CN103774134A - High temperature component with thermal barrier coating for gas turbine - Google Patents
High temperature component with thermal barrier coating for gas turbine Download PDFInfo
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- CN103774134A CN103774134A CN201310508420.6A CN201310508420A CN103774134A CN 103774134 A CN103774134 A CN 103774134A CN 201310508420 A CN201310508420 A CN 201310508420A CN 103774134 A CN103774134 A CN 103774134A
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- combustion turbine
- temperature component
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
- C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/08—Metallic material containing only metal elements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/182—Transpiration cooling
- F01D5/183—Blade walls being porous
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- General Engineering & Computer Science (AREA)
- Inorganic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The object of the present invention is to provide a high temperature component with a thermal barrier coating for a gas turbine. The most principal feature of the high temperature component having a thermal barrier coating and a cooling structure is as follows: micro passages are provided inside in an alloy bottom layer and a thermal insulation ceramic layer of the thermal battier coating, and are in communication from a substrate side to a surface side. Moreover, a partial amount of coolant of a coolant for cooling the high-temperature component is caused to flow out to the outside of the high-temperature component via these micro passages. The employment of the structure like this makes it possible to expect the implementation of a high-temperature component's heat-resistant-temperature enhancement effect based on the transpiration cooling effect.
Description
Technical field
The present invention relates to the internal combustion turbine high-temperature components such as the rotor and stator blade, burner, shroud (shroud) of the internal combustion turbine of the heat insulating coat with excellent heat resistance.
Background technology
Internal combustion turbine is to raise the efficiency as object, and operating temperature raises year by year.In order to tackle the high temperature of operating temperature, high-temperature component of gas turbine uses the material of excellent heat resistance, and has adopted and utilize the fluid coolant such as air or steam to carry out cooling structure to the surperficial opposing face that is exposed to combustion gases.In addition, for the object that temperature environment is relaxed, effects on surface is implemented the heat insulating coat (Thermal Barrier Coating: hereinafter referred to as TBC) being made up of the pottery of low heat conductivity.Although also according to working conditions and difference,, general by application TBC, base material temperature can reduce by 50～100 ℃.For example, in Japanese kokai publication sho 62-211387 communique (patent documentation 1) etc., disclose: with respect to base material, across MCrAlY alloy layer, there is the TBC of the thermofin that the PSZ of and excellent heat resistance low by thermal conductivity forms.At this, M represents at least a kind in chosen from Fe (Fe), Ni and Co, and Cr represents chromium, and Al represents aluminium, and Y represents yttrium.
The high-temperature component of gas turbine with TBC and cooling structure like this demonstrates excellent thermotolerance, still, in order further to improve the performance of internal combustion turbine, wishes to adopt higher cooling (transpiration cooling) mode of dispersing of cooling efficiency.Dispersing cooling is by fine channel (being generally porous insert), micro-heat-eliminating medium to be oozed out equably from the whole surface of parts from the surface of high-temperature component, thereby carries out cooling method expeditiously.For example, in Japanese kokai publication hei 10-231704 communique (patent documentation 2), TOHKEMY 2010-65634 communique (patent documentation 3), disclose and on porous metal, formed porous ceramic layer and adopt and disperse cooling high-temperature component of gas turbine.In addition, in TOHKEMY 2005-350341 communique (patent documentation 4), disclose in the time of casting and made in porous ceramics and the integrated structure of refractory alloy base material, adopted the high-temperature component of gas turbine of dispersing cooling structure.
