Development of a Transonic Front Stage of an Axial Flow Compressor for Industrial Gas Turbines

1994 ◽  
Vol 116 (4) ◽  
pp. 605-611 ◽  
Author(s):  
Y. Katoh ◽  
Y. Kashiwabara ◽  
H. Ishii ◽  
Y. Tsuda ◽  
M. Yanagida
Keyword(s):  
Gas Turbines ◽  
Pressure Loss ◽  
Axial Flow ◽  
Rotating Stall ◽  
Rotor Blades ◽  
Industrial Gas Turbines ◽  
Stator Blade ◽  
Front Stage ◽  
Model Compressor ◽  
Flow Compressor

This paper describes the aerodynamic blade design of a highly loaded three-stage compressor, which is a model compressor for the front stage of an industrial gas turbine. Test results are presented that confirm design performance. Some surge and rotating stall measurement results are also discussed. The first stator blade in this test compressor operates in the high subsonic range at the inlet. To reduce the pressure loss due to blade surface shock waves, a shock-free airfoil is designed to replace the first stator blade in an NACA-65 airfoil in a three-stage compressor. Comparison of the performance of both blades shows that the shock-free airfoil blade reduces pressure loss. This paper also presents some experimental results for MCA (multicircular arc) airfoils, which are used for first rotor blades.

scholarly journals Development of a Transonic Front Stage of an Axial Flow Compressor for Industrial Gas Turbines

1993 ◽  
Author(s):  
Y. Katoh ◽  
Y. Kashiwabara ◽  
H. Ishii ◽  
Y. Tsuda ◽  
M. Yanagida
Keyword(s):  
Gas Turbines ◽  
Pressure Loss ◽  
Axial Flow ◽  
Rotating Stall ◽  
Rotor Blades ◽  
Industrial Gas Turbines ◽  
Stator Blade ◽  
Front Stage ◽  
Model Compressor ◽  
Flow Compressor

This paper describes the aerodynamic blade design of a highly-loaded three-stage compressor, which is a model compressor for the front stage of an industrial gas turbine. Test results are presented that confirm design performance. Some surge and rotating stall measurement results are also discussed. The first stator blade in this test compressor operates in the high subsonic range at the inlet. To reduce the pressure loss due to blade surface shock waves, a shock-free airfoil is designed to replace the first stator blade in an NACA-65 airfoil in a three-stage compressor. Comparison of the performance of both blades shows that the shock-free airfoil blade reduces pressure loss. This paper also presents some experimental results for MCA (multi-circular arc) airfoils, which are used for first rotor blades.

Compressor Surge in Gas Turbines and Blast Furnace Compressor Installations

1965 ◽  
Vol 87 (2) ◽  
pp. 193-196
Author(s):  
R. A. Strub ◽  
P. Suter
Keyword(s):  
Fatigue Failure ◽  
Gas Turbines ◽  
Axial Flow ◽  
Rotor Blades ◽  
Test Results ◽  
Dynamic Stresses ◽  
Compressor Surge ◽  
Bending Stresses ◽  
Flow Compressor ◽  
Measured Pressure

The character of different surge cycles is described, and the corresponding influence on the dynamic loading of the blades of axial flow compressors is discussed. It is shown that essentially fatigue is governed by the rapidity of loading or unloading of the blading. Test results from an experimental 4-stage axial flow compressor showed that the induced dynamic stresses in the blades, which reach about three times the steady gas bending stresses, can lead to fatigue failure. Reference is also made to previous surge tests carried out on a gas turbine installation, which indicate that a good correlation can be expected between the calculated and the measured pressure distribution. Mention is made of the fatigue failure of the rotor blades of an industrial compressor submitted to a long period of intense surging.

