14th European Conference on Turbomachinery Fluid dynamics & Thermodynamics

Paper ID:

ETC2021-639

Main Topic:

Axial compressors

Authors

Joseph Moubogha Moubogha - Univ. Lille, CNRS, ONERA, Arts et Métiers Institute of Technology, Centrale Lille, UMR 9014 - LMFL - Laboratoire de Mécanique des Fluides de Lille - Kampé de Fériet, F-59000 Lille, F
Gabriel Margalida - Univ. Lille, CNRS, ONERA, Arts et Métiers Institute of Technology, Centrale Lille, UMR 9014 - LMFL - Laboratoire de Mécanique des Fluides de Lille - Kampé de Fériet, F-59000 Lille, France
Pierric Joseph - Univ. Lille, CNRS, ONERA, Arts et Métiers Institute of Technology, Centrale Lille, UMR 9014 - LMFL - Laboratoire de Mécanique des Fluides de Lille - Kampé de Fériet, F-59000 Lille, France
Olivier Roussette - Univ. Lille, CNRS, ONERA, Arts et Métiers Institute of Technology, Centrale Lille, UMR 9014 - LMFL - Laboratoire de Mécanique des Fluides de Lille - Kampé de Fériet, F-59000 Lille, France
Antoine Dazin - Univ. Lille, CNRS, ONERA, Arts et Métiers Institute of Technology, Centrale Lille, UMR 9014 - LMFL - Laboratoire de Mécanique des Fluides de Lille - Kampé de Fériet, F-59000 Lille, France

Abstract

Stall and surge are strong limitations in the operating range of compressors and thus one of the major limit in the jet engine performance. One of the promising way to push the stability limit of the compression machines is to inject a small amount of flow at blade tip. The test-bench, support of this work, is a single-stage axial compressor whose main parameters are given in Table 1. The compressor can be led to stall by throttling a valve located downstream to the machine. TABLE 1: COMPRESSOR PARAMETERS Rotational speed 3200 rpm Design mass flow rate at 3200rpm 5.3 kg/s Design total to static pressure ratio at 3200 rpm 1.03   Rotor blade number 30   Stator blade number 40   Casing diameter 550 mm Rotor tip chord 84 Mm Rotor tip stagger angle 54 ° Rotor tip gap 0.5 mm The compressor has been recently equipped with 40 actuators connected to an auxiliary compression system. They are able to generate high speed jet blowing just at the tip of the rotor blades. The opening of each actuator is controlled by an electromagnetic valve. This allows to generate continuous or pulsed jet with frequency up to 500 Hz. The performance of the system will be evaluated through a large parametric study (frequency, duty cycle, flow rate injected, blowing angle). A special attention will be paid on the energy balance of the control system and to the modification of the flow induced by the control strategy.







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