Manufacturing method of composite parts, bi-metal blisk, guide vane and blade ring

Abstract

A manufacturing method of a composite part, which utilizes a hot isostatic pressing process to prepare the part, the composite part comprising a plurality of sub-parts, an independent jacket is provided for each sub-part, each sub-part is filled with raw material powder and subjected to warm isostatic pressing preforming, then the jacket connection part is cut open and welded together, and the whole jacket is subjected to hot isostatic pressing processing to obtain a composite part blank. The method can realize full and effective filling of raw material powder in a complex structure, and improve the production efficiency and product quality of the composite part. The application also provides a manufacturing method of a double-alloy integral blisk, a guide vane and a blade ring.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engines, and particularly relates to a preparation method of a composite part, and further relates to a manufacturing method of a double-alloy blisk, a guide vane and a blade ring. BACKGROUND

[0002] In the modern aviation industry, engine part structures are increasingly complex, and are facing higher and higher performance requirements. Heat-resistant alloy materials represented by titanium alloy and nickel alloy have become ideal materials for civil aviation engine parts due to their superior high-temperature mechanical properties. Due to their own physical properties, heat-resistant alloys such as titanium alloy and nickel alloy are difficult to machine, and thus powder metallurgy processes that have near-net forming advantages and can obtain uniform organizational structures are increasingly applied in alloy blisk manufacturing, and hot isostatic pressing process is a typical representative.

[0003] However, in the machining and manufacturing of composite parts with complex structures, such as blisks, guide vanes or blisks, the existing hot isostatic pressing machining process still has limitations. On the one hand, the composite part often has a complex structure, and the inner cavity structure of the overall sleeve manufactured according to the contour is complex, and the powder raw material is difficult to fully fill; on the other hand, when the structures of different regions of the composite part need to be prepared by using different materials, mixing of the powder is prone to occur at the interface, which affects the overall performance of the part. The inventors recognize that it is of high practical value to provide a hot isostatic pressing manufacturing method for a composite part with a complex structure. SUMMARY

[0004] The purpose of the present application is to provide a manufacturing method of a composite part, which uses a hot isostatic pressing process to prepare a near-net forming composite part blank, can make the powder raw material fill fully and uniformly, avoid mixing of the powder between different regions, and improve the production efficiency and product quality of the composite part. The present application further provides a manufacturing method of a double-alloy blisk, a guide vane and a blade ring.

[0005] According to an aspect of an embodiment of the present application, a manufacturing method of a composite part is provided, which uses a hot isostatic pressing process to prepare the part, and the method comprises the following steps:

[0006] a) dividing the composite part into a plurality of sub-parts, and providing a plurality of sub-part sleeves for the plurality of sub-parts respectively;

[0007] b) filling raw material powder in the plurality of sub-part sleeves respectively and welding each of the plurality of sub-part sleeves closed;

[0008] c) performing warm isostatic pressing on the plurality of sub-sleeves respectively, so that the raw material powder in the plurality of sub-sleeves is combined into a plurality of sub-part powder blanks;

[0009] d) cutting off the sheaths of the reserved connecting parts between the sheaths of the plurality of sub-parts, and welding together along the cutting surfaces to form an integral sheath, so that the plurality of sub-part powder blanks are connected together in the integral sheath;

[0010] e) performing hot isostatic pressing on the integral sheath to obtain a composite part blank.

[0011] The provision of sheaths and filling of different parts of the composite part can solve the problem of difficulty in filling raw material powder in a complex cavity, and the filling of different powders in different sheaths and the preparation of the powder blanks by warm isostatic pressing can avoid the problem of mixed powder during hot isostatic pressing, improve the quality of the product, and the hot isostatic pressing process can use the same equipment to prepare multiple parts at a time, improving the production efficiency of the parts.

[0012] Further, the connecting reserved parts of the sheaths of the plurality of sub-parts are provided with connecting reserved bosses. The reserved boss structure facilitates the welding of the sheaths.

[0013] Further, the method further comprises step f): performing heat treatment and stress relief processing on the composite part blank to obtain a composite part finished product. According to different materials, corresponding heat treatment and stress relief processing of the part blank can improve the quality of the part.

[0014] Further, at least two of the sub-parts are made of raw material powder of different compositions. The use of different materials in different structures of the composite part can fully exert the performance advantages of different materials and improve the mechanical properties of the whole part.

[0015] According to another aspect of the embodiments of the present application, a manufacturing method of a dual-alloy blisk is provided, and the method comprises a near-net-shape blank preparation, characterized in that the near-net-shape blank preparation comprises a pre-blank preparation of the blisk and the blades respectively and a combined near-net-shape processing of the pre-blanks. In the pre-blank preparation, metal powders for manufacturing the blisk and the blades are respectively filled into a blisk metal package and a plurality of blade metal packages, vacuumized and welded to be closed, and the pre-blisk blank and the plurality of blade blanks are supported by warm isostatic pressing, wherein the metal powders for manufacturing the blisk and the blades are different metal materials. In the near-net-shape processing, the metal packages of the connecting positions of the blisk blank and each of the blade blanks are respectively cut off according to the structural design of the blisk, the connecting surfaces of the blisk blank and each of the blade blanks are exposed, the blisk metal package and all the blade metal packages are welded together along the cutting surfaces to become a blisk package, the connecting surfaces of the blisk blank and all the blade blanks are connected together in the blisk package, and then the blisk blank and the blade blanks are subjected to warm isostatic pressing near-net-shape processing to obtain a blisk blank.

[0016] The blisk blank is subjected to warm isostatic pressing near-net-shape processing, the required equipment is simple, the processing procedures are few, the metal raw materials are fully utilized, the structure is uniform due to the avoidance of the welding procedure, and the overall mechanical properties are good. The pre-blank is prepared by warm isostatic pressing, so that the metal powder raw material has formed a stable solid structure before being subjected to warm isostatic pressing near-net-shape processing, thereby avoiding uneven structure caused by mixing of powders in the powder filling stage when directly subjecting different metal powders to warm isostatic pressing, the dual-alloy interface is clear and stable, the combination is firm, and the mechanical properties of the connecting position are excellent. The material selection can be freely combined, and is not limited by alloy composition. The plurality of blade blanks and the blisk blank can be prepared at the same time, thereby saving the production cycle. A plurality of blisks can be manufactured in the same warm isostatic pressing equipment, thereby saving the manufacturing cost.

[0017] Preferably, the blisk blank and the blade blank are designed with a processing allowance and a connecting reserved boss at the connecting position. The processing allowance and the reserved boss make the combination of the blisk blank and the blade blank easier.

[0018] Preferably, the manufacturing method further comprises a heat treatment of the blisk blank, and the heat treatment comprises a local heat treatment of the blisk and the blades in the blisk blank respectively and a whole heat treatment of the blisk blank. The targeted heat treatment procedure can adjust the structure of the blisk and the blades respectively, so that the mechanical properties are more suitable for the working conditions.

[0019] Preferably, in the local heat treatment, the heat treatment area is heated while other areas are cooled by air cooling to reduce the mutual influence between different heat treatment processes at the junction area.

