Turbine blade assembly thermal barrier coating and preparation method thereof

A technology of turbine blades and thermal barrier coatings, which is applied in the surface coatings containing ceramic layers and its preparation, can solve problems affecting the thermal fatigue performance of holes, accelerate crack extension, thermal fatigue cracks, etc., and achieve long-term stable work, Improve the effect of high temperature oxidation resistance and cooling effect

Active Publication Date: 2017-11-14
BEIJING HUAQING GAS TURBINE & INTEGRATED GASIFICATION COMBINED CYCLE ENG TECH
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  • Application Information

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Problems solved by technology

The atmosphere containing carbon and other impurities generated in these two processes will inevitably remain in the base material near the cooling hole, reducing the oxidation resistance, thermal corrosion resistance and even mechanical properties of the base material surface.
In the second solution, the laser can only ablate the outer layer of the ceramic, and will produce a certain thickness of remelted layer, which will affect the thermal fati

Method used

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  • Turbine blade assembly thermal barrier coating and preparation method thereof
  • Turbine blade assembly thermal barrier coating and preparation method thereof
  • Turbine blade assembly thermal barrier coating and preparation method thereof

Examples

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Example Embodiment

[0046] Example 1:

[0047] figure 1 It is a perspective view of a turbine blade. The turbine blade assembly 10 includes a blade body 12, an edge plate 14 (including two upper and lower edge plates), and cooling holes 18.

[0048] see figure 2 This embodiment discloses a thermal barrier coating system for high-temperature alloy substrates. The base body is a gas turbine turbine guide blade assembly, which mainly provides sufficient strength under high temperature and mixed gas atmosphere, and plays a role of a structural member. The preparation process of each layer of the coating mainly includes:

[0049] In the first step, a local MCrAlY bonding layer is prepared. The principle of selecting the application area of ​​the adhesive layer is: first exclude the area around the cooling hole, and the specific excluded area is the area within about 10 mm on the left and right sides of the cooling hole array. Then select the areas where the outer surface of the blade body and the edge p...

Example Embodiment

[0057] Example 2

[0058] see image 3 . The base body is a gas turbine turbine guide blade assembly, which mainly provides sufficient strength under high temperature and mixed gas atmosphere, and plays a role of a structural member. The coating process on the guide vane assembly 30 is:

[0059] In the first step, chemical vapor deposition is applied to the entire blade and the outer surface area of ​​the edge plate.

[0060] In this embodiment, the aluminide layer 26 adopts a typical chemical vapor deposition process in which the reactant gas is mixed externally and then passed into the chamber to prepare the platinum modified aluminide coating. The specific process steps are: first electrochemically deposit a layer of platinum-nickel alloy on the surface of the substrate 22, and then perform platinum diffusion annealing before chemical vapor deposition aluminizing. Since aluminum diffuses inward through the platinum layer, the resulting coating is on the coating- The gas-phase ...

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Abstract

The invention provides a turbine blade assembly thermal barrier coating. The turbine blade assembly thermal barrier coating comprises a bonding layer, an aluminide layer, an aluminum oxide layer and a ceramic layer which are sequentially arranged in an upward mode from a turbine blade assembly base material or comprises an aluminide layer, a bonding layer, an aluminum oxide layer and a ceramic layer which are sequentially arranged. The bonding layer is a MCrAlY layer, and M represents one or two or three sorts of nickel, cobalt and iron. According to the thermal barrier coating system provided by the invention, the high-temperature oxidation resistance, thermal corrosion resistance and endurance property of the thermal barrier coating are improved on the premise that the thermal barrier effect of the thermal barrier coating is guaranteed, and thus the service life of a turbine blade assembly is prolonged. By means of the thermal barrier coating system prepared through the method, the weight of the blade assembly can be lowered obviously, and therefore the creep degree of the assembly by tension of the turbine blade assembly in the high-speed rotating process is decreased and the service life of the turbine blade assembly is prolonged.

Description

technical field [0001] The invention belongs to the field of surface treatment of metal materials, and in particular relates to a surface coating containing a ceramic layer and a preparation method thereof. Background technique [0002] A gas turbine is a well-developed and widely used mechanical device that converts the chemical energy of fuel into heat and mechanical energy to drive equipment or facilities such as jet aircraft, large ships, generator sets, and fluid pumps. In order to improve energy utilization efficiency, the metal materials used for the hot end parts of gas turbines are often close to or reach the critical state of their thermal stability when the equipment is working, that is, in order to improve the efficiency of gas turbines, the temperature of the turbine inlet is greatly increased. In fact, the first stage moving and guide vanes of advanced gas turbines are often in a mixed gas atmosphere higher than their melting point when they work. Only because...

Claims

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Application Information

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IPC IPC(8): C23C28/00
CPCC23C28/3215C23C28/345Y02T50/60
Inventor 于大千段方苗张涛刘伟
Owner BEIJING HUAQING GAS TURBINE & INTEGRATED GASIFICATION COMBINED CYCLE ENG TECH
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