Prior art document
Patent documentation
Patent documentation 1: Japanese kokai publication sho 62-211387 communique
Patent documentation 2: Japanese kokai publication hei 10-231704 communique
Patent documentation 3: TOHKEMY 2010-65634 communique
Patent documentation 4: TOHKEMY 2005-350341 communique
Summary of the invention
The technical problem that invention will solve
In above-mentioned prior art, although adopted the thermal insulation ceramics layer of TBC in a part, in arbitrary known case, be equivalent to TBC alloy underlayer layer be not film but with porous metal replace, or be equivalent to alloy underlayer layer be omitted.This is because be difficult to use the film of alloy underlayer in the past to form the fine path as the stream of heat-eliminating medium.In TBC, thermal insulation ceramics layer is born the hot effect of blocking from combustion gases, and the effect that can expect that apparent thermal conduction is suppressed lowlyer and thermal stresses is relaxed, therefore, has adopted porous ceramic layer.On the other hand, alloy underlayer is born and is guaranteed that the closely sealed of ceramic layer and base material and protection base material are not subject to the oxidation of combustion gases and the effect of corrosion, have adopted finer and close tissue.Therefore, for realize by TBC with disperse the high-temperature component of cooling combination, need to from the in the past different alloy underlayer with heat-eliminating medium stream.
Therefore, the object of the invention is to realize and there is the alloy underlayer that is suitable for dispersing cooling fine heat-eliminating medium stream, provide possess use this alloy underlayer disperse refrigerating function and heat insulating coat, the internal combustion turbine high-temperature component of excellent heat resistance.
For the means of technical solution problem
The present invention is in view of above-mentioned technical problem, a kind of internal combustion turbine high-temperature component is provided, this internal combustion turbine has heat insulating coat with high-temperature component on the substrate surface of combustion gases that is exposed to high temperature, this heat insulating coat is provided with alloy underlayer, and further on the surface of this alloy underlayer, be provided with thermal insulation ceramics layer, and this internal combustion turbine has the cooling structure that uses fluid coolant with high-temperature component, this internal combustion turbine is characterised in that with the topmost of high-temperature component: in alloy underlayer and thermal insulation ceramics layer, be provided with the fine path being communicated with from base material lateral surface side, a part of parts being carried out to cooling refrigerant is flowed out to parts are outside by these fine paths.
Invention effect
In the present invention, the fine path being communicated with from base material lateral surface side is set in the alloy underlayer of TBC and thermal insulation ceramics layer, a part of parts being carried out to cooling refrigerant is flowed out to parts are outside by these fine paths, and thus, TBC, particularly alloy underlayer are by cooling expeditiously.In addition, refrigerant from the whole surface uniform of high-temperature component ooze out, thus, can expect even and high efficiency film cooling performance.By these effects, have the following advantages: even rise in the part temperatures owing to accompanying with the high temperature of burning gas temperature, prior art is difficult to, under the harsh condition of application, also can use.In addition, use the internal combustion turbine internal combustion turbine of high-temperature component with heat insulating coat of the present invention and cooling structure, have and can under higher temperature, turn round, and the advantage that can raise the efficiency.
Accompanying drawing explanation
Fig. 1 is the schematic cross-section that represents the structure of the internal combustion turbine high-temperature component with heat insulating coat of the present invention and cooling structure.
Fig. 2 is the schematic cross-section that represents the structure of internal combustion turbine.
Embodiment
Below, the present invention is described in detail to use accompanying drawing.
The present invention, as shown in Figure 1, is on base material 1, to be provided with alloy underlayer 2, and further in this alloy underlayer 2, is provided with the structure of thermal insulation ceramics layer 3.In base material 1, be provided with multiple cooling hole 4, this cooling hole 4 connects base material 1 from the heat-eliminating medium path of base material 1 to the surface that is provided with alloy underlayer 2.Alloy underlayer 2 is characterised in that to have following structure: lamination has multiple roughly spherical alloy powder particles 5, has the intergranular gap 6 that is communicated to coatingsurface from base material 1 side.In addition, be provided with thermal insulation ceramics layer 3 in alloy underlayer 2, thermal insulation ceramics layer 3 has many longitudinal slits 7.Arrive the fluid coolant 8 of alloy underlayer 2 by cooling hole 4 from the heat-eliminating medium path of base material 1, by the intergranular gap 6 in alloy underlayer, in alloy underlayer 2 internal diffusion, flow to face side, arrive thermal insulation ceramics layer 3, by the longitudinal slit 7 in thermal insulation ceramics layer, flow out from the surface of thermal insulation ceramics layer 3.