[0020] Preferably, the manufacturing method further comprises a final machining, which processes the whole blisk blank after the heat treatment to obtain a whole blisk finished product, and the final machining comprises machining and stress relief annealing.

[0021] Preferably, the technical powder used by the blisk and the blade is titanium alloy or nickel alloy powder.

[0022] Further, the titanium alloy includes TC17 and TC4, and the nickel alloy includes FGH96, GH4169D, GH4720Li, GH4065A, GH4169 or K417G.

[0023] Optionally, the blisk is made of TC17 alloy powder, and the blade is made of TC4 alloy powder.

[0024] Preferably, the parameters of the warm isostatic pressing are heating temperature 350-500℃, pressure 20-80MPa, and pressure holding time 0.5-1h.

[0025] Optionally, the blisk is made of FGH96 alloy powder, and the blade is made of GH4169D alloy.

[0026] Optionally, the blisk is made of FGH96 alloy powder, and the blade is made of GH4720Li alloy.

[0027] Optionally, the blisk is made of GH4065A alloy powder, and the blade is made of GH4169D alloy powder.

[0028] Optionally, the blisk is made of GH4065A alloy powder, and the blade is made of GH4720Li alloy powder.

[0029] Optionally, the blisk is made of GH4169 alloy powder, and the blade is made of GH4169D alloy powder.

[0030] Optionally, the blisk is made of GH4065A alloy powder, and the blade is made of K417G alloy powder.

[0031] Preferably, for the above nickel alloy double-alloy blisk embodiment, the parameters of the warm isostatic pressing are heating temperature 350-950℃, pressure 20-80MPa, and pressure holding time 0.25-1h.

[0032] According to another aspect of the embodiment of the present application, a manufacturing method of a guide vane is provided for manufacturing a multi-union turbine guide vane, the method comprising the following steps:

[0033] a) dividing the guide vane into a plurality of single guide vanes, and providing a single guide vane cover for each single guide vane;

[0034] b) filling raw material powder into each single guide vane cover and welding each single guide vane cover closed;

[0035] c) subjecting the single guide vane covers to warm isostatic pressing processing to combine the raw material powder in the single guide vane covers into single guide vane powder blanks;

[0036] d) cutting off the cover of the reserved part between the single guide vane covers and welding the cutting surfaces together to form an annular guide vane whole cover, so that the single guide vane powder blanks are connected together in the guide vane whole cover;

[0037] e) subjecting the guide vane whole cover to hot isostatic pressing processing to obtain a guide vane whole blank.

[0038] By dividing the multi-union turbine guide vane into a plurality of single guide vanes, providing a cover for each single guide vane and filling the cover, the raw material powder can be fully filled to improve the product quality. Meanwhile, the hot isostatic pressing equipment can process multiple parts at the same time, improving the production efficiency.

[0039] Further, the raw material powder is a nickel-based alloy powder or a titanium alloy powder. Nickel alloy and titanium alloy have good high-temperature mechanical properties and are suitable for the manufacture of guide vanes.

[0040] According to another aspect of the embodiment of the present application, a manufacturing method of a guide vane is provided for manufacturing a multi-union turbine guide vane, the method comprising the following steps:

[0041] a) dividing the guide vane into a plurality of single guide vanes, and providing a single guide vane cover for each single guide vane;

[0042] b) filling raw material powder into each single guide vane cover and welding each single guide vane cover closed;

[0043] c) subjecting the single guide vane covers to warm isostatic pressing processing to combine the raw material powder in the single guide vane covers into single guide vane powder blanks;

[0044] d) cutting off the cover of the connecting reserved part between the inner ring cover, the outer ring cover and the blade cover of the blade ring, and welding together along the cutting surface to become the blade ring integral cover, so that the inner ring powder blank, the outer ring powder blank and the blade ring blade powder blank are connected together in the blade ring integral cover;

[0045] e) hot isostatic pressing the blade ring integral cover to obtain a composite part blank.

[0046] By dividing the integral blade ring into multiple parts and providing a cover for each part, the raw material powder can be fully filled to improve product quality. Filling different powders with different components in different covers and preforming the powder blanks can prevent powder mixing during hot isostatic pressing. At the same time, the hot isostatic pressing equipment can process multiple parts simultaneously using the same equipment, improving production efficiency.

[0047] Further, the inner ring, the outer ring and the blade ring are made of at least two different raw material powders. Selecting different materials according to the service environment and mechanical properties of different regions of the integral blade ring can fully utilize the performance advantages of dissimilar materials and improve the mechanical properties of the integral blade ring.

[0048] Further, the raw material powder includes titanium alloy powder or nickel-based alloy powder. Titanium alloy and nickel-based alloy have good high-temperature mechanical properties and are suitable for manufacturing integral blade rings. BRIEF DESCRIPTION OF DRAWINGS

[0049] Figure 1 is a schematic diagram of a double-alloy integral blade disc in an embodiment;

[0050] Figure 2 is a schematic diagram of a steel cover structure of a blade disc and a blade in an embodiment;

[0051] Figure 3 is a schematic diagram of a combination of a steel cover of a blade disc and a steel cover of a blade in an embodiment.

[0052] Figure 4 is a schematic diagram of a turbine guide vane structure in an embodiment;

[0053] Figure 5 is a schematic diagram of a projection structure of a single guide vane cover in an embodiment;

[0054] Figure 6 is a schematic diagram of a turbine guide vane integral cover in an embodiment;

[0055] Figure 7 is a schematic diagram of an integral blade ring structure in an embodiment;

[0056] Figure 8a is a schematic diagram of a divided outer ring structure in an embodiment;

[0057] Figure 8b Fig. 2 is a schematic diagram of the structure of the divided blade of the outer ring in an embodiment;

[0058] Figure 8c Fig. 3 is a schematic diagram of the structure of the divided inner ring in an embodiment;

[0059] Figure 9 Fig. 4 is a schematic diagram of the axial section structure of the overall outer ring in an embodiment;

[0060] Figure 10 Fig. 5 is a schematic diagram of the overall outer ring in an embodiment.

[0061] Significance of reference signs:

[0062] 1-blade; 2-vane disc; 3-blade cover; 4-vane disc cover; 5-reserved boss; 6-blade alloy powder; 7-vane disc powder; 8-connection surface; 9-upper edge plate; 10-guide vane blade body; 11-lower edge plate; 12-single guide vane cover; 13-outer ring; 14-outer ring blade; 15-inner ring; 16-outer ring cover; 17-outer ring blade cover; 18-inner ring cover.

[0063] It should be understood that the above drawings are used to specifically describe the technical concept of the present application, and are not limited to the specific embodiments of the present application. In the drawings, only the parts involved in the technical solution of the present application are schematically described, and the overall and all details of the involved components are not strictly drawn according to the size ratio. DETAILED DESCRIPTION

[0064] The technical concept of the present application will be further described below in combination with the drawings and specific embodiments.

[0065] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art; the terms used herein are intended to describe specific embodiments, and are not intended to limit the scope of protection of the present application; the terms "include" and "have" and their equivalent expressions in the specification and claims and the above drawing description are intended to cover non-exclusive inclusion.

