FLOW STABILIZATION STRUCTURE OF COMPRESSOR FOR A GAS TURBINE

摘要

PURPOSE: A flow stabilization structure of a compressor for a gas turbine is provided to stabilize the flow through change of flowing speed and a flow angle on a leakage of a hub by installing a wing in a blade hub in order to utilize the leakage of compressed air between a vane and the hub. CONSTITUTION: A flow stabilization structure of a compressor (1) for a gas turbine comprises a casing (4), a hub (2), a plurality of vanes (5), and a flow stabilization unit (6). The casing is formed in the compressor. The hub comprises a plurality of blades (3) formed at regular intervals on an inner surface of the casing in order to rotate. The vane wraps the hub at regular intervals on the inner surface of the casing. The flow stabilization unit is installed in the hub so that the flow is stabilized by changing a flow angle and flow speed of a leakage of the hub. [Reference numerals] (AA) Air