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Wednesday, April 22, 2020 | History

2 edition of Effect of stator blade orientation on the performance of an axial flow compressor found in the catalog.

Effect of stator blade orientation on the performance of an axial flow compressor

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Published by Naval Postgraduate School in Monterey, California .
Written in English

    Subjects:
  • Aeronautics

  • Edition Notes

    ContributionsNaval Postgraduate School (U.S.)
    The Physical Object
    Pagination1 v. :
    ID Numbers
    Open LibraryOL25200388M

    Figure shows some examples of blade damage to an axial-flow engine. The descriptions and possible causes of blade damage are given in Figure Corrosion pitting is not considered serious on the compressor stator vanes of axial-flow engines if the pitting is within the allowed tolerance. A turbine (from the Latin turbo, a vortex, related to the Greek τύρβη, tyrbē, meaning "turbulence") is a rotary mechanical device that extracts energy from a fluid flow and converts it into useful work produced by a turbine can be used for generating electrical power when combined with a generator. A turbine is a turbomachine with at least one moving part called a rotor .


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Effect of stator blade orientation on the performance of an axial flow compressor by Bruce Cameron Marshall Download PDF EPUB FB2

Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection Effect of stator blade orientation on the performance of an axial flow compressor. Variability in stator vanes is a widely used technique to improve the stability and efficiency of axial flow compressor in gas turbine engines.

Most of the modern aircraft jet engines use variable stator vanes in both low pressure and high pressure compressors primarily for off-design : Kirubakaran Purushothaman, N.

Naveen Kumar, Vidyadheesh Pandurangi, Ajay Pratap. Measurement were made on a 3-stage axial flow compressor at the Naval Postgraduate School at six stator stagger angles between degrees and degrees for a fixed orientation of the rotor blades.

Maximum efficiency and pressure ratio were measured at a stator stagger angle of : Bruce Cameron Marshall. Groups of 5 8 blades are then assembled into vane-packs by welding them together at the casing. The hub platforms are not welded together to allow for the effects of vibration and thermal expansion.

This results in an axial inter-platform gap at the hub between each blade row, which is estimated to up to 1% of pitch. Also, the effect of various stator stagger angles on the compressor performance and especially on the compressor surge margin has been discussed.

To validate the CFD method, another known compressor stage is presented and its performance is numerically investigated and the results are compared with available experimental by: 2.

The Effect of Rotor Blade Thickness and Surface Finish on the Performance of a Small Axial Flow Turbine Richard J. Roel,ke National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio and Jeffrey E. Haas Propulsion Laboratory AVRADCOM Research and Technology Laboratories Lewis Research Center Cleveland, Ohio   Moore R D, Reid L () Performance of single-stage axial flow transonic compressor with rotor and stator aspect ratios of andrespectively, and with design pressure ratio ofNASA TP Google ScholarAuthor: N.-Z.

Huang, X. Zhao, Y.-H. Zhang. A theoretical analysis of turbine performance deterioration with the presence of particulate flow in a two dimensional axial flow compressor cascade, is reported, and includes the inelastic.

The object of the present work is an experimental study of the effect of blade aspeot ratio on the performance of axial flow compressors.

In order to do this a single stage, low speed, large axial flow compressor was used. The stage consisted of three blade rows (i.g.v., rotor and stator File Size: 2MB. In a two-part paper, key computed results from a set of first-of-a-kind numerical simulations on the unsteady interaction of axial compressor stator with upstream rotor wakes and tip leakage vortices are employed to elucidate their impact on the time-averaged performance of the by: Research in axial compressors involves the inter effect of one blade on the other; thus, several blades are placed in a row to simulate a compressor rotor or stator.

Such a row is called a cascade. When discussing blades, all angles which describe the blade and its orientation are measured with respect to the shaft (Z axis) of the compressor. Vol. 19 No. 4 CHINESE JOURNAL OF AERONAUTICS November Effect of Turning Angle on Flow Field Performance of Linear Bowed Stator in Compressor at Low Mach Number 1 ZHANG Yong-jun, CHEN Fu, FENG Guo-tai, SU Jie-xian (Energy Science and Engineering School, Harbin Institute of Technology, Harbin Ä‘China) AbstractÄŸA comparison of Cited by: 6.

