiffness m mass t time x _istate variables i=1, 4 z complex co-ordinate (z=x+iy)[J] Jacobian matrix Oxyz inertial co-ordinate frame Oz rotating co-ordinate frame perturbation term eccentricity complex co-ordinate (=+i) system eigenvalues nonlinearity parameter nondimensional time phase spin speed u nonrotating t rotating0 amplitude t nondimensional termsNomenclature