JP2005214148A - Engine parts and coating method - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To improve efficiency of manufacturing work of engine part 3 by reducing the number of processes necessary for manufacturing the engine part 3. <P>SOLUTION: A green compact electrode which consists of a green compact formed by compressing powder of soft material not creating carbide easily is used for a section of a part main body 13. Pulse electric discharge is generated between the section of the part main body 13 and the green compact electrode 17 in oil or air. An abradable coat 15 which can be easily shaved by relative rotation of a mating engine part is formed by depositing and/or diffusing and/or welding material of the green compact electrode 17 on the section of the part main body 13 by electric discharge energy. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

  The present invention relates to a compressor case used in a gas turbine engine such as a jet engine, an engine component such as a compressor vane, and a coating method for coating an abradable coat on a part of a component main body of the engine component. .

  A conventional compressor case which is one of engine parts used in a gas turbine engine such as a jet engine will be briefly described as follows.

  That is, the compressor case includes a cylindrical case main body (component main body) as a main component, and the case main body houses a plurality of compressor blades that are counterpart engine components. In addition, an abradable coat that is easily scraped by relative rotation of the compressor blades is coated on a portion (a portion to be coated) surrounding the plurality of compressor blades on the inner peripheral surface of the case body. In the abradable coating, a soft material powder is used as a thermal spray material, and the portion to be coated of the case body is coated by thermal spraying.

  Accordingly, even if the compressor blades and the compressor case come into contact with each other during operation of the gas turbine engine, the abradable coat is easily scraped by the relative rotation of the compressor blades. The wing can be relatively rotated in a stable state.

In addition, there exists a thing shown to patent document 1 as a prior art relevant to this invention.
JP-A-5-148615

  By the way, since the abradable is coated by thermal spraying, in the manufacture of the compressor case (the engine part), before coating the abradable, a blasting process, a masking tape applying process, etc. In other words, after the abradable coat is coated, a post-treatment such as a masking tape removal treatment is necessary. Therefore, there is a problem that the number of steps required for manufacturing the compressor case increases, and the manufacturing operation of the compressor case becomes complicated.

  Further, for the same reason, the abradable cannot be sufficiently firmly coupled to the case main body (the component main body). Therefore, there is a problem that the abradable is easily peeled off from the case main body, and the quality of the compressor case (the engine part) is not stable.

In the invention according to claim 1, in the engine component used for the gas turbine engine,
With the component body;
An abradable coating coated on a part of the component body and easily scraped by relative rotation of the counterpart engine component;
The abradable coat is a green compact formed by compressing a powder of a soft material (metal or alloy, etc.) that does not easily generate carbides, or a green compact that has been processed by heating the green compact. An electrode is used to generate a pulsed discharge between the part of the component body and the green compact electrode in oil or air, and the discharge energy causes the part of the component body to It is characterized by being coated by depositing and / or diffusing and / or welding the electrode material of the green compact electrode or the reactant of this electrode material.

  Here, the engine parts include a compressor case, a compressor coupling rotor, a compressor vane, a turbine vane, a turbine case, and the like. The relative rotation of the counterpart engine component includes rotation of the engine component when the counterpart engine component does not rotate. Furthermore, the soft material that does not easily generate carbide includes a soft material that does not generate carbide at all.

  According to the invention specific matter of the first aspect, even if the engine component and the counterpart engine component come into contact with each other during operation of the gas turbine engine, the abradable coating is easily performed by relative rotation of the engine component. By cutting, the engine parts can be relatively rotated in a stable state.

  Further, the abradable coating is applied by diffusing and / or welding and / or depositing the electrode material of the green compact electrode or the like on the part of the component main body by discharge energy without spraying. Therefore, the coating range of the abradable coat can be limited to a discharge range, the abrasive coat can be coated, and in the manufacture of the engine parts, blasting and masking tape are applied. Pre-coating treatment such as attaching treatment and post-coating treatment such as masking tape removal treatment are not required.

  Furthermore, the boundary between the abradable coat coated with discharge energy and the base material of the component body has a gradient alloy characteristic, and the abradable coat is firmly bonded to the component body. Can do.

  In the invention described in claim 2, in addition to the matters specifying the invention described in claim 1, the abradable coat is configured to be a porous layer having a thickness of 0.5 mm or more. It is characterized by that.

