Loss and Flow Path Studies on Centrifugal Compressors—Part I

1970 ◽  
Vol 92 (3) ◽  
pp. 275-286 ◽  
Author(s):  
O. E. Balje´
Keyword(s):  
Boundary Layer ◽  
Flow Separation ◽  
Calculated Data ◽  
Flow Path ◽  
Fair Agreement ◽  
Pressure Gradients ◽  
Momentum Thickness ◽  
Centrifugal Compressors ◽  
Separation Criterion ◽  
Test Information

Relations are derived for the boundary layer momentum thickness growth in channels with adverse pressure gradients and for the maximum allowable momentum thickness to avoid flow separation. These data are obtained by integrating the Truckenbrodt equation stepwise and by extending the Gruschwitz-Schmidbauer separation criterion. Fair agreement between calculated data and test information is demonstrated.

Axial Cascade Technology and Application to Flow Path Designs. Part II—Application of Data to Flow Path Designs

1968 ◽  
Vol 90 (4) ◽  
pp. 329-340
Author(s):  
O. E. Balje´
Keyword(s):  
Calculated Data ◽  
Flow Path ◽  
Fair Agreement ◽  
Design Parameters ◽  
Performance Potential ◽  
Test Information ◽  
Speed Regime ◽  
Specific Speed

The cascade considerations presented in Part I are extended to obtain interrelations between cascade parameters and machine similarity parameters, and to assess the effect of compressibility on these interrelations. These data are used to compute the efficiency potential and cavitation sensitivity of single cascaded and multiple cascaded axial machines in the medium to high specific speed regime. The calculated data show fair agreement with the available test information. The effect of only a limited number of design parameters has been investigated. Further studies will be required to cover the performance potential adequately.

Loss and Flow Path Studies on Centrifugal Compressors—Part II

1970 ◽  
Vol 92 (3) ◽  
pp. 287-300 ◽  
Author(s):  
O. E. Balje´
Keyword(s):  
Boundary Layer ◽  
High Efficiency ◽  
Flow Path ◽  
Flow Conditions ◽  
Centrifugal Compressors ◽  
Mixed Flow ◽  
Path Design ◽  
Balanced Flow ◽  
Efficiency Data ◽  
Rotor Flow

The flow conditions in a mixed flow rotor are investigated for a “pressure balanced” flow path design. Boundary layer arguments are applied to calculate the losses in the rotor as well as in the subsequent diffuser section. The resulting efficiency data imply a comparatively high efficiency potential for mixed flow compressors with multiple cascaded components, designed on the premise of a “pressure balanced” rotor flow path.

A Simplified Form of the Auxiliary Equation for Use in the Calculation of Turbulent Boundary Layers

1958 ◽  
Vol 62 (567) ◽  
pp. 215-219
Author(s):  
T. J. Black
Keyword(s):  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Boundary Layers ◽  
Turbulent Boundary Layers ◽  
Auxiliary Equation ◽  
Pressure Gradients ◽  
Momentum Thickness ◽  
Form Parameter ◽  
New Type ◽  
Simple Quadrature

A New type of auxiliary equation is given for calculating the development of the form-parameter H in turbulent boundary layers with adverse pressure gradients. The chief advantage of this new method lies in the rapidity and ease of calculation which has been achieved, without apparent sacrifice of accuracy.Whereas the growth of momentum thickness in the turbulent boundary layer can now be rapidly calculated by methods involving only simple quadrature, the prediction of the form parameter development remains a laborious task, while the results obtained do not always appear to justify the complexity of the calculations.

Paper 1: Centrifugal Compressors for Gas Turbines

1968 ◽  
Vol 183 (14) ◽  
pp. 1-10 ◽  
Author(s):  
T. B. Ferguson
Keyword(s):  
Boundary Layer ◽  
Gas Turbines ◽  
Three Dimensional ◽  
Boundary Layer Theory ◽  
Pressure Gradients ◽  
Two Dimensional ◽  
Centrifugal Compressors ◽  
Blade Loading ◽  
Actual Flow ◽  
High Mach

The trends in fluid mechanical development of centrifugal compressors are discussed. The main developments in the impeller are the application of quasi-three-dimensional isentropic methods together with some separation criteria based on two-dimensional turbulent boundary layer theory. Diffusers are sometimes designed on a simplified two-dimensional basis but channel diffusers still appear to be preferred especially at high Mach numbers. Recent visualization studies have shown how far the actual flow in impellers may depart from the actual model and there is a lack of systematic quantitative experimental work on limiting blade loading and pressure gradients both in impellers and diffusers. A summary of gas turbine centrifugal compressors is also made.