That base material 1 can use is Ni-based, the refractory alloy of cobalt-based or iron-based.That alloy underlayer 2 can be used is Ni-based, the refractory alloy of cobalt-based or iron-based, preferably uses MCrAlY alloy, and wherein M is any one or more in Fe, Ni and Co.MCrAlY alloy excellent in oxidation resistance, therefore preferred.
In addition, alloy underlayer 2 has following structure: lamination has multiple roughly spherical alloying pellets 5, has the intergranular gap 6 that is communicated to alloy underlayer 2 surfaces from substrate 1 side.In order to form the film of such structure, for example preferably use the roughly spherical powdered alloy of being manufactured by gas atomization as raw material, make powdered alloy and substrate surface high velocity impact and the method for lamination.Particularly, for example can use the methods such as plasma spraying process, HVOF (High Velocity Oxygen Fuel) (HVOF) method, cold spraying method.Wherein, most preferably use cold spraying method.
For form as feature of the present invention, have to exist and from base material 1 side, be communicated to the alloy underlayer 2 of the structure in the intergranular gap 6 of coatingsurface, such in electric arc spraying or flame plating, make at high temperature melting of alloy powder particle and with base material collision and in the method for lamination, the powder particle of melting flat and lamination significantly in the time colliding with base material, therefore, easily form disconnected pore (the so-called hole of holding one's breath).In addition, be heated in the powdered alloy of temperature of melting in atmosphere, can produce oxide compound on surface, this oxide compound can be sneaked in film and the oxidation-resistance of film is reduced.In addition, also can produce combination between particle because oxide compound is hindered, the problem that film strength reduces.
Therefore,, in the time forming the alloy underlayer 2 of heat insulating coat of the present invention, roughly spherical powdered alloy melting, the oxidation that does not preferably make to use as raw material, to maintain the state lamination of shape of subglobular originally.As such method, preferably can carry out in lower temperature the cold spraying method of film forming.But, even at low temperatures, in the time that particle speed becomes too fast, in the time colliding with base material, also can produce the flat of powder particle, it is fine and close that film becomes, and is communicated with pore and reduces, and therefore, can not form alloy underlayer 2 of the present invention, therefore, needs suitably to adjust filming condition.In addition,, by similarly suitably adjusting filming condition, also can use plasma spraying process, HVOF (High Velocity Oxygen Fuel) (HVOF) method etc.
Use the film endosome integration rate of the communication gap of the alloy underlayer 2 with the intergranular gap 6 being communicated with from base material lateral surface side of the present invention of above-mentioned one-tenth embrane method formation to be preferably 30～70% scope.In the time that the volume fraction in gap is less than 30%, the heat-eliminating medium amount of circulation is few, can not fully obtain dispersing cooling effect.On the other hand, in the time that the volume fraction in gap increases, cooling performance improves, but film toughness reduces, and in the time that the volume fraction in gap exceedes 70%, the damage of coating in use easily occurs.More preferably the scope that the volume fraction in gap is 40～60%.
In addition, heat insulating coat of the present invention, preferably alloy bottom 2 and thermal insulation ceramics layer 3 are all implemented thermal treatment after film forming.In alloy underlayer 2, utilize the solid phase diffusion being caused by thermal treatment that intergranular combination is strengthened, can improve thus film toughness.In addition, in thermal insulation ceramics layer 3, can expect to promote the opening of longitudinal slit, make the circulation of heat-eliminating medium become smooth.In order to prevent the oxidation of alloy underlayer 2, heat treating method preferably carries out in a vacuum.Although heat-treat condition also depends on coating and substrate material, more than roughly preferably keeping 2h more than 1000 ℃.In addition, as thermal insulation ceramics layer 3, be preferably the structure with many longitudinal slits 7, but also can use the vesicular structure that is endowed ventilation property by multiple pores.