  According to the invention specific matter of claim 2, according to the invention specific matter of claim 1, the abradable coat is a porous layer having a thickness of 0.5 mm or more. The abradable coat can be easily scraped (abradability) while sufficiently protecting the component main body with the coat.

  In the invention of claim 3, in addition to the matters specifying the invention of claim 1 or claim 2, the soft material powder is Co powder, Co alloy powder, Ni powder, It is any one of a powder of Ni alloy, a powder of Fe, and a powder of Fe alloy, or a mixed powder of a plurality of kinds.

  According to the invention specific matter of claim 3, the same effect as the effect of the invention specific matter of claim 1 or claim 2 is achieved.

In the invention according to claim 4, a coating method for coating an abradable coat that is easily scraped by relative rotation of a counterpart engine component on a part of a component body of an engine component used in a gas turbine engine In
Using a green compact formed by compression-molding a powder of a soft material (metal or alloy, etc.) that does not easily generate carbide, or a green compact electrode made of a processed green compact obtained by heat-treating the green compact. A pulsed discharge is generated between the part of the component main body and the green compact electrode in the air, and the discharge energy causes the electrode material of the green compact electrode to the part of the component main body. Alternatively, the electrode material is coated by depositing and / or diffusing and / or welding the reactant.

  Here, the engine parts include a compressor case, a compressor coupling rotor, a compressor vane, a turbine vane, a turbine case, and the like. The relative rotation of the counterpart engine component includes rotation of the engine component when the counterpart engine component does not rotate. Furthermore, the soft material that does not easily generate carbide includes a soft material that does not generate carbide at all.

  According to the invention specific matter described in claim 4, the abradable coating diffuses and / or welds the electrode material of the green compact electrode or the like to the part of the component main body by discharge energy without spraying. Since the coating is performed by depositing and / or depositing, the coating range of the abradable coat can be limited to a discharge range. In the production of the engine component, blasting and masking tape application are performed. Thus, post-coating treatments such as coating pretreatment and masking tape removal treatment are not required.

  In addition, the boundary between the abradable coat coated with discharge energy and the base material of the component body has a gradient alloy characteristic, and the abradable coat is firmly bonded to the component body. Can do.

  According to the invention specific matter of claim 5, in addition to the action of the invention specific matter of claim 4, the soft material powder is Co powder, Co alloy powder, Ni powder, Ni alloy It is characterized by being any one of powders of Fe, Fe, and Fe alloys, or mixed powders.

  In invention of Claim 5, there exists an effect | action similar to the effect | action by the invention specific matter of Claim 4.

  In the invention according to claim 6, in addition to the invention specific matter according to claim 4 or claim 5, the engine component is a compressor case or a turbine case, and The part is a part of the inner peripheral surface of the case main body in the compressor case or the turbine case, and is a part surrounding the plurality of compressor blades or the plurality of turbine blades.

  According to the invention specific matter of the sixth aspect, the same effect as the effect of the invention specific matter of the fourth or fifth aspect is exhibited.

  According to a seventh aspect of the invention, in addition to the invention specific matters of the fourth or fifth aspect, the engine component is a compressor-connected rotor, and the part of the component main body is The compressor connecting rotor is a part of the connecting rotor main body and is surrounded by a plurality of compressor vanes.

  According to the invention specific matter of claim 7, the same effect as the effect of the invention specific matter of claim 4 or claim 5 is achieved.

  In the invention according to claim 8, in addition to the invention specific matters according to claim 4 or 5, the engine component is a compressor vane or a turbine vane, and The part is an air seal portion on a proximal end side of a stationary blade body in the compressor stationary blade or the turbine stationary blade.

  According to the invention specific matter of the eighth aspect, the same effect as the effect of the invention specific matter of the fourth or fifth aspect is exhibited.

  In the invention according to claim 9, in addition to the operation according to the invention specific matter according to claim 4 or claim 5, the engine component is a turbine case, and the part of the component body is The turbine case is a part of the inner peripheral surface of the case main body and surrounds a plurality of turbine rotor blades.

  According to the invention specific matter of the ninth aspect, the same effect as the effect of the invention specific matter of the fourth or fifth aspect is exhibited.

  According to the invention of any one of claims 1 to 9, the coating range of the abradable coat can be limited to a discharge range, and in manufacturing the engine component, This eliminates the need for pre-coating processes such as blasting and masking tape attaching processes, and post-coating processes such as masking tape removing processes. Improve the efficiency of parts manufacturing operations.

