Computational and experimental study of air bleeding from the compressor intermediate stage effect on its characteristics

Thermal engines, electric propulsion and power plants for flying vehicles


Аuthors

Kizeev I. S.*, Kozhemyako P. G., Ezrokhi Y. A.**

Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia

*e-mail: 30105@ciam.ru
**e-mail: yaezrokhi@ciam.ru

Abstract

Recently in connection with the studies of three-stream schemes of adaptive cycle engines the fan with air bleeding is considered as a basic part of three-stream adaptive engines. The values of such bleedings herewith can reach 15-20 % and more. Under such conditions, this pressuring element representation as a set of two compressor stages (the first – from the inlet to the bleeding point, the second – from the bleeding point to the outlet), with their own characteristics independent from the bleeding value, may lead to significant errors in determining integral characteristics of a power plant with a three-stream engine. In this connection, the problem of adequate characteristics setting of such adaptive fan acquires considerable importance.

The article presents the results of a compressors characteristics behavior changing estimation as a result of the air bleeding from an intermediate stage. Physical bases of the air bleeding effect on vane machines characteristics are presented as well.

Two compressors with different numbers of stages are considered: the three-stage compressor with air bleeding of 0 to 15% from behind the first or second stage (relative to the air consumption at the compressor inlet), and the six-stage with compressor with air bleeding of 0 to 10% from behind the third stage.

The obtained results of numerical computation and experimental data revealed that the additional air bleeding at maximum frequencies did not lead to the pressure line shift of a group of stages to the bleeding point. However, the pressure lines of the stages beyond the bleeding point were being shifted to the right and downward with the increase in the bleed air. At the lower rotation frequencies, the additional air bleeding did not lead to the pressure line shift for the first group, but it led to the significant shift of the pressure line to the right and upward for the second group.

This stratification of the pressure lines of the second group, following the bleeding point, can be explained as follows. While tapping a part of propellant from the multistage compressor airflow duct the operating point shifts right and downward (or downward in case of vertical branch) on the pressure line of the characteristic of the first group of stages by the lower values of pressure ratio, ensuring lower temperature levels of the air fed to the inlet of the second group of stages. This leads to the operating point shift on characteristic of the second group towards the larger reduced values of air consumption. Besides, the impact of non-uniform field of parameters at the inlet of this group of stages, appeared due to the air bleeding at the peripheral area of the blades, leads to the operating point shift in the same direction.

Keywords:

compressor, compressor characteristics, pressure line, compressor efficiency, air tapping

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