Secondary Flows in Straight and Annular Turbine Cascades

1985 ◽  
pp. 621-664 ◽  
Author(s):  
C. H. Sieverding
Keyword(s):  
Secondary Flows ◽  
Turbine Cascades

Production and Development of Secondary Flows and Losses in Two Types of Straight Turbine Cascades: Part 1—A Stator Case

1987 ◽  
Vol 109 (2) ◽  
pp. 186-193 ◽  
Author(s):  
A. Yamamoto
Keyword(s):  
Secondary Flow ◽  
Total Pressure ◽  
Experimental Information ◽  
Secondary Flows ◽  
Accumulation Process ◽  
Flow Angle ◽  
Turning Angle ◽  
Pressure Losses ◽  
Flow Vectors ◽  
Turbine Cascades

The present study intends to give some experimental information on secondary flows and on the associated total pressure losses occurring within turbine cascades. Part 1 of the paper describes the mechanism of production and development of the loss caused by secondary flows in a straight stator cascade with a turning angle of about 65 deg. A full representation of superimposed secondary flow vectors and loss contours is given at fourteen serial traverse planes located throughout the cascade. The presentation shows the mechanism clearly. Distributions of static pressures and of the loss on various planes close to blade surfaces and close to an endwall surface are given to show the loss accumulation process over the surfaces of the cascade passage. Variation of mass-averaged flow angle, velocity and loss through the cascade, and evolution of overall loss from upstream to downstream of the cascade are also given. Part 2 of the paper describes the mechanism in a straight rotor cascade with a turning angle of about 102 deg.

Production and Development of Secondary Flows and Losses in Two Types of Straight Turbine Cascades: Part 2—A Rotor Case

1987 ◽  
Vol 109 (2) ◽  
pp. 194-200 ◽  
Author(s):  
A. Yamamoto
Keyword(s):  
Pressure Gradient ◽  
Production Process ◽  
Experimental Analysis ◽  
Significant Contribution ◽  
Adverse Pressure Gradient ◽  
Secondary Flows ◽  
Suction Surface ◽  
Turning Angle ◽  
Detailed Mechanism ◽  
Turbine Cascades

Part 1 of this paper [1] presents the detailed mechanism of secondary flows and the associated losses occurring within a straight stator cascade with a relatively low turning angle of about 65 deg. The significant contribution of secondary flows on the loss production process was shown only near the blade suction surface downstream from the cascade throat (Z/Cax = 0.74) in which regional flows decelerated due to adverse pressure gradient. In the second part, the same experimental analysis is applied to a straight rotor cascade with a much larger turning angle of 102 deg. Flow surveys were made at 12 traverse planes located throughout the rotor cascade. The larger turning results in a similar but much stronger contribution of the secondary flows to the loss developing mechanism. Evolution of overall loss starts quite early within the cascade, and the rate of the loss growth is much larger in the rotor case than in the stator case.

Production and Development of Secondary Flows and Losses Within Two Types of Straight Turbine Cascades: Part 1 — A Stator Case

1986 ◽  
Author(s):  
A. Yamamoto
Keyword(s):  
Secondary Flow ◽  
Total Pressure ◽  
Experimental Information ◽  
Secondary Flows ◽  
Accumulation Process ◽  
Flow Angle ◽  
Turning Angle ◽  
Pressure Losses ◽  
Flow Vectors ◽  
Turbine Cascades

The present study intends to give some experimental information on secondary flows and on the associated total pressure losses occurring within turbine cascades. Part 1 of the paper describes the mechanism of production and development of the loss caused by secondary flows in a straight stator cascade with a turning angle of about 65°. A full representation of superimposed secondary flow vectors and loss contours is given at serial fourteen traverse planes located throughout the cascade, which shows the mechanism clearly. Distributions of static pressures and of the loss on various planes close to blade surfaces and close to an endwall surface are given to show the loss accumulation process over the surfaces of the cascade passage. Variation of mass-averaged flow angle, velocity and loss through the cascade, and evolution of overall loss from upstream to downstream of the cascade are also given. Part 2 of the paper describes the mechanism in a straight rotor cascade with a turning angle of about 102°.

Feasibility Study of Incorporating Flow Unsteadiness in Control of Secondary Flows in Shrouded Turbines

2013 ◽  
Author(s):  
Jie Gao ◽  
Qun Zheng ◽  
Xiaoquan Jia
Keyword(s):  
High Pressure ◽  
Three Dimensional ◽  
Internal Flow ◽  
Secondary Flows ◽  
Navier Stokes ◽  
High Pressure Turbine ◽  
Numerical Investigations ◽  
Flow Interactions ◽  
Turbine Cascades ◽  
Flow Effects

The internal flow in turbomachinery is inherently unsteady, and the endwall losses are major sources of lost efficiency in high-pressure turbine cascades. Therefore, the investigation of the unsteady endwall flow interactions is valuable to improve the performance of high-pressure turbines. Unsteady and steady numerical investigations of endwall flow interactions of 1.5-stage shrouded turbines with straight and bowed vanes are performed using a three-dimensional Navier-Stokes viscous solver. Emphasis is placed on how unsteady stator-rotor interactions affect shrouded turbine endwall secondary flows, on the basis of which the feasibility of incorporating the unsteady endwall flow effects in the control of secondary flows is discussed in detail. Results from this investigation are well presented and discussed in this paper.

