3 edition of **Viscous three-dimensional calculations of transonic fan performance** found in the catalog.

Viscous three-dimensional calculations of transonic fan performance

- 231 Want to read
- 5 Currently reading

Published
**1991**
by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va
.

Written in English

- Navier-Stokes equations.,
- Turbomachines.

**Edition Notes**

Other titles | Viscous three dimensional calculations of transonic fan performance. |

Statement | Rodrick V. Chima. |

Series | NASA technical memorandum -- 103800. |

Contributions | United States. National Aeronautics and Space Administration. |

The Physical Object | |
---|---|

Format | Microform |

Pagination | 1 v. |

ID Numbers | |

Open Library | OL18054366M |

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Frontiers of Fluid Mechanics documents the proceedings of the Beijing International Conference on Fluid Mechanics, held in Beijing, People's Republic of China, July The aims of the conference were to provide a forum for a cross-sectional review of the state-of-the-art and new advances in various branches of fluid mechanics, and to.

A theory for base pressures in transonic and supersonic flow / (Urbana, Ill.: Mechanical Engineering Dept., Univ. of Illinois, May ), by Helmut Hans Korst, M. E. Childs, R. H. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at . The proper orthogonal decomposition (POD) technique is applied in the frequency domain to obtain a reduced-order model of the unsteady flow in a transonic turbomachinery cascade of oscillating blades. The flow is described by a inviscid—viscous model, i.e. a full potential equation outer flow model and an integral equation boundary layer by:

In this paper, a computational model for predicting the aerodynamic behavior of wind turbine wakes and blades subjected to unsteady motions and viscous effects is presented. The model is based on a three‐dimensional panel method using a surface distribution of quadrilateral sources and doublets, which is coupled to a viscous boundary layer. Alex K. H. Lee and M. Damodaran, "Comparison of Artificial Dissipation Models for Three-dimensional Transonic Flow Calculations", Proceedings of the 6 th Asian Congress on Fluid Mechanics, Singapore, Volume 2, pp. , Ed. Y. T. Chew and C. P. Tso, May ,

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Get this from a library. Viscous three-dimensional calculations of transonic fan performance. [Rodrick V Chima; United States. National Aeronautics and Space Administration.]. A three-dimensional viscous solver has been used to model the flow in the stator of a highly loaded single-stage transonic fan.

The fan has a very high level of aerodynamic loading at the hub, which results in a severe hub endwall by: 3. The code is validated by studying the NASA rotor 67 transonic fan. This fan has important viscous and three-dimensional effects and experiments are available in a wide range of flow rates from the maximum one to near stall.

Moreover, this. The aerodynamics of transonic fans is discussed with emphasis on the use of three-dimensional design techniques, such as blade sweep and lean, to improve their performance.

Chima, R. V., "Viscous Three-Dimensional Calculations of Transonic Fan Performance," in CFD Techniques for Propulsion Applications, AGARD Conference Proceedings No. CP, AGARD, Neuilly-Sur-Seine, France, Feb. pp to Also NASA TM Experimental measurements in the inlet of a transonic turbine blade cascade showed unacceptable pitchwise flow nonuniformity.

A three-dimensional, Navier–Stokes computational fluid dynamics (CFD) analysis of the imbedded bellmouth inlet in the facility was performed to identify and eliminate the source of the flow by: 7.

Viscous Three-Dimensional Simulation of Transonic Compressor Stage on Parallel Hardware Article in Journal of Propulsion and Power 16(3) May with 6 Reads How we measure 'reads'. An experimental Investigation of the three-dimensional flow field through a low aspect ratio, transonic, axial-flow fan rotor has been conducted using an advanced laser anemometer (LA) system.

Laser velodmeter measurements of the rotor flow field at the design operating speed and over a. Chima, R. “Viscous Three-Dimensional Calculations of Transonic Fan Performance”, CFD Techniques for Propulsion Applications, AGARD Conference Proceedings No.

