Turbine blade
A technology for turbine blades and protective layers, which is applied in the field of turbine blades with high-temperature corrosion and erosion resistance. It can solve the problems of turbine blade erosion, high-temperature vulcanization, and short service life, so as to improve the erosion resistance and high temperature resistance. Corrosion performance, effect of prolonging working life
Inactive Publication Date: 2014-12-03
AVIC PST NANFANG GAS TURBINE COMPLETE MFG & INSTALLATION
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Problems solved by technology
[0003] The purpose of the present invention is to provide a turbine blade to solve the problem that when the ground gas turbine is used in an environment with poor fuel quality (higher impurity content and sulfur content), the turbine blade is easily subjected to erosion and high-temperature vulcanization of high-temperature gas, resulting in Technical problems with too short service life
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[0018] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.
[0019] Please refer to figure 1 , the surface of the turbine blade 1 in the preferred embodiment of the present invention is evenly covered with a layer of anti-corrosion protective layer 2 . The material of the turbine blade 1 is a nickel-based superalloy. The composition of the anti-corrosion protective layer 2 includes MCrAlY alloy powder and aluminum oxide powder (Al2O3); wherein, the MCrAlY alloy powder includes chromium (Cr), aluminum (Al), M and rare earth (Y), and M is nickel (Ni) , cobalt (Co) or NiCo. Chromium (Cr) or aluminum (Al) accounts for 5-25% of the weight of the MCrAlY alloy powder. Aluminum oxide (Al2O3) powder accounts for 0.5-5% of the weight of the anti-corrosion protection layer 2 .
[0020] The anti-corrosion protection ...
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Abstract
The invention provides a turbine blade. A corrosion-resistant protective layer is sprayed and coated on the turbine blade; components of the corrosion-resistant protective layer comprise MCrAlY alloy powder and aluminum oxide powder, and the weight ratio of the aluminum oxide powder is 0.5-5%, wherein Y is rear earth, and M is Ni, Co or NiCo. The surface of the turbine blade provided by the invention is provided with the corrosion-resistant protective layer, so that the washing-resistant performance and high-temperature-corrosion resistant performance of the turbine blade are improved, thus the working service life of the blade is prolonged.
Description
technical field [0001] The invention relates to the field of turbine blades, in particular to a turbine blade of an aeroderivative gas engine with high-temperature corrosion and erosion resistance. Background technique [0002] At present, the fuel used by the aero-derivative low-power gas turbines produced by domestic enterprises is gas with high impurity content such as anxiety gas and yellow phosphorus tail gas. Due to the anxiety gas, yellow phosphorus tail gas and other gases not only contain sulfur, but also some impurities, and the air at the intake end also contains fine particles of dust, sodium salts and vanadate harmful substances, which will cause high-temperature vulcanization of the turbine blades of the gas turbine at high temperatures Corrosion and thermal corrosion, affecting the life of turbine blades. Contents of the invention [0003] The purpose of the present invention is to provide a turbine blade to solve the problem that when the ground gas turbin...
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IPC IPC(8): F01D5/28C23C4/12C23C4/06C23C4/073C23C4/129
Inventor 王辉周建罗付浩
Owner AVIC PST NANFANG GAS TURBINE COMPLETE MFG & INSTALLATION