Separated Flows in Axial Flow Compressor With Variable Stator Vanes at Positive Incidence Angles

1994 ◽  
Author(s):  
Vaclav Cyrus
Keyword(s):  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Flow ◽  
Separated Flow ◽  
Rotating Stall ◽  
Compressor Stage ◽  
Diffusion Factor ◽  
Stator Blade ◽  
Flow Compressor ◽  
End Wall

A detailed investigation of three-dimensional flow was carried out in a low speed rear axial compressor stage with the change of the stator blade row setting. The stator blade stagger change was in the range of (−14) – (23) degree. Measurements were performed by means of both stationary and rotating pressure probes at seven working points. The origin of large regions of separated flow in blade rows at positive incidence angles was analysed with the use of the spanwise diffusion factor distribution. These areas in the rotor and stator rows originated as the diffusion factor exceeded the critial value D = 0.6 within (1/4 – 1/3) of the blade height near one end-wall. The rotating stall in compressor stage arised when large regions of separated flow occured simultaneously in both rotor and stator blade rows.

Washing Effectiveness Assessment of Different Cleaners on a Small-Scale Multistage Compressor

2021 ◽  
Author(s):  
Alessandro Vulpio ◽  
Alessio Suman ◽  
Nicola Casari ◽  
Michele Pinelli ◽  
Craig Appleby ◽  
...  
Keyword(s):  
Gas Turbines ◽  
Axial Flow ◽  
Solid Particles ◽  
Rotor Blades ◽  
Small Scale ◽  
Internal Surfaces ◽  
Environmentally Sensitive ◽  
Flow Compressor ◽  
Processing Techniques ◽  
Effectiveness Assessment

Abstract Suspended micrometric particles are always present in the air swallowed by gas turbines. These solid particles can overpass the filters of heavy-duty gas turbines and deposit onto the internal surfaces of the compressor, leading to the overtime reduction of the machine performances, and, as a result, to the fuel consumption augmentation. A widely employed method to slow down the engine degradation is to wash the engine frequently. Over the years, the washing techniques have been continuously improved in order to reach the best compromise between low fluid consumption and high washing capabilities. In this work, an experimental campaign has been carried out to estimate the washing effectiveness on a multistage axial-flow compressor fouled with micrometric soot particles. The cleaning fluids tested in the present work were demineralized water and two cleaners provided by ZOK International Group ltd: a commercial cleaner available on the market (ZOK 27), and a new, under development, environmentally-sensitive formula. The fluids have been tested employing three droplet size distributions (with mean diameters of 20 μm, 50 μm, and 100 μm). The washing effectiveness has been assessed through image post-processing techniques by analyzing the pictures of the stator vanes and rotor blades taken in fouled and washed conditions. From the present investigation, two results arise. The finest droplets show a greater capability to remove soot deposits showing how, when the washing operation takes place during quasi-idle operating condition, the turbulent-driven motion spread smaller particles on a wider blade region. The second results is the demonstration how a environmentally-sensitive chemical formula allows the obtainment of good results in terms removal capability for the same amount of product. This finding could help the plant manager to operate the gas turbine with less constraints in terms of cost and rules.

Application of Bifurcation Theory to Axial Flow Compressor Instability

1989 ◽  
Vol 111 (4) ◽  
pp. 426-433 ◽  
Author(s):  
F. E. McCaughan
Keyword(s):  
Parameter Space ◽  
Bifurcation Theory ◽  
Qualitative Difference ◽  
Axial Flow ◽  
Complete Information ◽  
Rotating Stall ◽  
Numerical Work ◽  
System Parameters ◽  
Parametric Effects ◽  
Flow Compressor

When a compression system becomes unstable, the mode of response depends on the operating and system parameters, such as throttle setting and B parameter. Previous numerical work on the model developed by Moore and Greitzer has provided a limited picture of the parametric effects. Applying bifurcation theory to a single-harmonic version of the model has supplied much more complete information, defining the boundaries of each mode of response in the parameter space. Specifically this is shown in a plot of B versus throttle setting, which compares well with the corresponding map produced experimentally. We stress the importance of the shape of the rotating stall characteristic. The analysis shows the qualitative difference between classic surge and deep surge.