[0066] Reference herein to "embodiment" means that the specific features, structures or properties described in connection with the embodiment can be included in at least one embodiment herein. The phrase appears at various places in the specification does not necessarily refer to the same embodiment, nor is it limited to mutually exclusive or alternative embodiments. Those skilled in the art should understand that the embodiments herein can be combined with other embodiments without structural conflict.

[0067] In the description herein, the terms "first", "second" and the like are used only to distinguish different objects, and cannot be understood as indicating relative importance or limiting the number, specific order or primary and secondary relationship of the technical features described. In the description herein, the meaning of "a plurality of" is at least three.

[0068] In the description herein, the terms "up", "down", "inner", "outer", "axial", "radial" and the like indicating the orientation or positional relationship are intended to accurately describe the embodiments and simplify the description, and are not intended to limit the parts or structures involved to have a specific orientation, be installed or operated in a specific orientation, and cannot be understood as a limitation on the embodiments herein.

[0069] Unless otherwise explicitly specified and limited, the technical terms "mounting", "connecting", "fixing" and the like should be understood broadly, for example: it can be rigid connection, or elastic connection; it can be detachable connection, or integral; it can be direct connection, or indirect connection through an intermediate structure. For those skilled in the art, the specific meaning of the above terms in the description of the embodiments can be understood according to the specific circumstances.

[0070] According to one embodiment of one aspect of the present application, a manufacturing method of a composite part is provided, which uses a hot isostatic pressing process to prepare the part, wherein the composite part refers to a part with obvious structural and functional differences between different parts, which usually includes one or more components with supporting or connecting functions and a plurality of repeated units with specific mechanical functions, for example: Figure 1 The integral blisk shown in the figure includes a blisk 2 and a plurality of blades 1 mounted on the blisk body, wherein the blisk 2 is structurally different from the blade 1, and the functions they undertake are also different; as shown in Figure 4 The multi-link guide vane shown in the figure includes an upper edge plate 9, a lower edge plate 11 and a guide vane blade 10 connected between the upper and lower edge plates, wherein the upper edge plate 9 and the lower edge plate 11 mainly play a supporting role, and the guide vane blade 10 has aerodynamic function; as shown in Figure 7 The integral blisk shown in the figure includes an outer ring 13, an inner ring 15 and a blisk blade 14, wherein the outer ring 13 and the inner ring 15 mainly play a supporting role, and the blisk blade 14 has aerodynamic function. The method comprises the following steps:

[0071] a) dividing the composite part into a plurality of sub-parts, and providing a sub-part package for each of the plurality of sub-parts; as an option, the sub-parts can be the same or different from each other; as a preferred embodiment, the connection reserved part of the sub-part package is provided with a reserved boss structure for connection, so as to facilitate subsequent cutting and splicing;

[0072] b) filling raw material powder in each sub-part package, vacuumizing and welding to seal; optionally, the raw material powder filled in the sub-part packages can be the same or different, such as filling nickel-based alloy in the first sub-part package and titanium alloy in the second sub-part package, or filling titanium alloy in both;

[0073] c) warm isostatic pressing each sub-part package to combine the raw material powder in the sub-part package into a sub-part powder blank; the processing temperature of warm isostatic pressing should not exceed the recrystallization temperature of the raw material powder, preferably, the raw material powder is mechanically deformed to combine into a powder blank with fixed shape;

[0074] d) cutting off the package of the connecting reserved part between the sub-part packages, and welding together along the cutting surface to form an integral package, so that the sub-part powder blanks are connected together in the integral package;

[0075] e) hot isostatic pressing the integral package to make the powder in the integral package fully deform, diffuse, creep and recrystallize under the action of temperature and pressure, and finally combine into an integral, to obtain a composite part blank;

[0076] f) according to the heat treatment system of the part material, the obtained composite part blank is subjected to corresponding heat treatment, and after flaw detection, mechanical finishing is performed to eliminate stress, to obtain a part finished product.

[0077] According to another aspect of the present application, an embodiment of a manufacturing method of a double-alloy integral blisk is provided, which provides a double-alloy integral blisk, as shown in Figure 1 which includes a blisk 1 and 20 blades 2. The blisk 1 is made of TC17 alloy, and the blades 2 are made of TC4 alloy. The manufacturing method of the double-alloy integral blisk includes the following steps:

[0078] 1) near-net shape blank preparation, including pre-blank preparation and integral near-net shape processing.

[0079] Pre-blank preparation: as shown in Figure 2As shown, according to the structure and size of the blisk, the blade cover 3 and the blisk cover 4 of each blade 2 are designed and manufactured respectively, the covers are made of stainless steel, size allowance is made for subsequent processing, and a boss 5 is reserved at the connecting position of the blisk 1 and the blade 2; the TC4 titanium alloy powder 6 is filled into all the blade covers 3, and the TC17 titanium alloy powder 7 is filled into the blisk cover 4, the filling process is vibration filling to improve the density of the powder; after filling is completed, vacuumizing is performed to remove residual gas in the body, and the blade cover 3 and the blisk cover 4 are welded and closed respectively; warm isostatic pressing processing is performed at a temperature of 350-500°C, preferably 350-400°C, under a pressure of 20-80MPa, preferably 30-50MPa, for 0.5-1h, preferably 0.5h, to extrude the titanium alloy powder into a preform of the blisk and the blade respectively. The titanium alloy powder used is prepared by a rotating electrode centrifugal atomization method, and the average particle size is 100μm. According to the specific structure of the blade and the blisk, the thickness of the stainless steel cover is 0.5-2mm.

[0080] Blisk near-net forming processing: as shown in Figure 3 According to the structural design of the blisk, the cover at the connecting surface 8 of the blisk and the blade is cut off by wire cutting, the connecting surface of the blisk preform and the blade preform is exposed, each blade cover 3 and the blisk cover 4 are welded together along the cutting surface by argon arc welding to become a blisk cover, and the blisk preform and the blade preform are connected together along the connecting surface 8 in the blisk cover; the blisk preform and the blade preform are subjected to hot isostatic pressing treatment at a temperature of 850-920°C, preferably 870-900°C, and a pressure of 120-170MPa, preferably 120-140MPa, for 0.5-2h, preferably 1h, the preforms of the blade and the blisk form a uniform alloy structure under high temperature and high pressure, and are firmly combined along the connecting surface 8 to obtain a blisk blank.

[0081] The preform is treated by hot isostatic pressing near-net forming processing, which avoids uneven structure caused by mixing powder at the interface position when directly processing different metal powders, and ensures that the alloys of different components at the connecting surface position are firmly combined to improve the overall mechanical properties.

[0082] 2) Blank processing: the blisk blank is machined by a machine tool to remove the stainless steel cover on the surface.

[0083] 3) Heat treatment, including local solid solution treatment and overall aging treatment.

