Fluid Dynamics

, Volume 4, Issue 3, pp 107–112 | Cite as

Study of incident shock interaction with a two-dimensional boundary layer

  • G. S. Balandina
  • L. M. Zysina-Molozhen
  • L. A. Fel'dberg
  • I. G. Shapiro
Article
  • 19 Downloads

Abstract

This paper presents the results of an experimental study of a boundary layer disturbed by an incident shock for parameters which are characteristic of problems for flow about blade profiles in the final stages of high-power steam turbines.

Keywords

Boundary Layer Experimental Study Steam Final Stage Steam Turbine 

Notation

x

distance along the surface in question from the leading edge of the flat plate or profile

y

distance along the normal to the surface in question

X

dimensionless coordinate along interaction region

p

pressure

p∘

relative pressure change across the boundary layer

l

length of the interaction region

x+

coordinate of the first boundary-layer section at which pressure deviation occurs between the pressure at the outer edge of the boundary layer and the pressure in shock-free flow, i. e., it is the coordinate of the section where a deviation from the condition dp/dy=0

x

coordinate of section behind which the pressure rise above the shock-free flow pressure remains constant, or where the condition dp/dy=0 is established

δ

boundary-layer thickness

δ*

displacement thickness

δ**

momentum thickness

λ

reduced velocity

M

Mach number

R

Reynolds number

The subscript

0

stagnation parameters

1

flow which has not been disturbed by shock

2

flow behind the interaction region

the prime

the beginning of the interaction region

two primes

the maximum pressure in the shock at the edge of the boundary layer

the minus script

the subsonic part of the boundary layer

the superscript

asterisk

parameters associated with the shock

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References

  1. 1.
    E. A. Gukasova, M. I. Zhukovskii, A. M. Zavadovskii, L. M. Zysina-Molozhen, N. A. Sknar, and V. G. Tyryshkin, Aerodynamic Improvement of Steam and Gas Turbine Blading [in Russian], Gosenergoizdat, Moscow-Leningrad, 1960.Google Scholar
  2. 2.
    L. M. Zysina-Molozhen, N. I. Paramonov, I. N. Soskova, I. B. Uskov, V. M. Tsvetkov, and I. G. Shapiro, “Experimental study of thermal and dynamic boundary layers relative to flow conditions past turbomachinery profile cascades,” Tr. TsKTI, no. 54, 1965.Google Scholar
  3. 3.
    V. A. Mironova, and I. G. Shapiro, “Programming the Ural-2 digital computer for calculation of two-dimensional flow parameters from interferogram analysis data,” Tr. TsKTI, no. 71, 1966.Google Scholar
  4. 4.
    I. G. Shapiro, “Interference method for determining two-dimensional profile cascade flow parameters,” Author's abstract of dissertation, [in Russian], Leningrad Polytechnic Institute im. M. I. Kalinin, 1960.Google Scholar

Copyright information

© Consultants Bureau 1972

Authors and Affiliations

  • G. S. Balandina
    • 1
  • L. M. Zysina-Molozhen
    • 1
  • L. A. Fel'dberg
    • 1
  • I. G. Shapiro
    • 1
  1. 1.Leningrad

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