Large chord turbine cascade testing at engine Mach and Reynolds numbers

1991 ◽  
Vol 12-12 (1-2) ◽  
pp. 119-124 ◽  
Author(s):  
D. J. Mee
Keyword(s):  
Reynolds Numbers ◽  
Turbine Cascade ◽  
Cascade Testing ◽  
Mach And Reynolds Numbers

The Application of Convective Cooling Enhancement of Span-Wise Cooling Holes in a Typical First Stage Turbine Blade

1991 ◽  
Author(s):  
D. J. Stankiewicz ◽  
T. R. Kirkham
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Enhancement ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Reynolds Numbers ◽  
Transfer Enhancement ◽  
Test Rig ◽  
Heated Oil ◽  
Cooling Enhancement ◽  
Mach And Reynolds Numbers

A technique of heat transfer enhancement is investigated whereby the internal span-wise cooling passages of a typical first stage gas turbine blade are modified by the introduction of circumferential ribs. The technique is verified by the use of a test rig incorporating a heated internally ribbed tube operating at the same range of Mach and Reynolds numbers as the turbine blade as well as by a test rig incorporating actual production blades immersed in a heated oil bath.

The Off-Design Performance of a Low-Pressure Turbine Cascade

1987 ◽  
Vol 109 (2) ◽  
pp. 201-209 ◽  
Author(s):  
H. P. Hodson ◽  
R. G. Dominy
Keyword(s):  
Reynolds Numbers ◽  
Low Pressure ◽  
Turbine Rotor ◽  
Surface Flow ◽  
Operating Conditions ◽  
Turbine Cascade ◽  
Linear Cascade ◽  
Design Performance ◽  
Low Pressure Turbine ◽  
Wide Range

The ability of a given blade profile to operate over a wide range of conditions is often of the utmost importance. This paper reports the off-design performance of a low-pressure turbine rotor root section in a linear cascade. Data were obtained using pneumatic probes and surface flow visualization. The effects of incidence (+9, 0, −20 deg), Reynolds (1.5, 2.9, 6.0 × 105), pitch-chord ratio (0.46, 0.56, 0.69), and inlet boundary layer thickness (0.011, 0.022 δ*/C) are discussed. Particular attention is paid to the three dimensionality of the flow field. Significant differences in the detail of the flow occur over the range of operating conditions investigated. It is found that the production of new secondary loss is greatest at lower Reynolds numbers, positive incidence, and the higher pitch-chord ratios.

Influence of Mach and Reynolds numbers on heat transfer to the leeward surface of a half-cone at hypersonic speed

1977 ◽  
Vol 11 (5) ◽  
pp. 736-739 ◽  
Author(s):  
M. M. Ardasheva ◽  
V. Ya. Borovoi ◽  
P. I. Gorenbukh ◽  
M. V. Ryzhkova
Keyword(s):  
Heat Transfer ◽  
Reynolds Numbers ◽  
Hypersonic Speed ◽  
Half Cone ◽  
Mach And Reynolds Numbers

Combined influence of the mach and Reynolds numbers on transition in the boundary layer

1975 ◽  
Vol 9 (1) ◽  
pp. 126-129 ◽  
Author(s):  
V. G. Pridanov ◽  
A. M. Kharitonov ◽  
V. V. Chernykh
Keyword(s):  
Boundary Layer ◽  
Reynolds Numbers ◽  
Mach And Reynolds Numbers

Conversion of Centrifugal Compress Performance Curves Considering Non-Similar Flow Conditions

1982 ◽  
Author(s):  
W. Fister ◽  
J. Kotzur
Keyword(s):  
Energy Transfer ◽  
Centrifugal Compressor ◽  
Performance Testing ◽  
Reynolds Numbers ◽  
New Method ◽  
Flow Conditions ◽  
Flow Losses ◽  
Performance Curves ◽  
Thermodynamic Performance ◽  
Mach And Reynolds Numbers

Thermodynamic performance testing of centrifugal compressor cannot always be implemented at the same conditions on which the rating of the machine was based. To permit them to be compared to the rated values, the test values must therefore be converted to the respective suction data, gas properties and speeds. Conversion methods applied today which assume similar or approximately similar flow conditions for testing and rating, specify in various instance too narrow limits for this. A new conversion method based on few measurement values was developed to consider the influence exerted by the most important parameters, such as Mach and Reynolds numbers, etc. on energy transfer in the stage and on flow losses. Performance curves converted according to the new method, are compared to actually measured values.

Numerical Investigation of the Wake-Boundary Layer Interaction on a Highly Loaded LP Turbine Cascade Blade

2002 ◽  
Author(s):  
Pasquale Cardamone ◽  
Peter Stadtmu¨ller ◽  
Leonhard Fottner
Keyword(s):  
Boundary Layer ◽  
Separation Bubble ◽  
Transition Process ◽  
Reynolds Numbers ◽  
Numerical Approach ◽  
Experimental Investigations ◽  
Turbine Cascade ◽  
Suction Surface ◽  
Time Resolved ◽  
Highly Loaded

The effects of wake passing on the development of the profile boundary layer of a highly loaded low-pressure turbine cascade are studied using the RANS code TRACE-U. The numerical results are compared with available experimental data to verify the accuracy of the code in predicting the periodic-unsteady transition and separation mechanisms at low Reynolds number conditions. The experimental investigations have been carried out on a turbine cascade called T106D-EIZ subjected to wakes generated by an up-stream moving bar-type generator. The cascade pitch was increased by about 30% with respect to design conditions without modifying the blade geometry in order to obtain a large separation bubble on the suction surface. The extensive database containing time-averaged as well as time-resolved results was presented in a separate paper by Stadtmu¨ller and Fottner (2001) and is discussed only briefly. The time-accurate multistage Navier-Stokes solver TRACE-U developed by the DLR Cologne used for the numerical simulations employs a modified version of the one-equation Spalart-Allmaras turbulence model coupled with a transition correlation based on the work of Abu-Ghannam and Shaw in the formulation of Drela. The objective of this paper is to provide further insight into the aerodynamics of the wake-induced transition process and to rate the application limits of the numerical approach for exit Reynolds numbers as low as 60.000. The CFD predictions for two different flow conditions are compared with the measurements. Plots of wall-shear stress, blade loading, shape factor and loss behaviour are used to verify the reliability of the code. The periodic-unsteady development of the boundary layer as well as the loss behaviour is well reproduced for higher Reynolds numbers. For the case with massive separation, large discrepancies between numerical and experimental results are observed.

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