[0084] The local solid solution treatment is firstly carried out at 910-940℃ for 1.5h for the blade area, and the blade disc is air-cooled at the same time; and then the solid solution treatment is carried out at 788-816℃ for 4h for the blade disc area, and the blade is air-cooled at the same time. In this way, the structure of the integral blade blank is adjusted, and the mutual interference between the heat treatment processes is reduced.

[0085] The integral aging treatment is carried out at 600-620℃ for 8h for the integral blade blank.

[0086] The cooling mode after the above heat treatment processes is all air cooling.

[0087] 4) The integral blade blank is put into water for ultrasonic detection to check the internal quality of the integral blade blank.

[0088] 5) The final machining is carried out by using a machine tool to machine the integral blade blank, remove the reserved amount, so that the size and surface state meet the design requirements, and then stress relief annealing is carried out to obtain the integral blade finished product.

[0089] The finally obtained double-alloy integral blade disc has good uniformity of the bonding surface structure, high overall mechanical properties, and the tensile strength of the blade and the blade disc can reach the performance level of TC4 titanium alloy and TC17 titanium alloy forgings respectively, and the tensile strength of the blade and the blade disc bonding part can reach the strength level of TC4 and TC17 titanium alloy welded joints.

[0090] For the nickel alloy double-alloy blade disc, the parameter range of the warm isostatic pressing can be selected as follows: the heating temperature is 350-950℃, the pressure is 20-80MPa, and the pressure holding time is 0.25-1h.

[0091] According to another embodiment of another aspect of the present application, a double-alloy integral blade disc is provided, which comprises a blade disc 1 made of FGH96 alloy and 28 blades 2 made of GH4169D alloy. The manufacturing method of the double-alloy integral blade disc comprises the following steps:

[0092] 1) Near-net shape blank preparation, including preform preparation and bulk near-net shape processing. A metal jacket is made of low carbon steel, with reserved dimensions and boss structure for subsequent assembly. The nickel alloy powder for manufacturing the blade and vane preforms is separately vibratory packed, vacuumed and welded. The preforms are warm isostatic pressed at a temperature of 500-900°C, preferably 600-700°C, and a pressure of 20-70MPa, preferably 40-50MPa, for 0.25-1h, preferably 0.25-0.5h. The metal jacket at the connecting surface of the blade and vane preforms is cut off by wire cutting, and the connecting surface of the blade and vane preforms is exposed. The blade and vane preforms are connected together in the bulk blade jacket by laser welding along the connecting surface, and the blade and vane preforms are connected together in the bulk blade jacket by warm isostatic pressing at a temperature of 1010-1050°C, preferably 1020-1050°C, and a pressure of 95-135MPa, preferably 120-130MPa, for 0.5-3h, preferably 1.5-2h, to obtain the bulk blade blank. The nickel alloy powder is prepared by metal thermal reduction method, and has an average particle size of 150μm. The thickness of the low carbon steel jacket is 1mm.

[0093] 2) Blank processing, the low carbon steel jacket on the surface of the bulk blade blank is removed by acid treatment.

[0094] 3) Heat treatment, the blade and vane regions are separately solution treated and aged according to the nickel alloy heat treatment system. The blade region is first solution treated at 1135-1170°C for 1-4h, while the vane region is air cooled; the vane is then solution treated at 940-980°C for 1-2h, while the blade region is air cooled; the blade region is then aged at 750-770°C for 10-18h, while the vane region is air cooled; and finally the vane region is aged at 770-795°C for 6-12h, cooled to 690-715°C and held for 6-12h, while the blade region is air cooled.

[0095] 4) Inspection, the bulk blade blank is X-ray inspected to check the internal quality of the bulk blade blank.

[0096] 5) Final processing, the bulk blade blank is final processed by a machine tool, and vibratory stress relieved to obtain the finished bulk blade.

[0097] The finished bulk blade has good microstructure uniformity, and the blade and vane respectively reach the strength level of FGH96 and GH4169D alloy forgings. The strength at the joint of the two alloys reaches the level of the vane base material GH4169D.

[0098] At present, the blade is made of GH4169D deformed high-temperature alloy, which has high high-temperature strength, fatigue resistance and fatigue creep resistance, and has good corrosion resistance, oxidation resistance and long-term organizational stability, and is suitable for manufacturing high-pressure compressor or turbine blades of an aero-engine; the disk is made of FGH96 powder high-temperature alloy, which has a use temperature of 750 DEG C, uniform organization, small grain size, high yield strength, good fatigue performance and other comprehensive advantages.

[0099] According to another embodiment of the present application, a double-alloy blisk is provided, which comprises a disk 1 made of FGH96 alloy and 25 blades 2 made of GH4720Li alloy. The manufacturing method of the double-alloy blisk comprises the following steps:

[0100] 1) Preparation of a near-net-shaped blank. A metal jacket is made of low-carbon steel, a boss structure is reserved for subsequent assembly, nickel alloy powder is vibrated and filled to manufacture a disk and a patch blank, respectively, vacuumizing and welding sealing, warm isostatic pressing at a temperature of 450 DEG C-850 DEG C, preferably 450 DEG C-550 DEG C, and a pressure of 30 MPa-80 MPa, preferably 35 MPa-45 MPa, for 0.25 h-0.75 h, preferably 0.5 h-0.75 h, to obtain a preformed blank; the metal jacket at the connecting surface of the disk and the blade is cut off by wire cutting, the connecting surface of the disk preformed blank and the blade preformed blank is exposed, the disk jacket and the blade jacket are welded together by argon arc welding along the connecting surface to form a blisk jacket, and the disk blank and the blade blank are connected together in the blisk jacket, and hot isostatic pressing is performed at a temperature of 1125 DEG C-1160 DEG C, preferably 1130 DEG C-1150 DEG C, and a pressure of 100 MPa-130 MPa, preferably 105 MPa-115 MPa, for 1 h-3 h, preferably 1.5 h-2.5 h, to obtain a blisk blank.

[0101] 2) Machining of the blank, the low-carbon steel jacket on the surface of the blisk blank is removed by machine cutting.

[0102] 3) Heat treatment, according to the heat treatment system of nickel alloy, solid solution treatment and overall aging treatment are performed on the disk and blade regions, respectively. First, the disk region is subjected to solid solution treatment at 1135 DEG C-1170 DEG C for 1 h-4 h, and the blade region is air-cooled at the same time; then the blade is subjected to solid solution treatment at 1150 DEG C-1190 DEG C for 1 h-2 h, and the disk region is air-cooled at the same time; finally, the blisk blank is subjected to overall aging treatment at 630 DEG C-660 DEG C for 20 h-26 h, and then heated to 750 DEG C-780 DEG C for 12 h-18 h.

[0103] 4) Flaw detection, water immersion flaw detection is performed on the blisk blank to check the internal quality of the blisk blank.

[0104] 5) Final machining, using machine tools to finish machining the blisk blank, and performing stress relief annealing treatment to obtain the blisk finished product.

[0105] The final blisk has good uniformity of organization, and the blisk and the blade respectively reach the strength level of FGH96 and GH4720Li alloy forgings, and the strength at the joint of the double alloys reaches the level of the blade base material GH4720Li.

