Active control device for blade tip clearance of axial flow gas turbine

A technology of active control and blade tip clearance, applied in the direction of machines/engines, mechanical equipment, engine components, etc., can solve the problem that the compressor cannot be dynamically controlled, and achieve the effects of simple processing, increased blade tip clearance, and convenient installation
CN112160800AActive Publication Date: 2021-01-01HANGZHOU TURBINE POWER GRP
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
HANGZHOU TURBINE POWER GRP
Publication Date
2021-01-01

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Abstract

The invention relates to an active control device for a blade tip clearance of an axial flow gas turbine. The active control device comprises a gas compressor cylinder, a memory alloy mechanism, gas compressor moving blades and an active control mechanism, wherein a groove is formed in the surface of the inner wall of the gas compressor cylinder in the circumferential direction of the inner wall;the memory alloy mechanism is mounted in the groove in a sliding manner in the circumferential direction of the inner wall of the gas compressor cylinder, and is axially fixed along the inner wall ofthe gas compressor cylinder; the active control mechanism comprises a cooling fan, a heating resistance wire and a thermocouple sensor; the cooling fan is used for providing air flow for heat dissipation for the memory alloy mechanism; the heating resistance wire is used for heating the memory alloy mechanism; and the thermocouple sensor is used for detecting the real-time temperature of memory alloy and converting the temperature into an electric signal. The active control device solves the problem that a gas compressor in the prior art cannot be dynamically controlled in a start-stop stage and an operation stage, and the deformation temperature of a memory alloy part is dynamically controlled through the active control mechanism, so that optimization of the blade tip clearance is realized, and the efficiency of the gas compressor is improved.
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Description

technical field

[0001] The invention relates to the technical field of gas turbines, in particular to an active control device for blade tip clearance of an axial flow gas turbine. Background technique

[0002] The gas turbine compressor blade tip clearance is related to the safety and economy of the unit. During the start-up and stop of the compressor, due to the different radial deformation rates of the compressor rotor and the stator, there is a possibility of rubbing in the compressor blade tip clearance; In steady-state operation at rated load, the smaller the blade tip clearance, the higher the efficiency of the compressor. However, the start-stop process and the change of the blade tip clearance at rated load need to be considered comprehensively in the design of the compressor, which often leads to failure to take into account both safety and economy. The active control technology of heavy-duty gas turbine blade tip clearance is mainly the optimization of Siemens’ hy...

Claims

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