  Further, since the abradable coat can be firmly bonded to the component main body, the abradable is hardly peeled off from the component main body, and the quality of the engine component is stabilized.

 According to the second aspect of the present invention, in addition to the effects described above, the abradable coat can be easily scraped (abradability) while the component main body is sufficiently protected by the abradable coat. ) Can be improved, and the quality of the engine component can be improved, and the life of the engine component and the counterpart engine component can be extended.

  The best mode of the present invention will be described with reference to FIGS.

  1 is a cross-sectional view of the upper half of the compressor according to the best mode of the present invention (including the compressor case according to the first embodiment in the best mode of the present invention). FIGS. 3A and 3B are schematic diagrams for explaining a coating method according to the first embodiment in the best mode of the present invention. FIG. 3A is a second embodiment in the best mode of the present invention. FIG. 3B is a diagram showing a part of the compressor stationary blade and the compressor coupling rotor according to FIG. 3, and FIG. 3B is a diagram showing the compressor stationary blade and the compressor coupling rotor according to the third embodiment in the best mode of the present invention. It is a figure which shows a part of.

  As shown in FIG. 1, a compressor 1 according to the best mode of the present invention is an apparatus used for a jet engine (one of gas turbine engines) and includes a compressor case 3. A plurality of rotatable compressor disks 5 are arranged in the compressor case 3, and a compressor connecting rotor 7 is integrally formed between adjacent compressor disks 5. Is provided. Here, a plurality of stages (only three stages shown) of compressor disks 5 and a plurality of compressor coupling rotors 7 rotate integrally with a plurality of stages of turbine disks (not shown) in the turbine (not shown) of the jet engine. To do.

  A plurality of compressor blades 9 (only one is shown for each stage) are provided at equal intervals on the outer periphery of the compressor disk 5 at each stage, and each compressor-connected rotor in the compressor case 3 is provided. A plurality of compressor vanes 11 (only one is shown for each stage) are provided at equal intervals on the outside of 7.

  Accordingly, when the plurality of stages of the turbine disks are rotated by the driving of the turbine, the plurality of stages of the compressor disks 5 and the plurality of compressor coupling rotors 7 are integrally rotated, and the plurality of stages of the compressor blades 9 are rotated. . As a result, the air taken into the compressor case 3 is compressed by the cooperation of the plurality of stages of compressor blades 9 and the plurality of stages of compressor stationary blades 11 and rearward (based on the orientation of the drawings when the patent publication is published). As shown in FIG.

Example 1
The compressor case 3 according to Embodiment 1 in the best mode of the present invention is used for the compressor 1 as described above, and is mainly composed of a cylindrical case body (component body of the compressor case) 13. It is provided as a component.

  In addition, an abradable coat 15 is coated on a part (a part to be coated (three parts are shown)) surrounding the plurality of compressor rotor blades 9 on the inner peripheral surface of the case body 13. Is easily scraped by the relative rotation (rotation) of the plurality of compressor blades 9, and is configured to be a porous layer having a thickness of 0.5 mm or more and 2.5 mm or less. Instead of the abradable coat 15 being a thick layer (0.5 mm or more and 2.5 mm or less) of a porous layer, the abradable coat 15 is configured to be a thick layer having a weak bonding force. Also good.

  The abradable coat 15 is coated based on a novel coating method as follows.

  That is, as shown in FIGS. 2A and 2B, the abradable coat 15 uses the green compact electrode 17, and the coated portion and the green compact on the inner peripheral surface of the case body 13 in the oil L. A pulsed discharge is generated between the electrode 17 and the discharge energy diffuses the electrode material of the green compact electrode 17 or the reactant of the electrode material into the portion to be coated on the inner peripheral surface of the case body 13 by the discharge energy. And / or coated by welding and / or deposition.

  Here, the green compact electrode 17 is a green compact obtained by compression-molding a powder of a soft material (metal or alloy, etc.) that is difficult to generate carbide, or a processed green compact obtained by heat-treating the green compact. The soft material powder is any one of Co powder, Co alloy powder, Ni powder, Ni alloy powder, Fe powder, and Fe alloy powder. Or a mixed powder of a plurality of types.

