High-temperature axial-flow type tail gas turbine

Abstract

The invention provides a high-temperature axial-flow type tail gas turbine which belongs to the field of energy recovery. The device adopts a structure form of axial air inlet and radial upward or downward exhaust and comprises an air inlet casing (1), a first stage guide vane (2), a second stage guide vane (3), a rotor (4), a transition casing (20), an exhaust casing (5), a bearing system (6) and a base (7). A moving vane adopts a vane shroud in a V-shaped structure, and a surrounding belt of the top of the moving vane is sealed by a honeycomb in an integral domain structure. The invention is suitable for tail gas with higher inlet pressure and low flowing quantity and the tail gas with solid particles, has higher efficiency, improves the heat insulation efficiency by 4% compared with the existing tail gas turbine products, and improves the sealing reliability of the moving vane and the surrounding belt of the top of the moving vane.

Description

technical field [0001] The invention belongs to the field of energy recovery, and in particular relates to a high-temperature axial flow exhaust gas turbine. Background technique [0002] The medium of the exhaust gas turbine is usually the exhaust gas from oil refining, chemical, and metallurgical installations, which has the characteristics of high temperature, solid particles, and corrosiveness. The exhaust gas turbine converts the pressure energy in the exhaust gas into mechanical work, and drives the compressor or generator to recover energy. At present, there are some tail gas turbine products in China, such as tail gas turbines for high-temperature nitric acid plants and flue gas turbines for oil refinery catalytic cracking units. Structure, axial air intake, radial exhaust; the rotor blade tip has no blade crown, the blade tip and the shroud are provided with a large blade tip gap, and there is no sealing measure. The main reasons for these characteristics are: gen...

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Problems solved by technology

However, the structure is not a whole ring structure, the strength and rigidity are poor, and it can only avoid the leakage of interstage gas

[0004] The patent with the publication number CN2469184 provides a structure of a steam turbine motor blade with its own shroud damping sheet. When running at high speed, the strength margin is too small. This form is suitable for steam turbines, but it cannot be used for high-speed turbines with solid particles in the medium; the gap between the shroud and the shroud is limited by the sealing properties and there is a certain amount of tip air leakage. losses, especially when the blades are short, can have a large impact on turbine efficiency

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