[0106] The blade is made of GH4720Li deformed high-temperature alloy, which is a Ni-Cr-Co-based precipitation hardening type deformed high-temperature alloy and has a use temperature of 750 DEG C, high high-temperature strength, fatigue resistance and fatigue creep resistance, good corrosion resistance and oxidation resistance, and long-term organizational stability, and is suitable for making high-pressure compressor or turbine blades of an aero-engine. The blisk is made of FGH96 powder high-temperature alloy, which has a use temperature of 750 DEG C, uniform organization, small grain size, high yield strength, good fatigue performance and other comprehensive advantages.

[0107] According to still another embodiment of the present application, a double-alloy blisk is provided, which comprises a blisk 1 made of GH4065A alloy and 28 blades 2 made of GH4169D alloy. The manufacturing method of the double-alloy blisk comprises the following steps:

[0108] 1) Preparation of a near-net-shaped blank, a metal jacket is made of low-carbon steel, a size reservation is performed and a boss structure facilitating subsequent assembly is arranged, nickel alloy powder for manufacturing the blisk and blade blank is respectively vibration-filled, vacuum extraction is performed and welding is closed, warm isostatic pressing treatment can be performed at a temperature of 400 DEG C-800 DEG C, preferably 500 DEG C-600 DEG C, and a pressure of 20 MPa-75 MPa, preferably 20 MPa-30 MPa, for 0.25 h-1 h, preferably 0.5 h, to obtain a preformed blank; the metal jacket at the joint of the blisk and the blade is cut off by using wire cutting, the connecting surface of the blisk preformed blank and the blade preformed blank is exposed, the blisk jacket and the blade jacket are welded together along the cutting surface by laser welding to form a whole blisk jacket, the blisk blank and the blade blank are connected together in the blisk jacket, and hot isostatic pressing treatment is performed at a temperature of 1020 DEG C-1050 DEG C, preferably 1025 DEG C-1035 DEG C, and a pressure of 90 MPa-125 MPa, preferably 100 MPa-110 MPa, for 1 h-3 h, preferably 1 h-2 h, to obtain a blisk blank.

[0109] 2) Machining of the blank, using machine tools to cut and remove the low-carbon steel jacket on the surface of the blisk blank.

[0110] 3) heat treatment, the blade and the disc are respectively solid solution and aging treated according to the nickel alloy heat treatment system. Firstly, the disc is solid solution treated at 1040-1080℃ for 1-2h, and the blade is air-cooled; then the blade is solid solution treated at 940-980℃ for 1-2h, and the disc is air-cooled; next, the disc is aging treated at 750-775℃ for 6-12h, and the blade is air-cooled; finally, the blade is aging treated at 770-795℃ for 6-12h, and cooled to 690-715℃ for 6-12h, and the disc is air-cooled.

[0111] 4) flaw detection, the integral blade blank is water immersion flaw detected to check the internal quality of the integral blade blank.

[0112] 5) final machining, the integral blade blank is final machined by a machine tool, and stress relief annealing is carried out to obtain the integral blade finished product.

[0113] The finally obtained integral blade has good uniformity, the disc and the blade respectively reach the strength level of GH4169D and GH4065A alloy forgings, and the strength of the double-alloy joint reaches the level of the blade base material GH4169D.

[0114] The blade selects GH4169D deformed high-temperature alloy, which is a new type of nickel-based high-temperature alloy, has the same performance as GH4169 alloy, and the use temperature is increased to 700℃, has high high-temperature strength, fatigue resistance and fatigue creep resistance, and has good corrosion resistance and oxidation resistance and long-term organizational stability, and is suitable for making high-pressure compressor or turbine blades of an aero-engine. The disc selects GH4065A alloy with lower cost, which is a new type of nickel-based γ' precipitation strengthened deformed high-temperature alloy formed after special optimization according to the requirements of ingot metallurgy technology, and the use temperature can reach 750℃, the performance is close to the performance level of the second generation powder metallurgy, and the manufacturing cost is lower.

[0115] According to still another embodiment of another aspect of the present application, a double-alloy integral blade is provided, which comprises a disc 1 and 22 blades 2, the disc 1 is made of GH4065A alloy, and the blade 2 is made of GH4720Li alloy. The manufacturing method of the double-alloy integral blade comprises the following steps:

[0116] 1) Near-net shape preparation. A metal jacket is made of low carbon steel, with a boss structure reserved for the subsequent assembly. The nickel alloy powder for the vane disc and the blade preform is vibratory packed respectively, and the preform is obtained by vacuumizing and welding, warm isostatic pressing at 550-950°C, preferably 400-500°C, and 35-85MPa, preferably 30-40MPa, for 0.25h-1, preferably 0.25h-0.5h. The metal jacket at the joint surface of the vane disc and the blade is cut off by wire cutting, the joint surface of the vane disc preform and the blade preform is exposed, the vane disc jacket and the blade jacket are welded together by argon arc welding along the joint surface to form a whole vane disc jacket, the vane disc preform and the blade preform are connected together in the whole vane disc jacket, and the whole vane disc preform is obtained by warm isostatic pressing at 1135-1170°C, preferably 1145-1160°C, and 100-140MPa, preferably 110-120MPa, for 1.5h-3h, preferably 2h-3h.

[0117] 2) Machining of the preform. The low carbon steel jacket on the surface of the whole vane disc preform is removed by acid treatment.

[0118] 3) Heat treatment. The vane disc and the blade are respectively subjected to solution treatment, and the whole vane disc is subjected to aging treatment according to the heat treatment system of the nickel alloy. The vane disc is first subjected to solution treatment at 1040-1080°C for 1h-2h, and the blade is simultaneously subjected to air cooling; then the blade is subjected to solution treatment at 1150-1190°C for 1h-2h, and the vane disc is simultaneously subjected to air cooling; finally, the whole vane disc preform is subjected to aging treatment at 630-660°C for 20h-26h, and heated to 750-780°C for 10h-14h.

[0119] 4) Inspection. The whole vane disc preform is subjected to X-ray inspection to check the internal quality of the whole vane disc preform.

[0120] 5) Final machining. The whole vane disc preform is subjected to final machining by a machine tool, and subjected to vibration stress relief treatment to obtain the finished whole vane disc.

[0121] The finished whole vane disc has good uniformity of the structure, the vane disc and the blade respectively reach the strength level of the GH4065A and GH4720Li alloy forgings, and the strength at the joint of the two alloys reaches the level of the vane disc base material GH4065A.

[0122] The blade is made of GH4720Li deformed high-temperature alloy, which is a Ni-Cr-Co-based deformed high-temperature alloy with precipitation hardening, and has a service temperature of 750 DEG C, high high-temperature strength, fatigue resistance and fatigue creep resistance, good corrosion resistance and oxidation resistance, long-term organizational stability, and is suitable for making high-pressure compressor or turbine blades of an aero-engine; the disk is made of GH4065A alloy with lower cost, which is a new type of Ni-based γ' precipitation strengthened deformed high-temperature alloy formed by special optimization according to the requirements of ingot metallurgy technology, and has a service temperature of 750 DEG C, close to the performance level of the second generation of powder metallurgy, and lower manufacturing cost.

