1 edition of Controlled diffusion compressor blade wake measurements found in the catalog.
Controlled diffusion compressor blade wake measurements
John W. Jr Dreon
Written in English
|The Physical Object|
|Number of Pages||138|
and Testing of an Axial-Flow Compressor Different Blade Profiles in Each Stage A. D. S. CARTER, R. C. TURNER, D. W. SPARKES and R. A. BURROWS COMMUNICATED BY THE DIRECToR-GENERAL OF SCIENTIFIC RESEARCH (AIR), MINISTRY OF SUPPLY Reports and Memoranda No. 3 18 3" _/Vovemher, 19 5 7File Size: 1MB. Numerical optimization techniques combined with a three-dimensional thin-layer NavierStokes solver are presented to find an optimum shape of a stator blade in an axial compressor through calculations of single stage rotor-stator flow, Governing differential equations are discretized using an explicit finite difference method and solved by a multi-stage Runge-Kutta by:
In the experimental work, a linear compressor cascade test section was installed in an open loop wind tunnel. The experimental data was acquired for a Reynolds number of × 10 5 based on the blade chord and the inlet flow conditions. The flow field characteristics in blade passage including 3-D flow velocity and velocity magnitude have been measured by using calibrated five and seven-hole Author: Saeed A. El-Shahat, Hesham M. El-Batsh, Ali M. A. Attia, Guojun Li, Lei Fu. of the compressor for radial blades and leaned blades with states of the prewhirl are also plotted in Figure 1. A.H. Zahed and N.N. Bayomi / ISESCO Journal of Science and Technology - Volume 1 0.
direction. The axial-ﬂ ow compressor compresses its working ﬂ uid by ﬁ rst accelerating the ﬂ uid and then diffusing it to obtain a pressure increase. The ﬂ uid is accelerated by a row of rotating airfoils (blades) called the rotor, and then diffused in a row of stationary blades (the stator). The diffusion. A 'read' is counted each time someone views a publication summary (such as the title, abstract, and list of authors), clicks on a figure, or views or downloads the full-text.
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The abstract provided by the Pentagon follows: An investigation of vortex shedding downstream of a cascade of second-generation, controlled-diffusion, compressor stator blades, at off-design inlet-flow angles of 31, 33 and 35 degrees and Reynolds numbers, based on chord length, of ,andis : Peter J.
Brown. The capabilities of a stator blade row having control led-diffusion (CD) blade sections were compared with the capabilities of a stator blade row having double-circular-arc (DCA) blade sections. A CD stator with the same chord length but half the blades of File Size: 1MB.
The results of two component laser-Doppler velocimeter (LDV) surveys made in the near wake (to one fifth chord) of a controlled diffusion (CD) compressor blade in a large-scale cascade wind tunnel are reported.
The measurements were made at three positive incidence angles from near design to angles thought to approach by: Approved for public release; distribution is unlimitedA controlled-diffusion compressor Controlled diffusion compressor blade wake measurements book blade-element design was re-tested in an academic cascade wind tunnel to obtain data with which to assess viscous computational prediction methods.
Tests were conducted near design and toward stall conditions at Mach and Reynolds number of Author: Jr. John W. Dreon. Wake Measurements and Loss Evaluation in a Controlled Diffusion Compressor Cascade.
of a controlled diffusion (CD) compressor blade in a large-scale cascade wind tunnel are reported. The measurements were made at three positive incidence angles from near design to angles thought to approach stall.
Despite the precision obtained in the Cited by: The test blades were of controlled-diffusion design with a solidity ofand stalling occurred at 10 deg of incidence above the design inlet air angle.
All measurements were taken at a flow Reynolds number, based on chord length, of ,Cited by: 3. A detailed investigation of the three-dimensional flow in a cascade of second-generation controlled-diffusion compressor stator blades, at off-design inlet-flow angle, is : Kevin D.
Fitzgerald. AUTOMATED DESIGN OF CONTROLLED DIFFUSION BLADES h h % w I Jos6 M. Sanz National Aeronautics and Space Administration Lewi s Research Center Cleveland, Ohio SUMMARY A numerical automation procedure has been developed to be used in conjunc- tion with an inverse hodograph method for the design of controlled diffusion Size: KB.
