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Wednesday, May 6, 2020 | History

1 edition of Progress report - multistage axial compressor program on tip clearance effects found in the catalog.

Progress report - multistage axial compressor program on tip clearance effects

Ian N. Moyle

Progress report - multistage axial compressor program on tip clearance effects

by Ian N. Moyle

  • 66 Want to read
  • 39 Currently reading

Published by Naval Postgraduate School, Available from National Technical Information Service in Monterey, Calif, Springfield, Va .
Written in English


Edition Notes

Other titlesNPS-67-81-01CR.
StatementI. Moyle
ContributionsNaval Postgraduate School (U.S.). Dept. of Aeronautics
The Physical Object
Paginationv, 42 p. :
Number of Pages42
ID Numbers
Open LibraryOL25488084M

  The accurate characterization and simulation of rotor tip clearance flows has received much attention in recent years due to their impact on compressor performance and stability. At NASA Glenn the first known three dimensional digital particle image velocimetry (DPIV) measurements of the tip region of a low speed compressor rotor have been acquired to characterize the behavior of the rotor tip Cited by: Tip clearance of compressor rotor blade is introduced for avoiding friction collision between the moving blade and the casing. Because of the existence of the pressure difference between pressure surfaces and the suction surfaces of the blade, the blending of the leakage flow with the mainstream causes losses, which affects internal flow field and overall performance of the : Yong Lei Qu, Bo Wan, Xiao Meng Pei.

  For the rotor with exit axial width of mm, performance was investigated for tip clearance of , and mm. Results of this simulation at design point showed that the compressor pressure ratio peaked at an area ratio of while the efficiency peaked at Cited by: compressors till now. Ia Iei In this report, the influence of discharge pressure and the effect of working fluid on the four stage reciprocating compressor are conducted by using the original numerical simulation program. The possibility of applying this simulation program to estimate the compressor performance is also verified.

Tip clearance flows in axial flow compressors and pumps (Report) [Rains, Dean A] on *FREE* shipping on qualifying offers. Tip clearance flows in axial flow compressors and pumps (Report)Author: Dean A Rains. Full text of "Calculation of tip clearance effects in a transonic compressor rotor" See other formats / NASA Technical Memorandum Calculation of Tip Clearance Effects in a Transonic Compressor Rotor Rodrick V. Chima Lewis Research Center Cleveland, Ohio Prepared for the 41st Gas Turbine and Aeroengine Congress sponsored by the American Society of Mechanical Engineers .


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Progress report - multistage axial compressor program on tip clearance effects by Ian N. Moyle Download PDF EPUB FB2

Tip clearance has long been known to be a source of losses in axial compressors with cantilevered blades. The reasons for the losses, however, are not well understood and current prac-tice in engine design still requires extensive effort to main-tain constant minimal operating clearances over a wide range of conditions.

This thesis describes the effect of increasing multistage axial compressor rotor blade tip clearance on embedded stage performance and flow structure for clearance-to-span ratios ranging from % to % using steady and unsteady three-dimensional viscous flow multistage computations.

Embedded stage efficiency displays decreased sensitivity as rotor tip clearance increases with two flow : Andrew Koff. ROLE OF TIP CLEARANCE FLOW ON AXIAL COMPRESSOR STABILITY By Huu Duc Vo Abstract An examination of the fluid dynamic phenomena that link tip clearance flow to the formation of short length-scale (spike) rotating stall disturbances has been carried out.

Effect of tip clearance and rotor-stator axial gap on the efficiency of a multistage compressor Article in Applied Thermal Engineering 99 February with Reads How we measure 'reads'. Ct(tip chord), tip clearance 2 with a plain tip of %Ct, and tip clearance 3 with a convex type pinched tip of % Ct aroundtipcenterand%Ct neartherotortipLE/ three tip clearance shapes correspond to different usage in a realistic compressor and are recommended by GE Aviation to study.

