Presentation of a Blade-Design Method for Axial-Flow Turbines, Including Design and Test Results of a Typical Axial-Flow Stage

1960 ◽  
Vol 82 (1) ◽  
pp. 19-26
Author(s):  
F. Baumgartner ◽  
R. Amsler
Keyword(s):  
Design Method ◽  
Axial Flow ◽  
Rate Of Change ◽  
Rotor Blades ◽  
Test Results ◽  
Blade Loading ◽  
Blade Row ◽  
Consistent Manner ◽  
The Mean ◽  
Typical Design

A method is presented to determine the shape of stationary nozzle blades and rotor blades for an axial-flow-type turbine in a generally consistent manner based on the concept of aerodynamic blade loading. The mean blade load is a typical design parameter which predominantly determines the blade curvature. It depends in particular on the rate of change of momentum across the blade row. By applying the design method, airfoil shapes are obtained which satisfy the momentum requirements regardless of what blade-load distribution is assumed as long as the mean blade load remains constant. A specific application of the design method is described and test data are presented which show that good agreement between design goal and test results was achieved.

Effect of Annulus Flow Conditions on Turbine Rim Seal Ingestion

2019 ◽  
Author(s):  
Donato M. Palermo ◽  
Feng Gao ◽  
John W. Chew ◽  
Paul F. Beard
Keyword(s):  
Velocity Ratio ◽  
Axial Flow ◽  
Passive Scalar ◽  
External Flow ◽  
Rotor Blades ◽  
Flow Structures ◽  
Flow Conditions ◽  
Sealing Performance ◽  
Annulus Flow ◽  
The Mean

Abstract A systematic study of sealing performance for a chute style turbine rim seal using URANS methods is reported. This extends previous studies from a configuration without external flow in the main annulus to cases with a circumferentially uniform axial flow and vane generated swirling annulus flow (but without rotor blades). The study includes variation of the mean seal-to-rotor velocity ratio, main annulus-to-rotor velocity ratio, and seal clearance. The effects on the unsteady flow structures and the degree of main annulus flow ingestion into the rim seal cavity are examined. Sealing effectiveness is quantified by modeling a passive scalar, and the timescales for the convergence of this solution are considered. It has been found that intrinsic flow unsteadiness occurs in most cases, with the presence of vanes and external flow modifying, the associated flow structures and frequencies. Some sensitivities to the annulus flow conditions are identified. The circumferential pressure asymmetry generated by the vanes has a clear influence on the flow structure but does not lead to higher ingestion rates than the other conditions studied.

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.

A Parametric Study of Radial Turbomachinery Blade Design in Three-Dimensional Subsonic Flow

1990 ◽  
Vol 112 (3) ◽  
pp. 338-345 ◽  
Author(s):  
W. S. Ghaly
Keyword(s):  
Parametric Study ◽  
Subsonic Flow ◽  
Pressure Field ◽  
Design Method ◽  
Three Dimensional ◽  
Rate Of Change ◽  
Blade Design ◽  
Blade Loading ◽  
Pressure Fields ◽  
Blade Shape

An aerodynamic design method is described and used to implement a parametric study of radial turbomachinery blade design in three-dimensional subsonic flow. Given the impeller hub and shroud, the number of blades and their stacking position, the design method gives the detailed blade shape, flow, and pressure fields that would produce a prescribed tangentially averaged swirl schedule. The results from that study show that decreasing the number of blades increases the blade wrap, and that the blade loading is strongly affected by the rate of change of mean swirl along the mean streamlines. The results also show that the blade shape and the pressure field are rather sensitive to the prescribed mean swirl schedule, which suggests that, by carefully tailoring the swirl schedule, one might be able to control the blade shape and the pressure field and hence secondary flow.

scholarly journals The Effect of Rotor Blade Thickness and Surface Finish on the Performance of a Small Axial Flow Turbine

1983 ◽  
Vol 105 (2) ◽  
pp. 377-382 ◽  
Author(s):  
R. J. Roelke ◽  
J. E. Haas
Keyword(s):  
Surface Finish ◽  
Rotor Blade ◽  
Axial Flow ◽  
Aerodynamic Performance ◽  
Rotor Blades ◽  
Performance Gain ◽  
Test Results ◽  
Blade Profile ◽  
Blade Thickness ◽  
Rough Surface Finish

An experimental investigation was conducted to determine the effect of blade profile inaccuracies and surface finish on the aerodynamic performance of a 11.15-cm tip dia turbine. The as-received cast rotor blades had a significantly thicker profile than the design intent and a fairly rough surface finish. Stage test results showed an increase of one point in efficiency by smoothing the surface finish and another three points by thinning the blade profiles to near the design profile. Most of the performance gain between the as-cast thick and the thinned rotor blades, both with the same surface finish, was attributed to reduced trailing edge losses of the recontoured blades.

