Transonic flow analysis for rotors. Download PDF EPUB FB2
Transonic flow analysis for rotors. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.: For sale by the National Technical Information Service], (OCoLC) Material Type: Government publication, National government publication: Document Type: Book.
Get this from a library. Transonic flow analysis for rotors. Part 3, Three-dimensional, quasi-steady, Euler calculation. [I-Chung Chang; United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.]. Abstract. The fact that helicopter rotors encounter transonic aerodynamic flow problems has been recognised for several years, and with this realisation there has been considerable activity in recent years in the study of ways of improving rotor performance through blade section and tip design [1–12].Cited by: 1.
Due to the transonic tandem rotor requiring a high stall margin, Appl. Sci. 10, 7 of 13 the rotor tip element needs to operate in a deep choke point, which makes the shock position move. The paper describes the flow conditions found inside an optimized transonic, high pressure ratio centrifugal compressor rotor operated with a rotor tip speed of m/s.
The rotor was coupled with a vaned diffuser of rather small exit radius ratio. Measurements and calculations were carried out on. COMPUTATIONAL ANALYSIS OF FLOW THROUGH A TRANSONIC COMPRESSOR ROTOR Nikolaus J.
Bochette Ensign, United States Navy B.S., United States Naval Academy, Submitted in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE IN MECHANICAL ENGINEERING from the NAVAL POSTGRADUATE SCHOOL September Download Citation | Computational Analysis of Flow Through a Transonic Compressor Rotor | As the United States Navy prepares to field a single engine jet, the FC Joint Strike Fighter, it is.
Transonic rotor analyses use finite-difference Transonic flow analysis for rotors. book to solve the nonlinear flow equation. The rotor wake is a factor in almost all helicopter problems.
A major issue in advanced aerodynamic methods is how the wake can be included. Unsteady transonic aerodynamics is a field with many differences from its counterpart, steady aerodynamics.
The first volume of its kind, this text presents eight chapters and includes more than references and figures. Transonic ® offers several measurement solutions for the surgical suite including: Intraoperative volume flow through vessels and grafts during a wide range of surgeries including CABG, transplant and EC-IC bypass.
Non-invasive volume flow measurements through tubing used. This is a transonic flow case for which experimental results are available in the literature to compare .At inflow Mach number of and angle of attack of degrees, the adapted meshes and Mach number contours for levels 2 and 3 are shown in Figure 3, along with the initial mesh increased sharpness of the shock regions is evident from the results.
The effect of a single circumferential casing groove on the stability enhancement of two different transonic compressors has been examined with CFD analysis. The differences in flow field and stall inception mechanism between two rotors are presented with principal focus on passage blockage and tip leakage flow behavior.
Computational analysis has been conducted on the NASA Rotor 37 transonic compressor with various tip clearance gap heights.
Using steady rotor-only analysis, the change in overall performance, basic flow characteristics, and near-casing phenomena have been carefully observed. Single-Passage Analysis of Unsteady Flows Around Vibrating Blades of a Transonic Fan Under Inlet Distortion 9 April | Journal of Turbomachinery, Vol.No.
2 Transonic Rotor/Stator Interaction Using a 3-D Linearised Unsteady Viscous Flow Model. The interferogram in Fig. a shows a transonic interaction with shock-induced separation taking place in a channel, Fig. b giving an interpretative sketch of the flow field.
Boundary layer separation induces an oblique shock (C 1) after which the flow is still shock (C 1) meets the normal shock (C 3), cause of separation, at the point I, giving an interference. An in-depth analysis of three-dimensional flow structures reveals three features: (1) there exists an interface between the incoming main flow and the tip leakage flow, (2) in this rotor the tip leakage flows along the blade chord can be divided into at least two parts according to the blade loading distribution, and (3) each part plays a.
To focus on current ruggedization issues for transonic blading (e.g. bird, ice ingestion), detailed comparison of test data and analysis to characterize the aerodynamic flow details responsible for the measured performance differences was confined to the two rotors with the most forward location of maximum thickness.
