CN118030194A - Blade disc structure, production method, strength and thickness balancing method and engine - Google Patents
Blade disc structure, production method, strength and thickness balancing method and engine Download PDFInfo
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- CN118030194A CN118030194A CN202410017532.XA CN202410017532A CN118030194A CN 118030194 A CN118030194 A CN 118030194A CN 202410017532 A CN202410017532 A CN 202410017532A CN 118030194 A CN118030194 A CN 118030194A
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- boss
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- 238000000034 method Methods 0.000 title claims abstract description 20
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 19
- 238000002360 preparation method Methods 0.000 claims description 13
- 238000000151 deposition Methods 0.000 claims description 9
- 230000008021 deposition Effects 0.000 claims description 9
- 238000000280 densification Methods 0.000 claims description 8
- 238000007711 solidification Methods 0.000 claims description 3
- 230000008023 solidification Effects 0.000 claims description 3
- 239000011159 matrix material Substances 0.000 description 28
- 239000000835 fiber Substances 0.000 description 24
- 239000002131 composite material Substances 0.000 description 23
- 239000011226 reinforced ceramic Substances 0.000 description 18
- 239000000463 material Substances 0.000 description 13
- 239000000919 ceramic Substances 0.000 description 6
- 238000012545 processing Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000011148 porous material Substances 0.000 description 3
- 238000005245 sintering Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000011153 ceramic matrix composite Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000011900 installation process Methods 0.000 description 2
- 229910052582 BN Inorganic materials 0.000 description 1
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005229 chemical vapour deposition Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000005137 deposition process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000002657 fibrous material Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to the field of aero-engines, in particular to a turbine blade disc structure, a turbine blade disc production method, a turbine blade disc strength and thickness balancing method and an aero-engine. Wherein the turbine blade disk structure of the present invention comprises: the tray body is a plurality of tray bodies; the number of the bosses is several, the bosses are abutted against the disc body, and the bosses and the circle center of the disc body are positioned on the same axis; the plurality of blades are provided with a plurality of fixed and integrated mounting pieces respectively; the blades are radially distributed at the center of the disc body and are abutted against the outer edge of the disc body; the mounting piece is positioned between at least two disc bodies and fixedly connected with the at least two disc bodies.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to a turbine blade disc structure, a turbine blade disc production method, a turbine blade disc strength and thickness balancing method and an aero-engine.
Background
A turbine blade disc is an important component in turbomachinery, and is composed of blades and disks, and is commonly used in turbomachinery, turbochargers, turbojet engines, and the like.
In an aeroengine, a turbine blade disc is an important component part, is positioned on a rotor of a turbine and plays a role of fixing turbine blades, and is mainly used for installing and fixing the turbine blades to transmit power, and chemical energy of fuel gas is mechanical energy of the turbine; because turbine blade disks are required to operate in high temperature, high pressure, high rotational speed environments and are subject to complex loads, there are high demands on their construction and materials.
The design and manufacture of turbine blade disks involves knowledge in a number of fields, such as fluid mechanics, thermodynamics, materials science, etc. The shape and configuration of the turbine blade disk may also vary depending on the particular turbine model to maximize energy conversion efficiency and mechanical performance, as well as the shape, materials, and manufacturing process of the turbine blade disk, depending on the application scenario and requirements.
Because the design and the manufacture of the turbine blade disc need to consider the working environment of high temperature, high pressure and high-speed rotation, the material selection and the structural design of the turbine blade disc need to have higher strength and heat resistance; therefore, turbine blade disks are typically made of metallic materials, and materials commonly used today include nickel-based alloys, titanium alloys, and the like.
In summary, the turbine blade disc plays a critical role in the operation of the turbine, it carries the function of fixing and transferring the turbine blades, and it is required to have high strength and heat resistance. At the same time, the turbine blade disks must be designed and manufactured with different operating environments and turbine requirements in mind.