Below, embodiment is described.
(embodiment 1)
As matrix, prepare 1 grade of rotor blade of internal combustion turbine, this rotor blade is Ni by Refractoloy IN738(16%Cr-8.5%Co-3.4%Ti-3.4%Al-2.6%W-1.7%Mo-1.7%Ta-0.9 %Nb-0.1%C-0.05%Zr-0.01%B-rest part, % by weight) make, there is path of cool air in inside.In rotor blade, by electrodischarge machining(E.D.M.), be processed with from matrix surface and connect the multiple cooling hole to internal cooling path.In addition, as raw material powder, prepare the roughly CoNiCrAlY powdered alloy (Co-32%Ni-21%Cr-8%Al-0.5%Y, % by weight) of spherical median size approximately 40 μ m that utilizes gas atomization to manufacture.Use cold spray apparatus, make the combustion gases path surface filming of raw material powder at rotor blade.With regard to filming condition, working gas uses nitrogen, uses gaseous tension 3MPa, 800 ℃ of gas temperatures, powder feeding amount 20g/min, the film forming condition apart from 15mm, implements film forming until the thickness of alloy underlayer 2 becomes about 0.3mm.Then,, on the base material 1 that is provided with alloy underlayer 2, use yttrium oxide PSZ (ZrO
2-8wt%Y
2o
3) powder, in atmosphere, utilize plasma spraying (the about 100kW of plasma power) that the thermal insulation ceramics layer 3 with longitudinal slit of the about 0.6mm of thickness, void content approximately 8% is set.As filming condition now, preheating temperature is approximately 800 ℃, and the translational speed of spray gun is 30m/min, and spray distance is 90mm, and heat flux is about 0.4MW/m
2.Further, to forming the rotor blade after thermal insulation ceramics layer 3, implement in a vacuum the thermal treatment of 1120 ℃ × 2h, 840 ℃ × 24h.
The rotor blade of manufacturing is like this cut off and confirmed when section structure, and as shown in Figure 1, alloy underlayer 2 presents multiple roughly spherical alloying pellet 5 laminations, and has the tissue that is communicated to the intergranular gap 6 on alloy underlayer 2 surfaces from base material 1 side.During according to the volume fraction of relative density determination pore, be approximately 50%.
The pilot blade of manufacturing by above-mentioned steps is arranged in internal combustion turbine, carries out the trial run of 1 year.Now, at the cooling air intake of blade, throttle orifice is set, makes cooling air volume reduce 30% compared with design in the past.The rotor blade of use TBC of the present invention after trial run, in outward appearance and cut-out investigation, does not all see damage substantially.On the other hand, for relatively, reduce in the rotor blade of the TBC that is provided with prior art that cooling air volume turns round simultaneously, in appearance, partly see peeling off of TBC, in addition, in cross-sectional survey, beyond stripping portion, see the oxidative damage of alloy underlayer.According to these results, confirm that the high-temperature component of gas turbine that is provided with TBC of the present invention has excellent thermotolerance.
(embodiment 2)
Fig. 2 is the schematic cross-section of generating internal combustion turbine major portion.Internal combustion turbine possesses in the inside of internal combustion turbine cylinder 48: the turning axle (rotor) 49 that is positioned at center; With internal combustion turbine portion 44, this internal combustion turbine portion 44 has the stator blades 45 and the internal combustion turbine shroud 47 that are arranged on rotor blade 46 around of turning axle 49 and are supported on cylinder 48 sides.Internal combustion turbine has: link with this internal combustion turbine portion 44, suck atmosphere, obtain the compressed-air actuated compressor 50 that burning is used and heat-eliminating medium is used; With burner 40.Burner 40 has the burner nozzle 41 of the fuel of the pressurized air of supplying with from compressor 50 and supply (not shown) mixing jetting, make this mixed gas produce the combustion gases of High Temperature High Pressure in the interior burning of burner flame cylinder 42, these combustion gases are supplied with to internal combustion turbine 44 by transition section (transition piece) (tail pipe) 43, make thus rotor 49 high speed rotating.The compressed-air actuated part spraying from compressor 50, is used as burner inner liner 42, transition section 43 and the internal combustion turbine stator blades 45 of burner 40, the internal cooling air of gas turbine rotor blade 46.The combustion gases of the High Temperature High Pressure producing in burner 40,, spray internal combustion turbine portion 44 are rotated to driving to rotor blade 46 by 45 rectifications of internal combustion turbine stator blades through transition section 43.Although not shown, the generator being generally configured to by being combined with the end of turning axle 49 generates electricity.