CP, AGARD, Neuilly-Sur-Seine, France, Februarypp. 21 – 1 to 21 – 19 (also NASA TM). Google ScholarCited by: The Simulation of Three-Dimensional Viscous Flow in Turbomachinery Geometries Using a Solution-Adaptative Unstructured Mesh Methodology,Jour. of Viscous Three-Dimensional Calculations of Transonic Fan Performance,AGARD CPPa Multigrid Algorithms for Compressible Flow Calculations,Lecture Notes in Mathematics, Author: V.

Couaillier. @article{osti_, title = {Effects of inlet distortion on the flow field in a transonic compressor rotor}, author = {Hah, C and Rabe, D C and Sullivan, T J and Wadia, A R}, abstractNote = {The effects of circumferential distortions in inlet total pressure on the flow field in a low-aspect-ratio, high-speed, high-pressure-ratio, transonic compressor rotor are investigated in this paper.

the stator in order to determine global performance of the fan in terms of efﬁciency and total pressure ratio as seen in Figure 4. Rotor diameter m Hub to tip ratio Shaft speed at design point 1/min Blade tip speed m/s Relative Mach number at.

A quasi-three-dimensional inviscid-viscous coupled approached has been developed for unsteady flows around oscillating blades, as described in Part 1. To validate this method, calculations for several steady and unsteady flow cases with strong inviscid-viscous interactions are performed, and the.

Also NASA TM Chima, R. V., “Viscous Three-Dimensional Calculations of Transonic Fan Performance,” in CFD Techniques for Propulsion Applications,” AGARD Conference Proceedings No. CP, AGARD, Neuilly-Sur-Seine, France, Feb.

pp. 21. of a transonic fan stage that consists of a highly loaded rotor along with a tandem stator. Three dimensional, linearized Navier-Stokes flow solver TRACE is used to numerically analyse the flutter stability of the fan.

The linear flow solver enables the modeling of a single blade passage to simulate the desired inter-blade phase Size: KB.

Transition to turbulence in plane channel flow occurs even for conditions under which modes of the linearized dynamical system associated with the flow are stable.

In this paper an attempt is made to understand this phenomena by finding the linear three‐dimensional perturbations that gain the most energy in a given time period. A complete set of perturbations, ordered by energy growth, is Cited by: Abstract. This study investigates the role of compressibility on the amplification of instability and on the establishment of three-dimensional motion in the viscous transonic flow around a wing of constant section, NACA, at zero : A.

Bouhadji, M. Braza. However, the leading edges of transonic fan blades are three-dimensional as shown in Fig. 2(b). ¦Ás (a) (b) Fig Difference between (a) wing and (b)blade leading edge The design problem concerns the design of the leading edge curve such that the adiabatic efficiency of a transonic fan’sFile Size: KB.

the convective and viscous fluxes, and H is the source term vector consisting of non-inertia force due to constant rotation of the system and other external contribution to the conservation law. The turbulence contribution to viscous fluxes is modeled with sev-eral Boussinesq eddy-viscosity models.

For turbomachinery applications, the flow angle. transonic regime. Nadarajah et al. [14] extended their two-dimensional optimum shape design for unsteady ﬂows from a time-accurate scheme to the NLFD approach, in the process, developing the NLFD adjoint equations.

The method was further extended for three-dimensional inviscid ﬂows and presented in [15]. The. Three-Dimensional Supersonic Viscous Flow (AOFA) This program determines the complete viscous and inviscid flow around a body of revolution at a given angle of attack and traveling at supersonic speeds.

The viscous calculations from this program agree with experimental values for surface and pitot pressures and with surface heating rates.

At.Compressor Performance 53 Compressor Performance 54 Compressor Performance 55 Compressor Performance 56 Comparison of Variable Area and Regular Turbines 58 Comparison of Variable Area and Regular Turbines 59 Variable Area Turbine Performance 60 Variable Area Turbine Performance.

61 Viscous Engine 62 Viscosity, n is the frictional force per unit area per unit velocity gradient. Dimensions ;Force =F = MLT^[-2] Area =A =L^2 velocity gradient, G = velocity/ unit length= [L/T]/L= [1/T]=T^[-1], put them all together n = F/[ A. G] = MLT^[-2]/[L^.