Stator blades in turbine engines. the reason for having stators is to straighten or align the airflow ready for the next set of rotating blades, be they compressor or turbine.

With reference to the gaps around the base of the disks, there are seals on some engines to prevent flow to the lower pressure stages. The overall effect is a. Axial-Flow Compressors.

An axial-flow compressor compresses its working fluid by first accelerating the fluid and then diffusing it to obtain a pressure increase (Chapter 7). The fluid is accelerated by a row of rotating airfoils or blades (the rotor) and diffused by a row of stationary blades (the stator).

Compressor blades continuously pass through the wakes of upstream blades that introduce unsteady flow variations. Compressor designers must rely on wind tunnel testing and sophisticated computational models to determine the performance of an axial compressor.

The performance is characterized by the pressure ratio across the compressor CPR, the. Report presenting an investigation to study the influence of high relative inlet Mach number on the performance of a highly loaded blade row.

Twenty-nine rotor blades were installed in a compressor rotor and static and total pressure, total temperature, and flow-angle surveys were taken upstream and downstream of the : Paul D. Dugan, John J.

Mahoney, William A. Benser. Flow separation occur on the pressure side of the blade. Negative stall is negligible compared to the positive stall because flow separation is least likely to occur on the pressure side of the blade. In a multi-stage compressor, at the high pressure stages, axial velocity is very small.

Axial-Flow Compressor By D. KILPATRICK, A. CARTER and L. O'NEILL COMMUNICATED BY THE DIRECTOR-GENERAL OF SCIENTIFIC RESEARCH (AIR) MINISTRY OF SUPPLY Reports and Memoranda No. 3z8± * January, z Summary. A detailed investigation of the stresses in the early stator blade rows of an axial-flow compressor,File Size: 3MB.

Past researches have studied the stator blade guide vane angle implementation respective to the rotor blade angle. And outlet guide vane is recommended to encounter the air swirl problem occurs in the axial flow fan compared to inlet guide vane.

This paper presents an investigation on the distance between rotor-stator for an outlet guide vane with fixed stator : Kannan M. Munisamy, Ramies Govindasamy, Savithry K. Thangaraju. In compressor working, unsteady aerodynamic load induced by the interaction of stator-rotor blade rows is the main vibration source of blade high cycle fatigue.

It has a direct influence on fatigue strength of compressor blades. Further research on unsteady aerodynamic load has very important significance for improving the service life and reliability of compressor by: 1. The effects of tip clearance on the overall and blade- element performance of an axial-flow transonic fan stage are presented.

The centimeter-diameter fan was tested at four tip clearances (nonrotating) from to Size: 6MB. overall performance. The secondary flows have noxious effects on the axial flow compressor due to extract energy from the working fluid and increase the flow instability.

Therefore, controlling secondary flows will extremely improve the aerodynamic performance of the compressor. The components. Stator blades in the compressor section of an axial-flow turbine engine decrease the air velocity and prevent swirling A gas turbine engine comprises which three main sections.

This book provides a thorough description of an aerodynamic design and analysis systems for Axial-Flow Compressors.

It describes the basic fluid dynamic and thermodynamic principles, empirical models and numerical methods used for the full range of procedures and analytical tools that an engineer needs for virtually any tupe of Axial-Flow Compressor, aerodynamic design.

This book provides a thorough description of an aerodynamic design and analysis systems for Axial-Flow Compressors.

It describes the basic fluid dynamic and thermodynamic principles, empirical models and numerical methods used for the full range of procedures and analytical tools that an engineer needs for virtually any type of Axial-Flow Compressor, aerodynamic design Cited by: 87 () - (1) In a turbine engine axial-flow compressor, each consecutive pair of rotor and stator blades constitutes a pressure stage.(2) In a turbine engine axial-flow compressor, the number of rows of stages is determined by the amount of air and total pressure rise ing the above statements.

Experiments were performed on a low-speed multistage axial-flow compressor to assess the effects of shrouded stator cavity flows on aerodynamic performance. Five configurations, which involved changes in seal-tooth leakage rates and/or elimination of the shrouded stator Cited by: Experiments were performed on a low-speed multistage axial-flow compressor to assess the effects of shrouded stator cavity flows on aerodynamic performance.