In the present embodiment, except rotor blade 45, further on the combustion gases path surface of the internal combustion turbine shroud 47 of stator blades 46 and the first step, utilize the method for recording in embodiment 1 to be provided with the TBC of the present invention recording in above-described embodiment 1.Particularly, on the combustion gases path surface of each parts, by electrodischarge machining(E.D.M.), be processed with from matrix surface and connect the multiple cooling hole to internal cooling path.In addition, as raw material powder, prepare to utilize the NiCoCrAlY powdered alloy (Ni-23%Co-17%Cr-12.5%Al-0.5%Y, % by weight) that roughly spherical median size that gas atomization is manufactured is approximately 50 μ m.Use cold spray apparatus, make the combustion gases path surface filming of raw material powder at each parts.With regard to filming condition, working gas uses nitrogen, uses gaseous tension 3MPa, 900 ℃ of gas temperatures, powder feeding amount 15g/min, the film forming condition apart from 20mm, implements film forming until the thickness of alloy underlayer 2 becomes about 0.3mm.Then,, on the base material 1 that is provided with alloy underlayer 2, use yttrium oxide PSZ (ZrO
2-8wt%Y
2o
3) powder, in atmosphere, utilize plasma spraying (the about 50kW of plasma power) that the porous heat-insulating ceramic layer with ventilation property of the about 0.3mm of thickness is set.As filming condition now, preheating temperature is approximately 150 ℃, and the translational speed of spray gun is 45m/min, and spray distance is 100mm.In addition, to forming the each parts after thermal insulation ceramics layer, the heat-treat condition of the alloy using according to the base material as all parts, implements thermal treatment in a vacuum.
In addition, in the present embodiment, adopted only each first step of the rotor blade 45 in the internal combustion turbine portion 44 forming by 3 grades, stator blades 46, shroud 47 to be provided with the structure of TBC of the present invention, but also can further be applied to the second stage, the third stage thereafter.In addition, also can be applied to the internal combustion turbine being formed by other progression, for example, by all levels or the selected level of 2 grades, the 4 grades internal combustion turbine that form.
In the internal combustion turbine of the present embodiment of above structure, for the parts that are provided with TBC of the present invention, make cooling air reduce approximately 30% and turn round.After running 2 years, while observing each parts, in the gas turbine component of TBC that is provided with the present embodiment, TBC does not almost see damage, perfects.On the other hand, owing to having reduced cooling air, the efficiency of internal combustion turbine improves.In addition, the generating efficiency that possesses the internal combustion turbine compound power-generating station of this internal combustion turbine also improves.
Known according to above result, the internal combustion turbine of the present embodiment, due to the thermotolerance of its excellent high-temperature component, can at high temperature turn round, economy and the stable property used excellence.
Nomenclature
1 base material
2 alloy underlayer
3 thermal insulation ceramics layers
4 cooling hole
5 alloy powder particles
6 intergranular gaps
7 cracks
8 fluid coolants
40 burners
41 burner nozzles
42 burner flame cylinders
43 transition sections
44 internal combustion turbine
45 gas turbine rotor blades
46 internal combustion turbine stator bladess
47 internal combustion turbine shrouds
48 internal combustion turbine cylinders
49 gas turbine rotors
50 compressors
Claims (10)
1. an internal combustion turbine high-temperature component, it has heat insulating coat on the substrate surface of combustion gases that is exposed to high temperature, this heat insulating coat is provided with alloy underlayer, and further on the surface of this alloy underlayer, is provided with thermal insulation ceramics layer, and described internal combustion turbine is characterised in that with high-temperature component:
In described alloy underlayer and thermal insulation ceramics layer, be provided with the fine path being communicated with from base material lateral surface side, a part of parts being carried out to cooling refrigerant is flowed out to parts are outside by these fine paths.