One aspect of this project was the verification of the controlled diffusion concept for axial compressor blade design, in order to demonstrate the capabilities of some recent research results which are now available for industrial application.
The stator blades of the axial compressor section were first designed using NACA 65 by: It has been found that the nanosecond plasma actuation can control the compressor airfoil boundary layer flow through inducing two types of spanwise vortexes.
Results of this paper provide the basis of developing plasma actuation based flow control technique to control compressor airfoil boundary layer flow actively. : Haideng Zhang, Yun Wu, Yinghong Li.
A detailed investigation of the three-dimensional flow in a cascade of second-generation controlled-diffusion compressor stator blades, at off-design inlet-flow angle, is reported. Both a elliptic and a circular leading edge were tested on a controlled diffusion aerofoil stator blade.
Experiments were undertaken on the stator suction surface; these included hotwire boundary-layer traverses, surface hotfilm measurements, and high resolution leading-edge pressure by: Measurements have been made of the boundary layers and wakes about a highly loaded, double-clrcular-arc compressor blade in cascade.
These laser Doppler velocimetry measurements have yielded a very detailed and precise data base with which to test the application of viscous computational codes to Size: 5MB. Evaluation of Compressor Blading With Blade End Slots and Full-Span Slots in a Highly Loaded Compressor Cascade 30 October | Journal of Turbomachinery, Vol.No.
12 Numerical Investigations on Oscillating Aspiration Control in High-Load Compressor CascadesCited by: Approved for public release, distribution unlimitedThe flow around second generation controlled-diffusion compressor blades in cascade at stall was examined through the use of a Particle Image Velocimeter (PIV).
This examination was conducted from the trailing edge of the blade well into the wake Author: Robert C. Quesenbury. Lieblein () developed a correlation between local diffusion factor and the wake momentum thickness to chord ratio, θ 2 /l, at the reference incidence (midpoint of working range) for a range of compressor blades.
The wake momentum thickness, with the parameters of the flow model in Figureis defined as. Blade surface pressure measurements were obtained using instrumented blades, from which coefficients of pressure were calculated. Laser Doppler velocimetry (LDV) was used to characterize the off-design flow upstream, in the passage between two blades, in the boundary layer on the suction side of the blades, and in the wake : David G.
Schnorenberg. The new advanced compressor rotors have fewer blades with higher loadings, and the blades are thinner, larger, and are designed using advanced radial equilibrium theory, which creates three-dimensional and controlled diffusion shaped airfoils (3D/CDA), with smaller clearances and higher loading per stage.
where n≈ for compressor cascades and n≈1 for compressor inlet guide vanes (these can be considered as turbine blades because they accelerate the flow). Equation () is now widely referred to as Carter’s rule.
It demonstrates that the deviation increases with pitch–chord ratio and blade camber. The value of m depends upon the precise shape of the camber line and the blade stagger.
Crack propagation analysis of compressor blade subjected to resonant vibrations Figure 1: View of blade damaged by foreign object (a), dimension of the investigated blade with v-noth (b). 2 Experimental investigations In investigated blade a V-notch presented in Fig.
2 was created. The depth of notch was about mm whereas the apex angle 90 Cited by: 5. SUMMARY The effects of diffusion factor, aspect ratio, and solidity on rotor and stage per- formance have been evaluated for 14 subsonic compressor middle stages with a hub-tip ratio of and a design tip speed of meters per rotor efficiencies ranged from to Peak stage efficiencies ranged from toand.Design Optimization of Axial Flow Compressor Blades With Three-Dimensional Navier-Stokes Solver Article (PDF Available) in Journal of Mechanical Science and Technology 14(9) April.Abstract.
Approved for public release, distribution unlimitedAn investigation of vortex shedding downstream of a cascade of second-generation, controlled-diffusion, compressor stator blades, at off-design inlet-flow angles of 31, 33 and 35 degrees and Reynolds numbers, based on chord length, of ,andis : Peter J.