Annular flow duct for a turbomachine through which a main flow can flow in the axial direction

A flow channel, fluid machinery technology, applied in the components of pumping devices for elastic fluids, mechanical equipment, machines/engines, etc., can solve problems such as suboptimal flow direction of tributaries
CN101460707AActive Publication Date: 2009-06-17SIEMENS ENERGY AG
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
SIEMENS ENERGY AG
Publication Date
2009-06-17

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Abstract

The invention relates to an annular flow duct (18) for a turbomachine, said flow duct (18) being arranged concentrically about a machine axis (2) running in the axial direction and being defined by a boundary wall (22, 24) of circular cross section for directing a main flow (26), wherein the boundary wall (22, 24) has a plurality of return flow passages (46) which are distributed over its circumference and through which in each case a partial flow (49) which can be detached from the main flow (26) at a bleed position (50) can be returned to the main flow (26) at a feed position (52) situated upstream of the bleed position (50), and having aerofoils (32), arrranged radially in the flow duct (18), of a blade ring, the aerofoil tips (42) of which lie opposite the boundary wall (22, 24), with a gap being formed in each case, wherein the aerofoils (32) are movable in a predetermined rotation direction (U) along the circumference of the boundary wall (22 ,24). In order to specify a compressor which is insensitive to pumping and flow separations, it is proposed that as viewed in rotation direction (U) the bleed position (50) of each return flow passage lie upstream of the corresponding feed position (52).
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Description

technical field

[0001] The invention relates to a flow channel for a compressor, which is arranged concentrically around a machine axis extending in the axial direction and is delimited for the axially guided flow by a boundary wall having a circular cross-section, wherein the The dividing wall has a plurality of return channels distributed over its circumference, through which the partial flows which can be separated from the main flow at the withdrawal point can be returned to the feeding point upstream of the withdrawal point. is supplied to the main flow, and the flow channel has a blade ring radially arranged in the flow channel, the blade tip of which is correspondingly demarcated from the The walls are opposite. Background technique

[0002] Gas turbines and their principles of operation are well known. The air sucked in by the compressor of the gas turbine is compressed there and then mixed with fuel in the combustor. This mixture flowing into the combustion chamb...

Claims

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