Here we report on an effort to include an empirically based transition modeling capability in a Reynolds Averaged Navier-Stokes solver. Well known empirical models for both attached- and separated-flow transition were tested against cascade data and found unsuitable for use in turbomachinery design. Consequently, a program was launched to develop models with sufficient accuracy for use in design. As a first step, accurate prediction of free stream turbulence development was identified as a prerequisite for accurate modeling. Additionally, a demonstrated capability to capture the effects of free stream turbulence on pre-transitional boundary layers became an impetus for the work. A computational fluid dynamics (CFD)-supplemented database of 104 experimental cascade cases was constructed to explore the development of new correlations. Dimensional analyses were performed to guide the work, and appropriate non-dimensional parameters were then extracted from CFD predictions of the laminar boundary layers existing on the airfoil surfaces prior to either transition onset or incipient separation. For attached-flow transition, onset was found to occur at a critical ratio of the boundary-layer diffusion time to a time scale associated with the energy-bearing turbulent eddies. In the case of separated-flow transition, it was found that the length of a separation bubble prior to turbulent reattachment was a simple function of the local momentum thickness at separation and the overall surface length traversed by a fluid element prior to separation. Both the attached- and separated-flow transition models were implemented into the design system as point-like trips.
Skip Nav Destination
e-mail: john.clark3@wpafb.af.mil
Article navigation
January 2007
Technical Papers
Predicting Transition in Turbomachinery—Part I: A Review and New Model Development
T. J. Praisner,
T. J. Praisner
Turbine Aerodynamics
, United Technologies Pratt & Whitney, 400 Main St., M/S 169-29, East Hartford, CT 06108
Search for other works by this author on:
J. P. Clark
J. P. Clark
Turbine Branch, Turbine Engine Division, Propulsion Directorate,
e-mail: john.clark3@wpafb.af.mil
Air Force Research Laboratory
, Building 18, Room 136D, 1950 5th St., WPAFB, OH 45433
Search for other works by this author on:
T. J. Praisner
Turbine Aerodynamics
, United Technologies Pratt & Whitney, 400 Main St., M/S 169-29, East Hartford, CT 06108
J. P. Clark
Turbine Branch, Turbine Engine Division, Propulsion Directorate,
Air Force Research Laboratory
, Building 18, Room 136D, 1950 5th St., WPAFB, OH 45433e-mail: john.clark3@wpafb.af.mil
J. Turbomach. Jan 2007, 129(1): 1-13 (13 pages)
Published Online: March 1, 2004
Article history
Received:
October 1, 2003
Revised:
March 1, 2004
Connected Content
This is a correction to:
Predicting Transition in Turbomachinery—Part II: Model Validation and Benchmarking
Citation
Praisner, T. J., and Clark, J. P. (March 1, 2004). "Predicting Transition in Turbomachinery—Part I: A Review and New Model Development." ASME. J. Turbomach. January 2007; 129(1): 1–13. https://doi.org/10.1115/1.2366513
Download citation file:
Get Email Alerts
Related Articles
An Experimental Study of the Laminar Flow Separation on a Low-Reynolds-Number Airfoil
J. Fluids Eng (May,2008)
A Correlation-Based Transition Model Using Local Variables—Part II:
Test Cases and Industrial Applications
J. Turbomach (January,0001)
Predicting Transition in Turbomachinery—Part II: Model Validation and Benchmarking
J. Turbomach (January,2007)
Predicting Transitional Separation Bubbles
J. Turbomach (July,2005)
Related Proceedings Papers
Related Chapters
Applications
Introduction to Finite Element, Boundary Element, and Meshless Methods: With Applications to Heat Transfer and Fluid Flow
The Design and Implement of Remote Inclinometer for Power Towers Based on MXA2500G/GSM
International Conference on Mechanical and Electrical Technology, 3rd, (ICMET-China 2011), Volumes 1–3
Introduction
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis