By R. W. Bilger (auth.), Prof. Richard S. L. Lee, Prof. James H. Whitelaw, Prof. T. S. Wung (eds.)
A Symposium on Aerothermodynamics of Combustors used to be held on the Institute of utilized Mechanics of the nationwide Taiwan collage from three to five June 1991 and was once attended by way of one hundred thirty delegates from 8 nations. the themes of the 40 formal displays incorporated measurements and calculations of isothermal simulations and of combusting flows with one and stages, and with attention of configurations starting from basic diffusion to gas-turbine flows. The discussions inside and out of the Symposium corridor have been vigorous and an open discussion board consultation verified the diversity of evaluations presently and strongly held. The foreign Union of Theoretical and utilized Mechanics initiated the Symposium below the chairmanship of Professor R S L Lee and with the medical Committee indexed lower than. It benefited from sponsorship, back as indexed lower than, and from participants who awarded attention-grabbing and updated descriptions in their study. Invited lectures have been brought by means of Professors R Bilger and F Weinberg and set the scene by way of caliber of fabric and presentation.
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Extra resources for Aerothermodynamics in Combustors: IUTAM Symposium Taipei, Taiwan, 1991
Transition of Turbulent Flame Structure From the experimental results obtained with the conical turbulent flame, it can be said that the so-called wrinkled laminar flame within the range of R A below 100 and Da above 20. is produced 44 Even if R A increases to about 300, the wrinkled laminar flame is also achieved in the opposed jet burner, when Da remains of the order of 20. When RA increases to 520 and Da decreases to 10, a large temperature fluctuation was observed on the unburned gas side of the flame zone.
In the transition regime, the turbulent premixed flame has characteristic features of both wrinkled laminar flame and distributed reaction zone. 1. Introduction The structure of the turbulent premixed flame depends on the turbulence Reynolds number defined by R A =(U'A)/V or RL =(u'L)/v and the Damkohler number, Da = (L/u')/( 0L/SL), where u' is the turbulence intensity, kinematic viscosity, turbulence, v the A the Taylor microscale, L the integral scale of 0L is the laminar flame thickness and SL the laminar burn- ing velocity.
_ _ ..... _ ............ """"'~,~~~~~~_,,_. ___ """''''''''''~~ 111111111"~~~"',I . . . . . . . •• .. :............. •••••••••• 1IIIIIIlft~/III t till .................. -HI. -30. -20. -10. 0. 10. 20. 30. r(mm) Fig. §. BB -4B. 5 -3B. -2B. -1111. B. lB. 2B. SB. 4B. r(mm) Fig. 11: Radial profiles of the v (axial) component of the velocity field at different z locations Fig. 13 provides the radial distributions of the u (radial) component of the velocity as a function of r for various z locations.
Aerothermodynamics in Combustors: IUTAM Symposium Taipei, Taiwan, 1991 by R. W. Bilger (auth.), Prof. Richard S. L. Lee, Prof. James H. Whitelaw, Prof. T. S. Wung (eds.)
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