EFFECT OF HYSTERESIS IN AXIAL COMPRESSORS OF GAS-TURBINE ENGINES-Reference-Cited by-同舟云学术

EFFECT OF HYSTERESIS IN AXIAL COMPRESSORS OF GAS-TURBINE ENGINES

Published:2012-12-24 Issue:4 Volume:16 Page:97-102
ISSN:1648-7788
Container-title:Aviation
language:
Short-container-title:

Author:

Kulyk Mykola¹,Lastivka Ivan¹,Tereshchenko Yuri¹

Affiliation:

1. National Aviation University, 1 Kosmonavta Komarova Ave., 03680 Kiev, Ukraine

Abstract

The phenomenon of separated flow hysteresis in the process of the streamlining the axial compressor of gas-turbine engines is considered. Generalised results of research on the occurrence of hysteresis in the aerodynamic performance of compressor grids and its influence on the performance of the bladed disks of compressors that operate in real conditions of periodic circular non-uniformity are demonstrated.

Publisher

Vilnius Gediminas Technical University

Subject

Aerospace Engineering

Reference7 articles.

1. Chang , P. K. 1979 . Control of Flow Separation . Moscow : Mir . 365 p. (in Russian) .

2. RAISING GAS-DYNAMIC STABILITY MARGIN OF AXIAL AND CENTRIFUGAL COMPRESSOR STAGES BY MEANS OF VANED DIFFUSER BOUNDARY LAYER CONTROL / DUJŲ DINAMINIO STABILUMO RIBOS AŠINIO IR IŠCENTRINIO KOMPRESORIAUS PAKOPOSE DIDINIMAS ATLIEKANT STABILIZUOTO DIFUZORIAUS PARIBIO SLUOKSNIO KONTROLĘ

3. Liblein , S. ; Randebuseh , W. 1956 . Theoretical Loss Relations for Low-Speed Two-Dimensional-Cascade Flow . NASA . 3362 .

4. On boundary layers associated with oscillating streams

5. Schlichting , G. 1969 . Boundary Layer Theory . Moscow : Nauka . 413 p. (in Russian) .

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