Five configurations, which involved systematic changes in seal-tooth leakage rates and/or elimination of the shrouded stator cavities, were tested. In addition, I have to simulate the flow through the fan + compressor and bypass as well.

Of course, the fan blades, the splitter (bypass flow) geometry are larger than the compressor blades. And now I am struggeling with the meshing of all components. I have meshed all blades with TurboGrid and in TG they look fine for me.

Axial flow compressors produce a continuous flow of compressed gas, and have the benefits of high efficiency and large mass flow rate, particularly in relation to their size and cross-section.

They do, however, require several rows of airfoils to achieve a large pressure rise, making them complex and expensive relative to other designs (e.g Author: Rrhb. By tangential curvature of the stacking line of the profiles guide vanes can be designed, which have on both ends an obtuse angle between suction side and sidewall.

This configuration, according to literature, is capable of reducing secondary loss. This type of vanes develops considerable radial components of the blade force and effects a displacement of the meridional flow Author: Tzong-Hann Shieh.

The blade size reduction is to achieve large pressure pressure is proportional to the flow compressors produce a continuous decelerating flow of compressed gas,for high efficiency and large mass flow rate, particularly in relation to their casing around these blades also -pressure gas enters a turbine, where it expands down.

Performance Enhancement of a High Turning Axial Compressor Stator Blade Cascade Through End Wall Boundary Layer Suction Naresh P., *Nagpurwala Q.H. and Mahesh K. Varpe Department of Automotive and Aeronautical Engineering, Faculty of Engineering and Technology, Ramaiah University of Applied Sciences, Bengaluru The job of the stators is to increase pressure and keep the flow from spiraling around the axis by bringing the flow back parallel to the axis.

The stator removes swirl from the flow, but it is not a moving blade row and thus cannot add any net en. Vane clocking effects have been studied in great detail in this compressor, with a large focus on the effect of vane clocking on stator loss and thus stage performance [8, 16].

With similar vane counts for the IGV, S1, and S2, the effects of vane clocking can be isolated on the embedded stage by clocking S1 with respect to by: 2. 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 {micro}m ( rms {micro}in.) is applied to the pressure and suction surface of the rotor blades. Design of a rotor blade for axial flow turbomachine. Objective: Become familiar with basic design aspects of an axial flow rotor section, and perform preliminary study of the section in a stage (stator/rotor) Design: 1 From the table of X and Y co-ordinates around the blade profile (rotor) given below in non-dimensioned form (against chord, C), plot the generated blade.

Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of andrespectively, and with design pressure ration of / ([Washington, D.C.:] National Aeronautics and Space Administration, Scientific and Technical Information Office, ), by Lonnie Reid and Royce D.

Moore (page images at. The flow through a compressor is quite complex and three dimensional, but there is a simple way of looking at it: There are two main components of an axial flow compressor: the rotor and the stator.

These are essentially both discs with aerofoil. A blade for an axial flow machine having a pressure surface, suction surface and trailing edge. The blade has a cross-sectional aerofoil profile including: a region of maximum curvature corresponding to the trailing edge of the blade and defining a trailing edge radius of curvature r; a trailing edge region extending from the trailing edge and having a chordwise extent equal to Author: William J.

Brown, Christopher R. Hall, Anthony M. Dickens, James V. Taylor. AbstractIn this study, the thickness of water film, which is frequently formed on compressor blade surface, was investigated.

Simultaneously, its movement and extra torque demand were provided by a simulation model of the code. Having taken into account the transformation in blade’s profile and the thickness feature of the films, the working medium characteristic transformation in compressor Author: Chunlei Liu, Hai Zhang, Lu Yang, Qun Zheng, Guoqiang Yue.Experimental Investigation of the Effects of a Passing Shock on Compressor Stator Flow Matthew D.

Langford (Abstract) A stator cascade was developed to simulate the flow conditions within a close-stage-spacing transonic axial compressor. Experiments were conducted in a linear transonic blowdown cascade wind tunnel with an inlet Mach number of The basic components of an axial flow compressor are a rotor and stator, the former carrying the moving blades and the latter the stationary rows of blades.

The stationary blades convert the kinetic energy of the fluid into pressure energy, and also redirect the flow into an angle suitable for entry to the next row of moving blades.