Three-Dimensional Flows and Loss Reduction in Axial Compressors

1987 ◽  
Vol 109 (3) ◽  
pp. 354-361 ◽  
Author(s):  
Y. Dong ◽  
S. J. Gallimore ◽  
H. P. Hodson
Keyword(s):  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Flow ◽  
Tracer Gas ◽  
Suction Surface ◽  
Axial Compressors ◽  
Small Clearance ◽  
Oil Flow ◽  
Stator Blade ◽  
Flow Compressor

Measurements have been performed in a low-speed high-reaction single-stage axial compressor. Data obtained within and downstream of the rotor, when correlated with the results of other investigations, provide a link between the existence of suction surface–hub corner separations, their associated loss mechanisms, and blade loading. Within the stator, it has been shown that introducing a small clearance between the stator blade and the stationary hub increases the efficiency of the stator compared to the case with no clearance. Oil flow visualizaton indicated that the leakage reduced the extensive suction surface–hub corner separation that would otherwise exist. A tracer gas experiment showed that the large radial shifts of the surface streamlines indicated by the oil flow technique were only present close to the blade. The investigation demonstrates the possible advantages of including hub clearance in axial flow compressor stator blade rows.

Development of a New Front Stage for an Industrial Axial Flow Compressor

1994 ◽  
Vol 116 (4) ◽  
pp. 597-604 ◽  
Author(s):  
B. Eisenberg
Keyword(s):  
Design Method ◽  
Guide Vane ◽  
Theoretical Calculations ◽  
Axial Flow ◽  
Operating Range ◽  
Performance Curves ◽  
Front Stage ◽  
Inverse Design Method ◽  
Flow Compressor ◽  
High Degree

Industrial axial flow compressors are specially designed to achieve a wide operating range. The analysis of an existing six-stage axial flow research compressor indicated that the front stage could be improved significantly using modern design technique. To demonstrate the advantages of such a technique a redesign of the current front stage was conducted. By controlling the diffusion inside the blade sections with an inverse design method, loading was enlarged. Higher loading normally results in a reduction of profile incidence range. For compensation a wide chord application was chosen. Compared to the original compressor version, experiments resulted in steeper characteristic curves together with larger usable operating range. Keeping the same outer and inner diameter, mass flow was increased by 6 percent. Measurements of performance curves with variable speed and for guide vane control are presented. Theoretical calculations achieve a high degree of agreement with measured performance.

scholarly journals A 3D Rotating Stall Stability Model for Axial Flow Compressor

1997 ◽  
Author(s):  
Ren-Jing Cao ◽  
Sheng Zhou
Keyword(s):  
Axial Flow ◽  
Rotating Stall ◽  
3D Flow ◽  
Aerodynamic Stability ◽  
Stall Margin ◽  
Spatial Variables ◽  
Stability Behavior ◽  
Stability Model ◽  
Flow Effects ◽  
Flow Compressor

Rotating stall phenomenon is usually characterized by 3D aerodynamic stability behavior. The earlier models mainly considered the flow effects in terms of 1D and 2D spatial variables. In order to involve the characteristics of the 3D flow of the compressor, it is necessary to improve the existing rotating stall stability models and further develop the models to consider the effects of the 3D disturbance. In this paper, a new aerodynamic stability model concerning the effects of a radial disturbance produced by the compressor, and explaining more mechanisms about the aerodynamic stability of compressor is presented. Using the developed rotating stall stability model, the stall margins are calculated and compared to experimental data for two axial flow compressors. The calculated results show that the developed 3D rotating stall stability model gives better stall margin prediction than that by the 2D model.

Distributed Control of Rotating Stall in an Axial Flow Compressor With Actuator Constraints

2000 ◽  
Author(s):  
Craig A. Buhr ◽  
Matthew A. Franchek ◽  
Sanford Fleeter
Keyword(s):  
Absolute Stability ◽  
Closed Loop ◽  
Axial Flow ◽  
Gain Control ◽  
Rotating Stall ◽  
Control Law ◽  
Circle Criterion ◽  
Axial Flow Compressor ◽  
Flow Compressor ◽  
Stall Control

Abstract Presented in this paper is an analytical study evaluating the closed loop stability of rotating stall control in an axial flow compressor subject to a nonlinear spatial actuation constraint that limits the amplitude of a spatial mode input. Absolute stability of the rotating stall control system is investigated by applying the circle criterion to a linearized model of an axial compressor in series with the saturation element. This stability analysis is then used to design the gain and phase of the ‘classical’ complex gain feedback control law. Resulting is a systematic method for designing the parameters of the complex gain control law which increases the region of absolute stability guaranteed by the circle criterion for the closed-loop system.

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