2 The NSV Compressor A GE axial compressor. machinery is highly unsteady. Furthermore several technological effects like tip clearances, complexity of the blade shapes, variation of axial distance.

between stator and rotor, seal leakages and cooling holes among others complicate the machine. Therefore the study of a complicated, strongly three. Tip Clearance Effects on Performance of a Centrifugal Compressor S. Swamy1 angadu2 1. Assistant Professor, Department of Mechanical Engineering, GNITS, Hyderabad.

e-mail: [email protected] 2. Professors, Department of Mechanical Engineering, JNTUCE, Anantapur. Abstract-Tip clearance effects on flow field of a low speed centrifugal compressor performance is.

three-stage compressor, considering its natural spatial periodicity. The interest is to analyze multistage effects on performance and aerodynamic stability for three configurations of the same compressor (two sets of tip clearance dimensions and one configuration with a casing treatment).

The Effect of Tip Clearance on Aerodynamic Performance of an Axial Compressor PI Jun *1, LIN Liang 2 Sino-European Institute of Aviation Engineering, Civil Aviation University of. compressor has a high hub tip ratio that reproduces the rear stages of a multi stage compressor.

Compressor. This is shown with the probe assembly mounted on the framework. Outlet Banjo. Collects the air from the last stator and ducts it up through the ceiling of the test cell. Throttle. A pneumatic controlled butterfly valve that enables.

In addition to its effect on compressor stage performance, the change in tip clearance has a more significant impact on stage matching. 9, 10 Therefore, accurate prediction of tip clearance in. Title from cover. This banner text can have markup. web; books; video; audio; software; imagesPages:   Wisler () reported that for a low speed four stage compressor the effect of increasing rotor tip clearance from % to % was to reduce the efficiency by % and the peak pressure rise by.

Tip-Clearance Flow and Losses for an Compressor Blade In the absence of any variation in approach velocity there is no secondary flow and the effects of tip clearance only may be studied.

A theoretical and experimental study is made of the flow over such a split aerofoil placed in a measurements on an axial-flow pump. It may also be File Size: 1MB. Rotor tip clearance height and the associated tip leakage flow have a significant effect on the performance and stability of compressors.

Existing studies considering tip clearance effects on stability have been primarily limited to low-speed compressors, and many of these evaluated single-stage machines, which may not adequately represent stall trends for engine-scale by: 3.

Emphasis is given to tip clearance changes due to changing loading condition and at several compressor operating speeds. Measurements show a tip clearance change approaching mm (% rotor span) when comparing a near-choke operating condition to a Cited by: 9. Abstract-Tip clearance effects on flow field of a low speed centrifugal compressor performance is tested experimentally by using partial shroud (PS) attached to the rotor blade tip at three values of tip clearances i.e.= %, % and % of blade height at trailing edge are examined at three flow coefficients, and The.

Tip clearance effects on flow field of a low speed centrifugal compressor without and with partial shroud (PS) attached to the rotor blade tip at three values of tip clearance, viz.

φ =%, % and % of rotor blade height at the exit at three flow coefficients, namely, φ =, The flow through the tip clearance region of a transonic compressor rotor (NASA rotor 37) was computed and compared to aerodynamic probe and laser anemometer data.

Tip clearance effects were modeled both by gridding the clearance gap and by using Cited by: In the current study, the influence of blade tip clearance in different stages of a three-stage compressor is investigated. Performance diagrams of compressor were verified against experiment when there is no change in the tip clearance, after which the effect of tip clearance for Author: M.

Ostad, R. Kamali. The current study presents the experimental research of various tip geometry designs for the control of aerodynamic loss originating from tip leakage flow in an axial compressor cascade.

A series of baseline and winglet tips were studied by varying the tip clearance size. Conclusions are listed as follows: (1)Cited by: 4.multistage compressor resulted in a point efficiency penalty, an 11% reduction in flow range, and a 10% reduction in peak pressure rise.

The accumulation of low momentum fluid near the blade tip and the vortical structure of the flow downstream of low speed compressors File Size: 1MB.Tip clearance and axial gap of a multistage compressor is investigated through CFD.

Good agreement is found between CFD and experimental data. Tip clearance has detrimental effect on turbine performance. Upstream stator should be as close as possible to the rotor to improve by: 5.