[0123] According to yet another embodiment of another aspect of the application, a dual-alloy blisk is provided, comprising a disk 1 made of GH4169 alloy and 35 blades 2 made of GH4169D alloy. The manufacturing method of the dual-alloy blisk comprises the following steps:

[0124] 1) Preparation of near-net-shaped blank. A metal jacket is made of low-carbon steel, with reserved dimensions and boss structure for subsequent assembly. Nickel alloy powder for the disk and the blade is respectively vibrated and filled, vacuumized and welded, and warm isostatic pressing is performed at a temperature of 350 DEG C-750 DEG C, preferably 350 DEG C-450 DEG C, and a pressure of 25 MPa-60 MPa, preferably 30 MPa-40 MPa, for 0.25 h-0.75 h, preferably 0.5 h, to obtain a preformed blank. The metal jacket at the connecting surface of the disk and the blade is cut off by wire cutting, the connecting surface of the disk preformed blank and the blade preformed blank is exposed, the disk jacket and the blade jacket are welded together by argon arc welding along the connecting surface to form a blisk jacket, and the disk blank and the blade blank are connected together in the blisk jacket. Hot isostatic pressing is performed at a temperature of 1010 DEG C-1040 DEG C, preferably 1015 DEG C-1025 DEG C, and a pressure of 105 MPa-130 MPa, preferably 115 MPa-125 MPa, for 1 h-3 h, preferably 1 h-2 h, to obtain a blisk blank.

[0125] 2) Blank processing. The low-carbon steel jacket on the surface of the blisk blank is removed by milling.

[0126] 3) heat treatment, the whole blisk blank is subjected to integral solid solution treatment according to the nickel alloy heat treatment system, and the blisk and the blade are subjected to local aging treatment respectively. Firstly, the whole blisk is subjected to solid solution treatment at 940-980 ℃ for 1-2 h; then the blisk part is subjected to aging treatment at 720-730 ℃ for 8-9 h, and the blade is cooled by air cooling when the temperature is reduced to 620-630 ℃ and kept for 8-9 h; finally, the blade part is subjected to aging treatment at 770-795 ℃ for 6-12 h, and the blisk is cooled by air cooling when the temperature is reduced to 690-715 ℃ and kept for 6-12 h.

[0127] 4) flaw detection, the whole blisk blank is subjected to X-ray flaw detection to check the internal quality of the whole blisk blank.

[0128] 5) final machining, the whole blisk blank is subjected to final machining by a machine tool, and is subjected to vibration stress relief treatment to obtain the whole blisk finished product.

[0129] The finally obtained whole blisk has good uniformity, the blisk and the blade respectively reach the strength level of GH4169 and GH4169D alloy forgings, and the strength of the double-alloy joint reaches the level of the blisk base material GH4169.

[0130] The blade is made of GH4169D deformed high-temperature alloy, which is a new type of nickel-based high-temperature alloy, has the same performance as GH4169 alloy, and has a use temperature increased to 700 ℃, has high high-temperature strength, fatigue resistance and fatigue creep resistance, and has good corrosion resistance and oxidation resistance and long-term organizational stability, and is suitable for making high-pressure compressor or turbine blades of an aero-engine; the blisk is made of commonly used GH4169 alloy, which is a γ' phase precipitation strengthened nickel-based high-temperature alloy, has high yield strength below 650 ℃, has high fatigue resistance, corrosion resistance and oxidation resistance, and has good processing performance, welding performance and long-term organizational stability.

[0131] According to still another embodiment of another aspect of the present application, a double-alloy whole blisk is provided, which comprises a blisk 1 made of GH4065A alloy and 38 blades 2 made of K417G alloy. The manufacturing method of the double-alloy whole blisk comprises the following steps:

[0132] 1) Near-net shape preparation. A metal jacket is made of low carbon steel, with reserved dimensions and boss structure for subsequent assembly. The nickel alloy powder for the vane disc and the blade preform is separately vibratory packed, vacuumed and welded closed, and then warm isostatic pressed at a temperature of 400-850°C, preferably 550-650°C, and a pressure of 30-80MPa, preferably 45-55MPa, for 0.25h, preferably 0.25h, to obtain a preform; the metal jacket at the connecting surface of the vane disc and the blade is cut off by wire cutting, the connecting surface of the vane disc preform and the blade preform is exposed, the vane disc jacket and the blade jacket are welded together by argon arc welding along the connecting surface to form an integral vane disc jacket, and the vane disc preform and the blade preform are connected together in the integral vane disc jacket, and then the integral vane disc preform is hot isostatic pressed at a temperature of 1030-1070°C, preferably 1030-1040°C, and a pressure of 95-135MPa, preferably 100-110MPa, for 0.5-4h, preferably 1.5-2.5h, to obtain a vane disc blank.

[0133] 2) Blank processing. The low carbon steel jacket on the surface of the vane disc blank is removed by acid treatment.

[0134] 3) Heat treatment. The vane disc region is subjected to local solid solution treatment, and then the integral vane disc is subjected to aging treatment according to the heat treatment system of the nickel alloy. The vane disc region is first subjected to solid solution treatment at 940-980°C for 1-2h, and the blade region is simultaneously subjected to air cooling; then the integral vane disc blank is subjected to aging treatment at 720-730°C for 8-9h, and then cooled to 620-630°C for 8-9h.

[0135] 4) Inspection. The integral vane disc blank is subjected to X-ray inspection to check the internal quality of the integral vane disc blank.

[0136] 5) Final processing. The integral vane disc blank is subjected to final processing by a machine tool, and then subjected to vibration stress relief treatment, to obtain a vane disc finished product.

[0137] The finally obtained integral vane disc has good uniformity of structure, the vane disc and the blade respectively reach the strength level of GH4169 alloy forgings and K417G alloy castings, and the strength at the joint of the two alloys reaches the level of the blade base material K417G.

[0138] The turbine blades are made of K417G cast superalloy, a nickel-based cast superalloy developed by reducing cobalt by 5% and titanium by 0.3% based on K417 alloy. It not only possesses advantages such as low density, good plasticity, and high-temperature performance, but also has a relatively low price, good microstructural stability, and does not precipitate σ phase after long-term aging at 850℃, making it suitable for manufacturing aero-engine turbine blades. The low-pressure turbine disk uses the commonly used GH4169 alloy, a nickel-based superalloy with γ' phase precipitation strengthening. It has high yield strength below 650℃, high fatigue resistance, corrosion resistance, and oxidation resistance, as well as good machinability, weldability, and long-term microstructural stability.

[0139] According to another aspect of the present invention, a method for manufacturing a guide vane is provided, wherein the manufactured multi-stage turbine guide vane structure is as follows: Figure 4 As shown, seven consecutive guide vane blades are arranged between the upper edge plate 9 and the lower edge plate 11, forming a seven-unit turbine guide vane. The method includes the following steps:

[0140] a) The turbine guide vane is divided into 7 individual guide vanes, each individual guide vane comprising a single guide vane blade body 10, a 1 / 7 section upper edge plate 9, and a lower edge plate 11, combined with... Figure 5 Individual guide vane sleeves 12 are designed and manufactured for these individual guide vanes. The projection structure of each individual guide vane sleeve on the lower edge plate is as follows: Figure 5 As shown. The single guide vane sleeve 12 can be made of low carbon steel. According to the design, a connecting boss is reserved at the connection position between each sleeve and the adjacent sleeve.