Predictions of Endwall Losses and Secondary Flows in Axial Flow Turbine Cascades

1986 ◽  
Author(s):  
O. P. Sharma ◽  
T. L. Butler
Keyword(s):  
Flow Visualization ◽  
Secondary Flow ◽  
Axial Flow ◽  
Secondary Flows ◽  
Integral Boundary ◽  
Realistic Interpretation ◽  
Proposed Model ◽  
Turbine Cascades ◽  
Flow Theories ◽  
Semi Empirical

The development of a semi-empirical model for estimating endwall losses is described in this paper. The model has been developed from improved understanding of complex endwall secondary flows, acquired through review of flow visualization and pressure loss data for axial flow turbomachine cascades. The flow visualization data together with detailed measurements of viscous flow development through cascades have permitted more realistic interpretation of the classical secondary flow theories for axial turbomachine cascades. The re-interpreted secondary flow theories together with integral boundary layer concepts are used to formulate a calculation procedure for predicting losses due to the endwall secondary flows. The proposed model is evaluated against data from published literature and improved agreement between the data and predictions is demonstrated.

Secondary Flows in Compressor Bladings

1977 ◽  
Vol 99 (2) ◽  
pp. 211-224 ◽  
Author(s):  
K. Papailiou ◽  
R. Flot ◽  
J. Mathieu
Keyword(s):  
Shear Layers ◽  
Experimental Information ◽  
Secondary Flows ◽  
Experimental Results ◽  
Critical Examination ◽  
Calculation Methods ◽  
Multistage Compressors ◽  
Turbine Cascades ◽  
Wall Shear ◽  
End Wall

Present-day theories for the calculation of the development of end-wall shear layers in compressors demand detailed experimental information for their modeling. Experimental results obtained from compressor and turbine cascades and from single and multistage compressors were used in order to perform a critical examination of the underlying hypotheses of the available calculation methods.

scholarly journals Loss classification and review of secondary flow models in gas turbine cascades

2020 ◽  
pp. 30-39
Author(s):  
Stanislav Piskunov ◽  
◽  
Denis Popov ◽  
Nikita Samoylenko ◽  
◽  
...  
Keyword(s):  
Total Pressure ◽  
Complete Classification ◽  
Review Article ◽  
Secondary Flows ◽  
Sources Of Information ◽  
Aerodynamic Efficiency ◽  
Flow Models ◽  
Turbofan Engines ◽  
Turbine Cascades

Much attention is paid to increasing the efficiency of turbofan engines by increasing the efficiency of the main modules. The aerodynamic efficiency of a turbine depends on the level of total pressure and kinetic energy losses, which are determined by the scale of secondary flows in the channels of the turbine cascades. There are many studies and articles on the topic of secondary flows, in which vortex structures are often given incorrect names. The problem lies in the absence of a unified model of secondary flows and mismatch in the names of the components of secondary flows in adaptation of model descriptions from English to Russian. The purpose of this review article is to consider the existing classifications of losses and the most famous models of secondary flows in turbine cascades, including the Wang model, the Goldstein and Spores model, the Sharma and Butler model, etc. The considered sources of information made it possible to single out the most complete classification of losses, compare with each other the components of secondary flows of various models, describe the mechanism of their occurrence and give the most complete nomenclature of secondary flows in turbine cascades.

Production and Development of Secondary Flows and Losses Within Two Types of Straight Turbine Cascades: Part 2 — A Rotor Case

1986 ◽  
Author(s):  
A. Yamamoto
Keyword(s):  
Pressure Gradient ◽  
Production Process ◽  
Experimental Analysis ◽  
Significant Contribution ◽  
Adverse Pressure Gradient ◽  
Secondary Flows ◽  
Suction Surface ◽  
Turning Angle ◽  
Detailed Mechanism ◽  
Turbine Cascades

Part 1 of this paper[1] presented the detailed mechanism of secondary flows and the associated losses occurring within a straight stator cascade with a relatively low turning angle of about 65°. Significant contribution of secondary flows on the loss production process was shown only near the blade suction surface downstream from the cascade throat (Z/Cax=0.74) in which region flows decelerated due to adverse pressure gradient. In the second part, the same experimental analysis was applied to a straight rotor cascade with a much larger turning-angle of 102°. Flow surveys were made at twelve traverse planes located throughout the rotor cascade. The larger turning results in a similar but much stronger contribution of the secondary flows on the loss developing mechanism. Evolution of overall loss starts quite early within the cascade, and the rate of the loss growth is much larger in the rotor case than in the stator case.

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