The Effects of Adverse Pressure Gradients on Momentum and Thermal Structures in Transitional Boundary Layers: Part 2—Fluctuation Quantities

1996 ◽  
Vol 118 (4) ◽  
pp. 728-736 ◽  
Author(s):  
S. P. Mislevy ◽  
T. Wang
Keyword(s):  
Boundary Layer ◽  
Shear Stress ◽  
Transition Region ◽  
Boundary Layers ◽  
Reynolds Shear Stress ◽  
Turbulent Shear ◽  
Wall Region ◽  
Pressure Gradients ◽  
Baseline Case ◽  
Near Wall

The effects of adverse pressure gradients on the thermal and momentum characteristics of a heated transitional boundary layer were investigated with free-stream turbulence ranging from 0.3 to 0.6 percent. Boundary layer measurements were conducted for two constant-K cases, K1 = −0.51 × 10−6 and K2 = −1.05 × 10−6. The fluctuation quantities, u′, ν′, t′, the Reynolds shear stress (uν), and the Reynolds heat fluxes (νt and ut) were measured. In general, u′/U∞, ν′/U∞, and νt have higher values across the boundary layer for the adverse pressure-gradient cases than they do for the baseline case (K = 0). The development of ν′ for the adverse pressure gradients was more actively involved than that of the baseline. In the early transition region, the Reynolds shear stress distribution for the K2 case showed a near-wall region of high-turbulent shear generated at Y+ = 7. At stations farther downstream, this near-wall shear reduced in magnitude, while a second region of high-turbulent shear developed at Y+ = 70. For the baseline case, however, the maximum turbulent shear in the transition region was generated at Y+ = 70, and no near-wall high-shear region was seen. Stronger adverse pressure gradients appear to produce more uniform and higher t′ in the near-wall region (Y+ < 20) in both transitional and turbulent boundary layers. The instantaneous velocity signals did not show any clear turbulent/nonturbulent demarcations in the transition region. Increasingly stronger adverse pressure gradients seemed to produce large non turbulent unsteadiness (or instability waves) at a similar magnitude as the turbulent fluctuations such that the production of turbulent spots was obscured. The turbulent spots could not be identified visually or through conventional conditional-sampling schemes. In addition, the streamwise evolution of eddy viscosity, turbulent thermal diffusivity, and Prt, are also presented.

scholarly journals The flow separation delay in the boundary layer by induced vortices

2016 ◽  
Vol 20 (2) ◽  
pp. 251-261 ◽  
Author(s):  
Ishtiaq A. Chaudhry ◽  
Tipu Sultan ◽  
Farrukh A. Siddiqui ◽  
M. Farhan ◽  
M. Asim
Keyword(s):  
Boundary Layer ◽  
Flow Separation

scholarly journals Large eddies induced by local impulse at wall of boundary layer with pressure gradients

2008 ◽  
Vol 18 (7) ◽  
pp. 873-878 ◽  
Author(s):  
Changgen Lu ◽  
Weidong Cao ◽  
Yanmei Zhang ◽  
Jintao Peng
Keyword(s):  
Boundary Layer ◽  
Pressure Gradients ◽  
Large Eddies

Effects of Curvature on Laminar Boundary Layers in Sink-Type Flows

1969 ◽  
Vol 91 (3) ◽  
pp. 353-358 ◽  
Author(s):  
W. A. Gustafson ◽  
I. Pelech
Keyword(s):  
Boundary Layer ◽  
Boundary Layers ◽  
Momentum Equation ◽  
Similarity Solutions ◽  
Momentum Thickness ◽  
Two Dimensional ◽  
Thickness Increase ◽  
Laminar Boundary Layers ◽  
Converging Channel ◽  
Special Case

The two-dimensional, incompressible laminar boundary layer on a strongly curved wall in a converging channel is investigated for the special case of potential velocity inversely proportional to the distance along the wall. Similarity solutions of the momentum equation are obtained by two different methods and the differences between the methods are discussed. The numerical results show that displacement and momentum thickness increase linearly with curvature while skin friction decreases linearly.

Boundary Layer Flashback Model for Hydrogen Flames in Confined Geometries Including the Effect of Adverse Pressure Gradient

2020 ◽  
Author(s):  
Ólafur H. Björnsson ◽  
Sikke A. Klein ◽  
Joeri Tober
Keyword(s):  
Boundary Layer ◽  
Pressure Gradient ◽  
Flow Separation ◽  
Gradient Flow ◽  
Lewis Number ◽  
Adverse Pressure Gradient ◽  
Future Research ◽  
Diffuser Flow ◽  
Combustion Properties ◽  
Quenching Distance

Abstract The combustion properties of hydrogen make premixed hydrogen-air flames very prone to boundary layer flashback. This paper describes the improvement and extension of a boundary layer flashback model from Hoferichter [1] for flames confined in burner ducts. The original model did not perform well at higher preheat temperatures and overpredicted the backpressure of the flame at flashback by 4–5x. By simplifying the Lewis number dependent flame speed computation and by applying a generalized version of Stratford’s flow separation criterion [2], the prediction accuracy is improved significantly. The effect of adverse pressure gradient flow on the flashback limits in 2° and 4° diffusers is also captured adequately by coupling the model to flow simulations and taking into account the increased flow separation tendency in diffuser flow. Future research will focus on further experimental validation and direct numerical simulations to gain better insight into the role of the quenching distance and turbulence statistics.

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