[0141] b) K417G alloy powder was vibrated and filled into each individual guide vane sleeve 12. After filling, vacuum was applied and the sleeve was welded and sealed.

[0142] c) Perform warm isostatic pressing on all individual guide vane cladding 12 at 100MPa-300MPa for ≥5min, so that the K417G alloy powder particles undergo mechanical deformation and combine to form a shape-stable individual guide vane powder blank.

[0143] d) Cut off the sleeve at the reserved connection between the individual guide vane sleeves 12, and as follows Figure 6 The individual guide vane powder blanks are spliced ​​together along the cut surface, so that they are attached together along the connecting surface 8. The sleeves are then welded together by argon arc welding or laser welding to form an integral guide vane sleeve.

[0144] e) The whole vane is coated and subjected to hot isostatic pressing at a temperature of 1030-1070 DEG C and a pressure of 95-135 MPa for 0.5-4 h, so that the powder is fully mechanically deformed, diffused, creeped and recrystallized, and finally combined into the whole vane blank.

[0145] f) The coating is removed, and the whole vane blank is subjected to subsequent heat treatment according to the heat treatment system of K417G, and after the internal quality is checked by X-ray detection, the final machining is performed to remove a small amount of excess and internal stress outside the whole vane blank, so as to obtain the finished product of the seven-turbine vane.

[0146] The finished turbine vane product has uniform structure, good mechanical properties, no macroscopic composition segregation, and the comprehensive mechanical properties can reach the level of forgings, which are higher than the mechanical properties of castings / welded parts. Meanwhile, the material utilization rate is high, the process is relatively simple, and the production cycle is short.

[0147] In other embodiments, the number of single vanes can be less than or more than 7; the vanes can also be made of other grades of nickel-based alloys or titanium alloys.

[0148] According to an embodiment of another aspect of the present application, a manufacturing method of a whole vane ring is provided, and the manufactured whole vane ring structure is as shown in Figure 7 which comprises an outer ring 13, an inner ring 15 and a plurality of vane ring vanes 14 connected between the outer ring 13 and the inner ring 15. The method comprises the following steps:

[0149] a) The whole vane ring is divided into three parts of an outer ring, an inner ring and vane ring vanes as shown in Figure 8a- Figure 8c , and Figure 9 an outer ring coating 16, a plurality of vane ring vane coatings 17 and an inner ring coating 18 are provided, respectively, which can be designed and manufactured by low-carbon steel, and the connecting boss structure is provided at the designed connecting position.

[0150] b) The TC4 titanium alloy powder is vibrated and filled in the outer ring coating 16, each vane ring vane coating 17 and the inner ring coating 18, respectively, and then vacuumized and welded.

[0151] c) The coatings are subjected to warm isostatic pressing processing, and the processing pressure is 90-250 MPa, and the duration is ≥10 min, so that the mechanical deformation occurs between the TC4 titanium alloy powder particles, and the outer ring powder blank, the vane ring vane powder blank and the inner ring powder blank are combined into stable shapes.

[0152] d) The coatings of the connecting reserved parts between the outer ring coating 16, each vane ring vane coating 17 and the inner ring coating 18 are cut off as shown in Figure 10The shown splicing of the cladding along the cutting surface makes the outer ring powder blank, the vane ring vane powder blank and the inner ring powder blank adhere to each other along the connecting surface 8, and the cladding is welded together by argon arc welding to become the vane ring integral cladding.

[0153] e) The vane ring integral cladding is subjected to a hot isostatic pressing treatment at a temperature of 700-800℃ and a pressure of ≥80MPa for ≥2h, so that the TC4 titanium alloy powder in the vane ring integral cladding fully undergoes plastic deformation, diffusion creep and recrystallization, and finally combines to become the integral vane ring blank.

[0154] f) The vane ring integral cladding is removed, the integral vane ring blank is subjected to an annealing treatment at 690-730℃ for 0.5-3h, and after air cooling, water cooling or oil cooling, water immersion detection is performed, and finally, size finishing and stress relief treatment are performed through final machining to obtain the TC4 integral vane ring finished part.

[0155] According to another embodiment of the application, a manufacturing method of an integral vane ring is provided, and the manufactured integral vane ring structure is as shown in Figure 7 The outer ring 13 and the inner ring 15 are made of GH3625 nickel alloy, and the vane ring vanes 14 are made of GH4169 nickel alloy. The method comprises the following steps:

[0156] a) The integral vane ring is divided into three parts of an outer ring, an inner ring and vane ring vanes as shown in Figure 8a- Figure 8c According to the combination Figure 9 , an outer ring cladding 16, a plurality of vane ring vane claddings 17 and an inner ring cladding 18 are provided, each of which can be designed and manufactured by low-carbon steel, and a boss structure for connection is provided at the designed connection position.

[0157] b) GH3625 alloy powder is vibrated and filled in the outer ring cladding 16 and the inner ring cladding 18, and GH4169 alloy is vibrated and filled in the vane ring vane cladding 17, respectively, and vacuumized and welded to be closed.

[0158] c) Each cladding is subjected to warm isostatic pressing processing, the processing pressure is 100-300MPa, and the duration is ≥10min, so that the GH3625 alloy powder particles and the GH4169 alloy powder particles each undergo mechanical deformation and combine to become the outer ring powder blank, the vane ring vane powder blank and the inner ring powder blank with stable shape.

[0159] d) The cladding of the connecting reserved part between the outer ring cladding 16, each vane ring vane cladding 17 and the inner ring cladding 18 is cut off, as shown in Figure 10The shown splicing of the cladding along the cutting surface makes the outer ring powder blank, the vane ring vane powder blank and the inner ring powder blank adhere to each other along the connecting surface 8, and the cladding is welded together into a vane ring integral cladding by argon arc welding.

[0160] e) The vane ring integral cladding is subjected to a hot isostatic pressing treatment at a temperature of 980-1025 DEG C and a pressure of 115-125 MPa for 1-2 h, so that the GH3625 alloy powder and the GH4169 alloy powder inside the vane ring integral cladding fully plastically deform, diffusion creep and recrystallize internally and between each other, and finally combine into an integral vane ring blank.

[0161] f) The vane ring integral cladding is removed, the integral vane ring blank is subjected to a solution treatment at 950-960 DEG C for 0.5-1 h, and after air cooling, is subjected to an aging treatment at 725 DEG C for 8-9 h and at 625 DEG C for 8 h, and after again air cooling, is subjected to a water immersion flaw detection, and finally through final machining, is subjected to size finishing and stress relief treatment, to obtain a GH3625 / GH4196 dissimilar alloy integral vane ring finished part.

