CN101935818A

CN101935818A - Functionally gradient coating of rotor vane

Info

Publication number: CN101935818A
Application number: CN2010102768690A
Authority: CN
Inventors: 李永; 舒畅
Original assignee: Beijing Institute of Technology BIT
Current assignee: Beijing Institute of Technology BIT
Priority date: 2010-09-09
Filing date: 2010-09-09
Publication date: 2011-01-05

Abstract

The invention discloses a method for preparing a gradient coating of a rotor vane of an aircraft engine and the like by using a self-spreading synthesis method. 20 to 30 percent of titanium carbide (TiC), 10 to 15 percent of titanium nitride (TiN), 10 to 15 percent of nickel (Ni), 5 to 10 percent of molybdenum (Mo), 5 to 10 percent of tungsten (W) and 20 to 30 percent of aluminum oxide are distributed according to a proportion. A functionally gradient coating material is characterized in that the prepared gradient coating has mild thermal stress and has no obvious interface. The gradient coating has good thermal shock resistance and granule impact resistance at the high temperature of 1,300 DEG C, is applicable in the high-temperature protection field, and solves the problems of thermal shock, granule impact and the like of the gradient coating applied in the high-temperature protection field.

Description

A kind of functionally gradient coating of spinner blade

Technical field

The invention belongs to functionally gradient coating, Functionally Graded Materials technology preparation field, particularly a kind of self-spread synthesizing method wherein prepares the method for spinner blade ceramic metal functionally gradient coating.

Background technology

In order to obtain better Energy efficiency and bigger motor power, aeroengine rotor blade working temperature is up to more than 1300 ℃, only depend on the raising of blade material physical and mechanical property and the improvement of structure design, can't satisfy the demand of the aircraft engine industry of high speed development, high temperature protecting against shock coating technology is essential.Common high-temperature protection coating thermal stresses is excessive, and generation damage inefficacy, and coating heat shock resistance easily, granule impact performance can't satisfy the demand of aircraft engine.Functionally gradient coating material moiety becomes Gradient distribution, and physical and mechanical property changes continuously, and this variation can be satisfied the requirement of the Working environment of thermal shocking, granule impact to material.

Summary of the invention

Purpose of the present invention provides the method that a kind of self-spread synthesizing method prepares the ceramic metal gradient cladding, and the object of the invention is to provide for the aeroengine rotor blade the efficient coating of a kind of life-span length, high temperature resistant impact, anti-granule impact.Blade of aviation engine is worked in high temperature and granule impact environment throughout the year, aircraft is subjected to the effect of shock load in taking off and landing, under the effect of mechanics factors such as impact, the life-span of spinner blade reduces significantly, and the Working environment of safety has been caused great threat.Therefore, by effective preventive means, the component's life that improves aircraft has become attractive research direction.

The invention provides a kind of gradient cladding that is used for the aeroengine rotor blade, this coating is to be made of pottery and metal.Gradient cladding composition provided by the invention is TiC 20%～30%, TiN 10%～15%, Ni 10%～15%, Mo 5%～10%, W 5%～10%, Al ₂O ₃20%～30%.

The invention provides the gradient cladding that is used for the aeroengine rotor blade, the ceramic layer of its preparation is used the self propagating high temperature synthesis technique always, and power is 20～37kW.Flame plating technology is adopted in the preparation of metal level, and the fuel of its flame plating is kerosene, propane, acetylene or other inflammable gas.The spinner blade gradient cladding that is used for provided by the invention is that the sphere that gas atomization prepares spreads powder certainly from spreading synthesis technique its preparation aluminum oxide, aluminium sesquioxide powder that coating adopted.Size range is 180～360 orders.Provided by the invention the powder size scope is 90～280 orders from spreading its TiC of synthesis technique, TiN powder, and that controls reaction raw materials spreads acceleration certainly at 100～1200m/s ², the bias voltage of coating is-90～120V, vacuum tightness is 0.12～0.35Pa.This gradient cladding is because an amount of adding of Ni, Mo, W, effectively strengthened the combination of coating interface, the quantity and the diameter of hole among TiN, the TiC have been reduced, eliminated coating inside holes and defective, improved the compactness of coating, under 1300 ℃ of high temperature, has high compactness, high shock resistance, thermotolerance and do particle erosion ability is applicable to the protective coating of aeroengine rotor blade.From spreading spraying equipment electric current 470A, voltage 72V, powder feeding rate are 102g/min, spread distance certainly and are 53mm, and coat-thickness is 0.001～0.2mm.

Advantage of the present invention is: technology is simple, can prepare the multiple different spinner blade gradient cladding that requires.Utilize composition allotment and the control of process parameters not to need under the prerequisite that equipment is transformed, solved TiC, TiN gradient cladding in problems such as the pin hole in solar heat protection impact and anti-ion erosion field, holes.

Description of drawings

Fig. 1 is the three-dimensional picture of aeroengine rotor blade;

Fig. 2 is the three-dimensional picture of blade of aviation engine;

Fig. 3 is the hierarchical diagram of blade of aviation engine gradient cladding.

Embodiment:

Embodiment 1:TiC powder 15g, Al ₂O ₃Powder 27g, TiN powder 109g, Ni powder 7g, Mo powder 29g, W powder 62g mixes, and the wall thickness 6mm that packs in the shape rifle of long 120mm, is stuck in from spreading on the synthesizer.The shape rifle is contained on the self-propagating combustion machine lights TiC, TiN, Al ₂O ₃Prolonging gradient direction changes.

Embodiment 2:TiC powder 53g, TiN powder 96g, particle diameter is less than 102 μ m, Al ₂O ₃Powder 311g, Ni powder 102g, Mo powder 93g, W powder 28g mix to make and satisfy that particle-resistant is ballistic, the ceramic metal gradient cladding of high temperature resistance.

Claims

1. a self-spread synthesizing method prepares the spinner blade gradient cladding.It is characterized in that TiC, TiN powder and Al ₂O ₃Powder, Ni powder, Mo powder, W powder mix, and under the self propagating high temperature effect, have generated aluminum oxide and each molten metal layering, and metallographic phase, ceramic phase become graded according to the different beginning of density layering.After the cooling, remove impurity and obtain functionally gradient coating.

2. press claims 1 described method, it is characterized in that accounting for 30%～45% of powder gross weight with TiC, TiN powder.

3. it is described to press claims 1, it is characterized in that adopting TiC, TiN mixed powder, and TiC, TiN are in following formula ratio: TiC/TiN/Al ₂O ₃-Ni/Mo/W=TiC+TiN+Al ₂O ₃+ X _Ni+ Y _Mo+ Z _W, require X+Y+Z between 20%～35%.

4.Ni, the particle diameter of Mo, W is respectively 22 μ m, 28 μ m, 18 μ m, purity is 99.2%.