In addition, the state of the layer to be coated is caused by the particle size of the soft material, the energization pulse width, and the bonding strength of the green compact electrode 17. In the best mode of the present invention, the abradable While adjusting the bonding strength of the green compact electrode 17 so that the coat 15 is a thick porous layer or a thick thin layer with a weak bonding force, the particle size of the powder of the soft material as shown in Table 1 is adjusted. The energization pulse width of the discharge is selected according to the above. In other words, a discharge pulse width slightly smaller than or slightly larger than the energization pulse width (discharge condition) for forming a thick dense layer is selected. Note that the overlap between the four ranges of the energization pulse widths in Table 1 is partially omitted because the coupling strength of the green compact electrode 17 which is one of the parameters of the state of the layer is omitted from Table 1. Because.

  Next, the operation of the first embodiment in the best mode of the present invention will be described.

  Even when the compressor case 3 and a plurality of compressor blades 9 that are counterpart engine parts come into contact with each other during operation of the jet engine, the abradable coat 15 is easily scraped by the relative rotation of the plurality of compressor blades 9. Thus, the plurality of compressor blades 9 can be relatively rotated in a stable state. In particular, since the abradable coat 15 is a porous layer having a thickness of 1 mm or more, the abradable coat 15 can be easily scraped while sufficiently protecting the case body 13 with the abradable coat 15 (a) (Bradability) can be improved.

  In addition, the abradable coating 15 is coated by diffusing and / or welding and / or depositing the electrode material of the green compact electrode 17 on the coated portion of the case body 13 from the discharge energy without spraying. Therefore, the coating range of the abradable coat 15 can be limited to the discharge range. In the manufacture of the compressor case 3, pre-coating treatments such as blasting and masking tape pasting, Each post-coating process such as a removal process becomes unnecessary.

  In addition, the boundary between the abradable coat 15 coated with the discharge energy and the base material of the case body 13 has a gradient alloy characteristic, and the abradable coat 15 is firmly bonded to the case body 13. Can do.

  Therefore, according to the first embodiment in the best mode of the present invention, in the manufacture of the compressor case 3, the pre-coating process such as the blasting process, the masking tape attaching process, the masking tape removing process, etc. Since the coating post-treatment is not required, the number of steps required for manufacturing the compressor case 3 is reduced, and the efficiency of the manufacturing operation of the compressor case 3 is improved.

  Further, since the abradable coat 15 can be firmly bonded to the case main body 13, the abradable coat 15 becomes difficult to peel off from the case main body 13, and the quality of the compressor case 3 is stabilized.

  Furthermore, since the case main body 13 is sufficiently protected by the abradable coat 15, the ease of scraping (abradability) of the abradable coat 15 can be improved, so that the quality of the compressor case 3 is improved. Thus, the life of the compressor case 3 and the compressor rotor blade 9 can be extended.

<< Second Embodiment >>
As shown in FIG. 3A, the compressor connecting rotor 7 according to the second embodiment in the best mode of the present invention is used in the compressor 1 as described above, and is a cylindrical connecting rotor. A main body (component main body of the compressor coupling rotor) 19 is provided as a main component.

  In addition, a plurality of abradable coats 21 are coated on a part (a part to be coated) surrounded by the plurality of compressor stationary blades 11 in the connecting rotor body 19. It is easily scraped by the rotation of the connecting rotor 7 (in other words, the relative rotation of the plurality of compressor vanes 11 as the counterpart engine parts), and the porous layer has a thickness of 1 mm to 2.5 mm. It is comprised so that it may become. The abradable coat 21 is coated on the basis of the novel coating method in the same manner as the abradable coat 15.

  Therefore, according to the second embodiment in the best mode of the present invention, the same operations and effects as those of the first embodiment in the best mode of the present invention as described above are obtained.

<< Third embodiment >>
As shown in FIG. 3 (b), the compressor stationary blade 11 according to the third embodiment in the best mode of the present invention is used in the compressor 1 as described above, and is a stationary blade body (compressed). The component body 23 of the stationary blade 11) is provided as a main component.

  In addition, an abradable coat 25 is coated on an air seal portion (a part to be coated) on the base end side of the stationary blade body 23, and the abradable coat 25 of the compressor coupling rotor 7 which is a counterpart engine component. It is easily scraped by relative rotation (rotation), and is configured to be a porous layer having a thickness of 1 mm to 2.5 mm. The abradable coat 25 is coated based on the novel coating method in the same manner as the abradable coat 15.

  Therefore, according to the third embodiment in the best mode of the present invention, the same operations and effects as those of the first embodiment in the best mode of the present invention as described above are exhibited.