A Parametric Study of Radial Turbomachinery Blade Design in Three-Dimensional Subsonic Flow

1989 ◽  
Author(s):  
W. S. Ghaly ◽  
C. S. Tan
Keyword(s):  
Parametric Study ◽  
Subsonic Flow ◽  
Pressure Field ◽  
Design Method ◽  
Three Dimensional ◽  
Rate Of Change ◽  
Blade Design ◽  
Blade Loading ◽  
Pressure Fields ◽  
Blade Shape

An aerodynamic design method is described and used to implement a parametric study of radial turbomachinery blade design in three-dimensional subsonic flow. Given the impeller hub and shroud, the number of blades and their stacking position, the design method gives the detailed blade shape, flow and pressure fields that would produce a prescribed tangential averaged swirl schedule. The results from that study show that decreasing the number of blades increases the blade wrap, and that the blade loading is strongly affected by the rate of change of mean swirl along the mean streamlines. The results also show that the blade shape and the pressure field are rather sensitive to the prescribed mean swirl schedule which suggests that, by carefuly tailoring the swirl schedule, one might be able to control the blade shape and the pressure field and hence secondary flow.

scholarly journals Effect of Acoustic Resonance Condition on Wake Generated Rotor Blade Gust Response

1993 ◽  
Author(s):  
Steven R. Manwaring ◽  
Sanford Fleeter
Keyword(s):  
Rotor Blade ◽  
Resonance Condition ◽  
Axial Flow ◽  
Acoustic Resonance ◽  
Pressure Response ◽  
Rotor Blades ◽  
Flow Models ◽  
Unsteady Pressure ◽  
Unsteady Aerodynamic ◽  
Blade Row

Unsteady aerodynamic blade row response is generally categorized as either subresonant or superresonant, with an acoustic resonance at the points where these regions meet. Although these far field acoustic responses are critical to obtaining correct predictions from linearized unsteady flow models, they are a subject of some controversy, both analytically and experimentally. In this paper, multistage axial flow compressor acoustic resonance conditions, including both subresonant and superresonant unsteady aerodynamic response in the immediate vicinity of an acoustic resonance, are experimentally investigated. This is accomplished by quantifying these acoustic resonance and subresonant and superresonant blade row interaction phenomena in terms of their effect on the rotor blade row periodic unsteady pressure response. The subresonant and superresonant acoustic environments are established by changing the number of vanes while maintaining the number of rotor blades, thereby altering the unsteady stator-rotor interactions and the interblade phase angle and by varying the Mach number without changing the blade row interactions. First the first stage rotor row periodic unsteady pressure response to a downstream stator-rotor interaction generated acoustic wave is studied. Then, the gust unsteady aerodynamic response of the first stage rotor row due to IGV wakes, with the IGV-instrumented first stage rotor itself configured to generate subresonant and superresonant conditions is considered. Appropriate data are correlated with predictions.

Experimental Evaluation of an Axial-Flow Transonic Compressor

1976 ◽  
Author(s):  
T. Tamaki ◽  
S. Nagano
Keyword(s):  
Rotational Speed ◽  
Velocity Ratio ◽  
Axial Flow ◽  
Rotating Stall ◽  
Test Results ◽  
Transonic Compressor ◽  
Multi Stage ◽  
Blade Row ◽  
Compressor Surge ◽  
Overall Performance

A five-stage transonic compressor was designed and tested to obtain overall performance and surge limits over a wide rotational speed range. Compressor surge limits are evaluated using individual stage performance characteristics with the aid of a single-stage test. These show that surging at low rotational speed occurs when rotating stall occurs in the first stage and that the wider operating range multi-stage compressor can be realized with the lower aspect ratio blades. On the basis of these test results, a simple model is constructed in order to evaluate the effect of the axial velocity ratio on the flow in a rotor blade row.

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