An experimental investigation of stator/rotor interaction influence on multistage compressor rotor flow

1985 ◽  
Author(s):  
D. TWEEDT ◽  
T. OKIISHI ◽  
M. HATHAWAY
Keyword(s):  
Experimental Investigation ◽  
Compressor Rotor ◽  
Multistage Compressor ◽  
Rotor Flow

scholarly journals Experimental Investigation and Modeling of Surge in a Multistage Compressor

2017 ◽  
Vol 105 ◽  
pp. 1751-1756 ◽  
Author(s):  
Enrico Munari ◽  
Mirko Morini ◽  
Michele Pinelli ◽  
Pier Ruggero Spina
Keyword(s):  
Experimental Investigation ◽  
Multistage Compressor

Compressor/Diffuser/Combustor Aerodynamic Interactions in Lean Module Combustors

2008 ◽  
Vol 130 (1) ◽  
Author(s):  
A. Duncan Walker ◽  
Jon F. Carrotte ◽  
James J. McGuirk
Keyword(s):  
Experimental Investigation ◽  
Guide Vane ◽  
Interaction Effects ◽  
Single Stage ◽  
Flow Rates ◽  
Fuel Injectors ◽  
Compressor Rotor ◽  
Outer Annulus ◽  
Mass Flows ◽  
External Aerodynamics

The paper reports an experimental investigation into the possibility of increased interactions between combustor external aerodynamics and upstream components, e.g., prediffuser, compressor outlet guide vane (OGV), and even the compressor rotor, caused by the trend in lean module fuel injectors to larger mass flows entering the combustor cowl. To explore these component interaction effects, measurements were made on a fully annular rig comprising a single stage compressor, an advanced integrated OGV/prediffuser, followed by a dump diffuser and a generic combustor flametube with metered cowl and inner/outer annulus flows. The flow split entering the cowl was increased from 30% to 70%. The results demonstrate that, with fixed geometry, as the injector flow increases, the performance of the prediffuser and feed annuli suffer. Prediffuser losses increase and at high injector flow rates, the diffuser moves close to separation. The substantial circumferential variation in cowl flow can feed upstream and cause rotor forcing. Notable differences in performance were observed inline and between injectors at the OGV exit, suggesting that geometry changes such as an increased dump gap or nonaxisymmetric prediffuser designs may be beneficial.

A Fundamental Criterion for the Application of Rotor Casing Treatment

1979 ◽  
Vol 101 (2) ◽  
pp. 237-243 ◽  
Author(s):  
E. M. Greitzer ◽  
J. P. Nikkanen ◽  
D. E. Haddad ◽  
R. S. Mazzawy ◽  
H. D. Joslyn
Keyword(s):  
Experimental Investigation ◽  
Flow Field ◽  
Total Pressure ◽  
The Other ◽  
Substantial Decrease ◽  
Stall Margin ◽  
Casing Treatment ◽  
Compressor Rotor

An experimental investigation has been carried out on the influence of grooved casing treatment on the stall margin of a compressor rotor. Tests were conducted with two rotor builds having different solidities (but all other parameters identical) so that one of the rotors exhibited a wall, or casing, type of stall, while the other showed a blade stall. It was found that the casing treatment, when compared to the solid casing, was very effective in increasing the stall margin of the wall stall configuration, whereas there was little or no change in the stall point of the blade stall configuration. Detailed relative frame measurements of the rotor exit flow field were also taken as part of the program. These showed that in a wall stall situation, the use of casing treatment produced a substantial decrease in the relative total pressure defect, compared with the solid casing, while this was not true for the blade stall type of blading. The results of the experiments, both in overall measurements and in the detailed relative frame traverses, support the hypothesis that casing treatment is effective only in a situation in which a wall stall exists.

Impact of Uniform Surface Roughness on the Aerodynamic Performance of an Axial Compressor Rotor at Different Rotational Speeds

2021 ◽  
Author(s):  
Ashima Malhotra ◽  
Shraman Goswami ◽  
Pradeep A M
Keyword(s):  
Surface Roughness ◽  
Numerical Study ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Performance Loss ◽  
Compressor Rotor ◽  
Multistage Compressor ◽  
Design Speed ◽  
The Impact ◽  
Relative Flow

Abstract The aerodynamic performance of a compressor rotor is known to deteriorate due to surface roughness. It is important to understand this deterioration as it impacts the overall performance of the engine. This paper, therefore, aims to numerically investigate the impact of roughness on the performance of an axial compressor rotor at different rotational speeds. In this numerical study, the simulations are carried out for NASA Rotor37 at 100%, 80%, and 60% of its design speed. with and without roughness on the blade surface. These speeds are chosen because they represent different flow regimes. The front stages of a multistage compressor usually have a supersonic or transonic regime whereas the middle and aft stages have a subsonic regime. Thus, these performance characteristics can give an estimate of the impact on the performance of a multistage compressor. At 100% speed (design speed), the relative flow is supersonic, at 80% of design speed, the relative flow is transonic and at 60% of design speed, the relative flow is subsonic. Detailed flow field investigations are carried out to understand the underlying flow physics. The results indicate that, for the same amount of roughness, the degradation in the performance is maximum at 100% speed where the rotor is supersonic, while the impact is minimum at 60% speed where the rotor is subsonic. Thus, the rotor shock system plays an important role in determining the performance loss due to roughness. It is also observed that the loss increases with increased span for 100% and 80% speeds, but for 60% speed, the loss is almost constant from the hub to the shroud. This is because, with the increased span, the shock strength increases for 100% and 80% speeds, whereas at 60% speed flow is subsonic.

Experimental Investigation of Compressor Rotor Wakes.

1980 ◽  
Author(s):  
Robert P. Dring ◽  
H. D. Joslyn ◽  
L. W. Hardin
Keyword(s):  
Experimental Investigation ◽  
Compressor Rotor

An Experimental Investigation Into the Effect of Wakes on the Unsteady Turbine Rotor Flow

1985 ◽  
Vol 107 (2) ◽  
pp. 458-465 ◽  
Author(s):  
A. Binder ◽  
W. Fo¨rster ◽  
H. Kruse ◽  
H. Rogge
Keyword(s):  
Heat Transfer ◽  
Experimental Investigation ◽  
Turbine Rotor ◽  
Rotor Blades ◽  
Air Turbine ◽  
Flow Phenomena ◽  
Unsteady Effects ◽  
Yaw Angle ◽  
Insight Into ◽  
Rotor Flow

Detailed measurements were carried out near and within a turbine rotor using the Laser-2-Focus velocimeter. Testing was performed in a single stage cold air turbine at off-design conditions with a stator outlet Mach number of approximately 0.8. Instantaneous and averaged results of the velocity, the yaw angle, and the turbulence intensity provided information on the rotor flow field. This report describes the periodical and random unsteady effects of the stator wakes impinging on the rotor blades. In particular the constant unsteadiness contours clearly disclose the development of the wakes cut by the rotor blades. The objective of the study was to gain more insight into unsteady flow phenomena affecting losses, heat transfer, and related problems.

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