Performance of Single-stage Axial-flow Transonic Compressor with Rotor and Stator Aspect Ratios of andRespectively, and with Design Pressure Ration of Volume of NASA technical paper: Author: Lonnie Reid: Publisher: National Aeronautics and Space Administration, Scientific and Technical Information Office, Original from.
The aerodynamics about rotors are very complex, encompassing subsonic to transonic flow with unsteady, stalled behavior and 3D effects. CA treats aerodynamics as separated into local and global flows.
Semi-empirical models of dynamic stall were created in the s–s for modeling unsteady local aerodynamics, including stalled flow. W.H. Mason, Configuration Aerodynamics 3/10/06 flow code known as FLO These were the first truly accurate and useful transonic airfoil analysis codes.
Holst has published a survey describing current full potential methods The next logical development was to add viscous effects to the inviscid calculations, and to.
Masaki, D, & Kaji, S. "Numerical Analysis of Transonic Compressor Rotor Flow Near Stall Points." Proceedings of the ASME International Gas Turbine and Aeroengine Congress and Exhibition.
Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. Orlando, Florida, USA. June 2–5, VT03A ASME. The analytical design and experimental test of a single-stage transonic axial-flow compressor are described.
This design is the baseline of a compressor design study in which several blade design parameters have been systematically varied to determine their independent effects on. Effects of axial and tangential blade curvature were separately analyzed.
A commercial CFD package which solves the Reynolds-average Navier-Stokes equations was used to compute the complex flow field of transonic compressor rotors. The code was validated against NASA Rotor 37. The rig test confirmed the numerical assessment of the effects of aerodynamic sweep on the low-aspect-ratio, high-through-flow, transonic compressor rotor.
Detailed analyses of the measured and calculated flow fields indicate that two mechanisms are primarily responsible for the differences in aerodynamic performance among these rotors. Song, W.P., Han, Z.H., Qiao, Z.D.: Computational aeroacoustic prediction of transonic rotor noise based on Reynolds-Averaged Navier-Stokes flow simulation.
In: 25th Congress of the International Council of the Aeronautical Sciences, Paper ICASHamburg () Google Scholar. Moore, R., and Reid, L.,“Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of andRespectively.
Three-dimensional unsteady Navier—Stokes analysis of stator—rotor interaction in axial-flow turbines Show all authors.
L He 1. Flow analysis. Trans. Investigation of the unsteady flow of a transonic compressor using the nonlinear harmonic method. The performance deterioration of a high-speed axial compressor rotor due to surface roughness and airfoil thickness variations is reported.
A mm ( in.) thick rough coating with a surface finish of – rms μm (– rms μin.) is applied to the pressure and suction surface of the rotor blades. Transonic (or transsonic) flight is flying at or near the speed of sound ( m/s; 1, km/h; 1, ft/s; mph; kn, at sea level under average conditions), relative to the air through which the vehicle is traveling.
A typical convention used in aeronautics is to define transonic flight as speeds in the range of Mach to (–1, km/h (– mph) at sea level). The code has been used to study the complex flow fields of a transonic axial compressor rotor (i.e., NASA Rotor 37) and a subsonic centrifugal compressor impeller (i.e., the backswept impeller of Krain, first reported in ).
Transonic flow analysis for rotors. (Washington, D.C.: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va.: For sale by the National Technical Information Service, ), by I-Chung Chang and United States.
National Aeronautics and Space Administration.A calculation system has been set up to predict both the internal flow field and the overall performance of a transonic compressor blade row.
The system iterates between an inviscid-viscous time-marching blade-to-blade (S1) treatment and a streamline curvature throughflow calculation for the pitchwise-averaged flow in the meridional plane (S2).This paper analyses the flow in a transonic turbine stage, using numerical results from a full 3D Navier-Stokes computation over the whole stage.
This analysis, based on the combination of time and space Fourier transforms, points out how a spatio-temporal periodicity phenomenon is involved in the so-called stator-rotor interaction.