Characteristics of surge and rotating stall in a three-stage axial flow compressor using shock tube

Daisuke Morita, Yutaka Fujita, Yutaka Ohta, Eisuke Outa

研究成果: Conference contribution

抄録

Transient characteristics as well as unsteady cascade flow fields of a three-stage axial flow compressor with compression plane wave injection from the compressor downstream were experimentally investigated by detail measurements of casing wall pressure fluctuations and unsteady velocity. The main feature of tested compressor is a shock tube facility connected in series to the compressor outlet duct in order to supply a compression plane wave which simulates the sudden rise of the compressor back pressure in a gas turbine system. Research attention is mainly focused on the unsteady behavior of surge and rotating stall coexistence phenomenon, and influence of the compression plane wave injection on the compressor operating conditions. When the compressor is connected to the capacity tank, surge and rotating stall occur simultaneously according to the capacitance increment of the whole compression system. The surge cycle changes irregularly with a throttling of the valve installed just behind the compressor and several different types of surge behaviors are observed. Furthermore, even though the compressor is operating under the stable condition, it goes into surge by injecting the compression plane wave.

本文言語English
ホスト出版物のタイトルASME-JSME-KSME 2011 Joint Fluids Engineering Conference, AJK 2011
ページ595-602
ページ数8
PARTS A, B, C, D
DOI
出版ステータスPublished - 2011 12 1
イベントASME-JSME-KSME 2011 Joint Fluids Engineering Conference, AJK 2011 - Hamamatsu, Japan
継続期間: 2011 7 242011 7 29

出版物シリーズ

名前ASME-JSME-KSME 2011 Joint Fluids Engineering Conference, AJK 2011
番号PARTS A, B, C, D
1

Conference

ConferenceASME-JSME-KSME 2011 Joint Fluids Engineering Conference, AJK 2011
国/地域Japan
CityHamamatsu
Period11/7/2411/7/29

ASJC Scopus subject areas

  • 流体および伝熱

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