  The present invention is not limited to the description of the best mode of the invention described above, and appropriate modifications can be made as follows.

  That is, a part (a part to be coated) that is a part of the inner peripheral surface of the case body in the turbine case and surrounds a plurality of turbine blades so that the abradable coat 15 is coated on the part to be coated of the compressor case 3. ) May be coated with an abradable coat based on the novel coating method. In this case, as the green compact electrode used for coating, an electrode made of a green compact obtained by compression-molding a powder of a heat-resistant and oxidation-resistant alloy CoNiCrAlY is used.

  Further, the air seal part (coating part) on the base end side of the stationary blade body in the turbine stator blade is coated with the abradable coat 25 on the air seal part on the base end side of the stationary blade body 23 in the compressor stationary blade 11. In addition, an abradable coat based on the novel coating method may be coated.

  Further, instead of the oil L, a pulsed discharge may be generated in the air.

It is sectional drawing of the upper half of the compressor concerning the best form of this invention (The compressor case concerning the 1st Example in the best form of this invention is included). FIGS. 2A and 2B are schematic views for explaining the coating method according to the first embodiment in the best mode of the present invention. FIG. 3A is a view showing a part of a compressor stationary blade and a compressor coupling rotor according to the second embodiment in the best mode of the present invention, and FIG. 3B is the best view of the present invention. It is a figure which shows a part of compressor stationary blade and compressor connection rotor concerning 3rd Example in the form of this.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Compressor 3 Compressor case 7 Compressor connection rotor 9 Compressor rotor blade 11 Compressor vane 13 Case main body 15 Abradable coat 17 Compact electrode 19 Connected rotor main body 21 Abradable coat 23 Stator blade main body 25 Ablay Double coat

Claims (9)

In engine parts used in gas turbine engines,
With the component body;
An abradable coating coated on a part of the component body and easily scraped by relative rotation of the counterpart engine component;
The abradable coat uses a green compact formed by compression-molding a powder of a soft material that does not easily generate carbide, or a green compact electrode made of a processed green compact obtained by heat-treating the green compact. Alternatively, a pulsed discharge is generated between the part of the component main body and the green compact electrode in the air, and the discharge energy causes the electrode of the green compact electrode on the part of the component main body. Engine part, characterized in that it is coated by depositing and / or diffusing and / or welding the material or reactants of this electrode material.   The engine component according to claim 1, wherein the abradable coat is configured to be a porous layer having a thickness of 0.5 mm or more.   The soft material powder may be any one of a powder of Co, a powder of Co alloy, a powder of Ni, a powder of Ni alloy, a powder of Fe, a powder of Fe alloy, or a mixed powder of a plurality of kinds. The engine component according to claim 1, wherein the engine component is provided. In a coating method for coating an abradable coat that is easily scraped by relative rotation of a counterpart engine part on a part of a part body in an engine part used for a gas turbine engine,
Using a green compact formed by compressing a powder of a soft material that does not easily generate carbide, or a green compact electrode made of a processed green compact obtained by heat-treating the green compact, the component main body in oil or air A pulsed discharge is generated between the part and the green compact electrode, and the electrode material of the green compact electrode or the reaction of the electrode material is caused on the part of the component body by the discharge energy. A coating method comprising coating by depositing and / or diffusing and / or depositing a substance.   The soft material powder may be any one of a powder of Co, a powder of Co alloy, a powder of Ni, a powder of Ni alloy, a powder of Fe, a powder of Fe alloy, or a mixed powder of a plurality of kinds. The coating method according to claim 4, wherein the coating method is provided.   The engine component is a compressor case or a turbine case, and the part of the component body is a part of an inner peripheral surface of the case body in the compressor case or the turbine case, and a plurality of compressor blades 6. The coating method according to claim 4 or 5, wherein the coating method surrounds a plurality of turbine blades.   The engine component is a compressor coupling rotor, and the part of the component main body is a part of the coupling rotor main body in the compressor coupling rotor and surrounded by a plurality of compressor stationary blades. The coating method according to claim 4 or 5, wherein:   The engine component is a compressor vane or a turbine vane, and the part of the component main body is an air seal portion on a proximal end side of the stator vane body in the compressor vane or the turbine vane. The coating method according to claim 4 or 5, wherein:   The engine component is a turbine case, wherein the part of the component body is a part of an inner peripheral surface of the case body in the turbine case and surrounds a plurality of turbine blades. The coating method according to claim 4 or 5.

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