2. internal combustion turbine high-temperature component as claimed in claim 1, is characterized in that:
Described base material is made up of the refractory alloy of Ni base, Co base or Fe base.
3. internal combustion turbine high-temperature component as claimed in claim 1, is characterized in that:
Described alloy underlayer is made up of MCrAlY alloy, and wherein M is at least a kind that is selected from Fe, Ni and Co.
4. internal combustion turbine high-temperature component as claimed in claim 1, is characterized in that:
The scope that described alloy underlayer has particle diameter is the lamellar structure of the alloy powder particle of 5～100 μ m, and the film endosome integration rate of the fine path of the connection being formed by the intergranular gap of lamination is 30～70%.
5. internal combustion turbine high-temperature component as claimed in claim 1, is characterized in that:
Described alloy underlayer is formed by following methods: alloy powder particle is utilized the working gas of the temperature below the fusing point of alloy accelerate, make this alloy powder particle not follow melting ground to collide with substrate surface at high speed.
6. internal combustion turbine high-temperature component as claimed in claim 1, is characterized in that:
Described thermal insulation ceramics layer is PSZ.
7. internal combustion turbine high-temperature component as claimed in claim 1, is characterized in that:
The fine path of described thermal insulation ceramics layer is formed by crack.
8. internal combustion turbine high-temperature component as claimed in claim 1, is characterized in that:
The fine path of described thermal insulation ceramics layer is formed by pore.
9. an internal combustion turbine, is characterized in that:
Possesses the internal combustion turbine high-temperature component described in any one in claim 1～8.
10. an internal combustion turbine compound power-generating station, is characterized in that:
Possesses internal combustion turbine claimed in claim 9.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2012234278A JP6054137B2 (en) | 2012-10-24 | 2012-10-24 | High temperature member for gas turbine having thermal barrier coating |
| JP2012-234278 | 2012-10-24 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103774134A true CN103774134A (en) | 2014-05-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310508420.6A Pending CN103774134A (en) | 2012-10-24 | 2013-10-24 | High temperature component with thermal barrier coating for gas turbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20140112758A1 (en) |
| EP (1) | EP2725120B1 (en) |
| JP (1) | JP6054137B2 (en) |
| CN (1) | CN103774134A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110594785A (en) * | 2018-06-12 | 2019-12-20 | 通用电气公司 | Deflection relieving structure of combustion system |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6529243B2 (en) * | 2014-11-17 | 2019-06-12 | 三菱日立パワーシステムズ株式会社 | Gas turbine component and gas turbine |
| US10598026B2 (en) * | 2016-05-12 | 2020-03-24 | General Electric Company | Engine component wall with a cooling circuit |
| CN114807823B (en) * | 2022-04-13 | 2023-04-07 | 四川大学 | Preparation method of high-temperature protective coating for hot-end component of gas turbine |
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Also Published As
| Publication number | Publication date |
|---|---|
| EP2725120B1 (en) | 2016-07-27 |
| EP2725120A1 (en) | 2014-04-30 |
| JP2014084791A (en) | 2014-05-12 |
| US20140112758A1 (en) | 2014-04-24 |
| JP6054137B2 (en) | 2016-12-27 |
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Owner name: MITSUBISHI HITACHI POWER SYSTEM LTD. Free format text: FORMER OWNER: HITACHI,LTD. Effective date: 20141218 |
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| C41 | Transfer of patent application or patent right or utility model | ||
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| RJ01 | Rejection of invention patent application after publication |
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| RJ01 | Rejection of invention patent application after publication |