[0162] The integral vane ring obtained by the method has a uniform structure, good strength, a clear and firm interface between the dissimilar materials, and can reach the strength level of a forged piece of the same material.

[0163] The above examples are intended to make a detailed description of the technical concept of the present application for the understanding of those skilled in the art, and do not constitute a specific limitation on the embodiments of the present application. Within the scope of the claims of the present application, equivalent replacements or improvements of the materials, parts or operation steps involved therein, or combinations of different embodiments without conflict, all fall within the protection scope of the present application.

Claims

1. A method of manufacturing a composite part, using a hot isostatic pressing process for part production, characterized in that, The method comprises the following steps: a) dividing the composite part into a plurality of sub-parts, and providing a plurality of sub-part covers for the plurality of sub-parts respectively; b) filling raw material powder into the plurality of sub-part covers respectively and welding each of the plurality of sub-part covers closed; c) subjecting the plurality of sub-part covers to warm isostatic pressing processing respectively, so that the raw material powder in the plurality of sub-part covers is mechanically deformed and combined into a plurality of sub-part powder blanks, wherein the processing temperature of the warm isostatic pressing does not exceed the recrystallization temperature of the raw material powder; d) cutting off the connecting reserved parts of the plurality of sub-part covers and welding the plurality of sub-part covers together into an overall cover, so that the plurality of sub-part powder blanks are connected together in the overall cover; e) subjecting the overall cover to hot isostatic pressing processing to obtain a composite part blank.

2. The method of manufacturing a composite part according to claim 1, wherein, The connecting reserved parts of the sub-part covers are provided with reserved connecting bosses.

3. The method of manufacturing a composite part of claim 1, wherein, The method further comprises step f): subjecting the composite part blank to heat treatment and stress relief processing to obtain a finished composite part.

4. The method of manufacturing a composite part of claim 1, wherein, At least two of the sub-parts are made of raw material powder of different compositions.

5. A manufacturing method of a double-alloy blisk, wherein the method steps comprise near-net-shape blank preparation, and wherein the method is characterized in that: the near-net-shape blank preparation comprises pre-blank preparation of the blisk and the blades respectively and combined near-net-shape processing of the pre-blanks; in the pre-blank preparation, metal powder for manufacturing the blisk and the blades is filled into a blisk metal cover and a plurality of blade metal covers respectively, the metal covers are vacuumized and welded closed, and warm isostatic pressing is used to make a pre-blisk blank and a plurality of blade blanks, wherein the metal powder for manufacturing the blisk and the blades is of different metal materials, and wherein the processing temperature of the warm isostatic pressing does not exceed the recrystallization temperature of the metal powder; in the combined near-net-shape processing, the metal covers at the connecting positions of the blisk blank and the blade blanks are cut off according to the structural design of the blisk, the connecting surfaces of the blisk blank and each of the blade blanks are exposed, the blisk metal cover and all the blade metal covers are welded together along the cutting surfaces into an overall blisk cover, the connecting surfaces of the blisk blank and all the blade blanks are connected together in the overall blisk cover, and then hot isostatic pressing near-net-shape processing is performed on the blisk blank and the blade blanks as a whole to obtain a blisk blank.

6. The method of manufacturing a dual-alloy blisk of claim 5, wherein, The blisk blank and the blade blanks are designed in sizes with a reserved amount for subsequent processing and combination, and the connecting positions of the blisk blank and the blade blanks are provided with reserved connecting bosses.

7. The method of manufacturing a dual-alloy blisk of claim 5 or 6, wherein, The manufacturing method further comprises heat treatment of the blisk blank, wherein the heat treatment comprises local heat treatment of the blisk and the blades in the blisk blank and overall heat treatment of the blisk blank.

8. The method of manufacturing a dual-alloy blisk of claim 7, wherein, In the local heat treatment, the heat treatment area is heated while the other areas are air-cooled.

9. The method of manufacturing a dual-alloy blisk of claim 7, wherein, The manufacturing method further comprises final processing of the blisk blank after the heat treatment to obtain a finished blisk, wherein the final processing comprises machining and stress relief annealing.

10. The method of manufacturing a dual-alloy blisk of claim 5 or 6, wherein, The metal powder used in the blade disc and the blade is titanium alloy or nickel alloy.

11. The method of manufacturing a dual-alloy blisk of claim 10, wherein, The titanium alloy includes TC17 and TC4, and the nickel alloy includes FGH96, GH4169D, GH4720Li, GH4065A, GH4169 or K417G. For TC17 and TC4 alloys, the temperature of the warm isostatic pressing is 350-500°C. For FGH96, GH4169D, GH4720Li, GH4065A, GH4169 or K417G alloys, the temperature of the warm isostatic pressing is 350-950°C.

12. A method of manufacturing a guide vane for manufacturing a multi-cascade turbine guide vane, characterized by, The method comprises the following steps: a) dividing the guide vanes into a plurality of single guide vanes, and providing a single guide vane cover for each single guide vane; b) filling raw material powder into each single guide vane cover and welding each single guide vane cover closed; c) performing warm isostatic pressing on the single guide vane covers to combine the raw material powder in the single guide vane covers into single guide vane powder blanks; the temperature of the warm isostatic pressing is not higher than the recrystallization temperature of the raw material powder; d) cutting off the cover of the reserved connection part between the single guide vane covers, and welding the covers together along the cutting surface to form an annular guide vane overall cover, so that the single guide vane powder blanks are connected together in the guide vane overall cover; e) performing hot isostatic pressing on the guide vane overall cover to obtain a guide vane overall blank.

13. The method of manufacturing a guide vane according to claim 12, wherein The raw material powder is nickel-based alloy powder or titanium alloy powder.

14. A method of manufacturing a blisk for manufacturing an engine blisk, characterized by, The method comprises the following steps: a) dividing the blade ring into an inner ring, an outer ring and a plurality of blade ring blades, and providing an inner ring cover, an outer ring cover and a blade ring blade cover for the inner ring, the outer ring and the blade ring blades respectively; b) filling raw material powder into the inner ring cover, the outer ring cover and the blade ring blade cover and welding them closed; c) performing warm isostatic pressing on the inner ring cover, the outer ring cover and the blade ring blade cover respectively to combine the raw material powder in the inner ring cover, the outer ring cover and the blade ring blade cover into an inner ring powder blank, an outer ring powder blank and blade ring blade powder blanks; the temperature of the warm isostatic pressing is not higher than the recrystallization temperature of the raw material powder; d) cutting off the cover of the reserved connection part between the inner ring cover, the outer ring cover and the blade ring blade cover, and welding the covers together along the cutting surface to form a blade ring overall cover, so that the inner ring powder blank, the outer ring powder blank and the blade ring blade powder blanks are connected together in the blade ring overall cover; e) performing hot isostatic pressing on the blade ring overall cover to obtain a blade ring overall blank.

15. The method of manufacturing a vane ring of claim 14, wherein, The inner ring, the outer ring and the blade ring blades are made of at least two different raw material powders.

16. The method of manufacturing a blade ring according to claim 14 or 15, characterized in that The raw material powder includes titanium alloy powder or nickel-based alloy powder.

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