At present, the fiber reinforced ceramic matrix composite is applied to a turbine blade disc structure, and at least the following problems still exist:
1. At present, the research and preparation experience of the fiber reinforced ceramic matrix composite material integral turbine blade disc structure is less, a woven fiber preform scheme is mainly adopted to prepare blanks of the wheel disc, and the integral structure of the blade and the wheel disc is obtained through matrix deposition and mechanical processing means, so that the method is only suitable for small-size and small-thickness turbine blade disc structures. In practical application, the deposition process of the fiber reinforced ceramic matrix composite material matrix has higher requirements on the thickness of the component; but the thickness of the prepared member is further increased, the matrix deposition efficiency is low, the pores in the central part are more, and the strength is low. The turbine rotor is complex in stress, and has extremely high requirements on the strength of the disc body, the blades and other parts, so that great contradiction exists, and on one hand, the strength is high, and the thickness is large; on the other hand, too large a thickness of the member easily causes low densification degree of the matrix, and more pores exist to influence the strength of the member;
2. in the state of the existing preparation technology of the fiber reinforced ceramic matrix composite, the maximum thickness of the prepared component is about 15 mm; when the thickness of the prepared member is further increased, the matrix deposition efficiency is low, and the pores in the central part are more. And as the thickness of the disc body is increased, the steps of matrix deposition and machining are required to be repeated for a plurality of times, so that the working procedures are numerous, the production efficiency is greatly reduced, the preparation period and the cost are greatly increased, and the popularization and the application of the fiber reinforced ceramic matrix composite material on the integral turbine blade disc member are not facilitated;
3. The fiber reinforced ceramic matrix composite has the advantages of multiple preparation steps, long period and lower component yield. Aiming at the turbine blade disc structure with larger thickness, in order to ensure the uniformity of the whole structure, repeated deposition and processing steps are needed, the preparation cost and the period are far greater than those of the turbine blade disc structure with small size, and the dispersibility of component materials is larger; resulting in low yield.
Disclosure of Invention
The object of the present invention is to solve at least part of the above existing problems.
In terms of materials, a fiber-reinforced ceramic matrix composite is a composite that is composed of a ceramic matrix and a fiber-reinforced material. Fiber Reinforced Ceramic Matrix Composites (FRCMC) are a composite consisting of a fiber reinforced material and a ceramic matrix. The fiber reinforcement material is usually high-strength carbon fiber, glass fiber, ceramic fiber, etc., and the ceramic matrix may be alumina, silicon boride, boron nitride, etc. The composite material has excellent properties of high strength, high hardness, high temperature resistance, wear resistance and the like, and is widely applied to the fields of aerospace, automobiles, energy sources and the like. The preparation method of the fiber reinforced ceramic matrix composite material mainly comprises a static pressure sintering method, a reinforced bottom die sintering method, a chemical vapor deposition method and the like. In the preparation process, the fiber material and the ceramic matrix are pretreated first, and then are combined to form the composite material by adopting methods such as sintering or deposition.
Currently, fiber reinforced ceramic matrix composites have been used in the aerospace field for the manufacture of high performance engine parts, thermal protection materials, aerodynamic surfaces, and the like. In addition, it is also used in the industry of manufacturing high performance cutting tools, abrasive tools, electronic ceramics, and the like. Summarizing, the fiber reinforced ceramic matrix composite is a high-performance composite, has various excellent performances, and has wide application prospects in the fields of aerospace, automobiles, energy sources and the like.
The fiber reinforced ceramic matrix composite has the characteristics of high temperature resistance and low density, is a high-temperature material with potential on a hot end part of an aeroengine, can obviously reduce the weight of the engine and improve the temperature before a turbine, thereby greatly improving the power-weight ratio/thrust-weight ratio of the engine. In the field of aeroengines, fiber reinforced ceramic matrix composites are mainly applied to blades therein, such as chinese patent publication No.: CN108897931a, name: the prior art discloses a scheme for applying ceramic matrix composite materials to blades, wherein the blades are formed by layering a plurality of fiber cloth layers, and the scheme cannot be applied to a blade disc and has a plurality of working procedures; chinese patent publication No.: CN111365079a, name: the prior art discloses a scheme for applying ceramic matrix composite to blades, which mainly aims at designing tenon structures for the blades and cannot be applied to the blade discs.
The turbine blade disk structure of the present invention comprises:
the tray body is a plurality of tray bodies;
The number of the bosses is several, the bosses are abutted against the disc body, and the bosses and the circle center of the disc body are positioned on the same axis;
The plurality of blades are provided with a plurality of fixed and integrated mounting pieces respectively; the blades are radially distributed at the center of the disc body and are abutted against the outer edge of the disc body; the mounting piece is positioned between at least two disc bodies and fixedly connected with the at least two disc bodies.
As a preferred embodiment of the turbine blade disk structure of the present invention, comprising:
Each tray body is provided with a plurality of first pin holes, and the first pin holes are positioned close to the middle part of the tray body and are radially distributed at the center of the tray body;
The boss is provided with a plurality of second pin holes; the second pin hole is coaxial with the first pin hole;
The straight pins penetrate through the first pin holes and the second pin holes at the same time, and are fixedly connected with the disc body and the boss.
As a preferred embodiment of the turbine blade disk structure of the present invention, comprising:
each tray body is provided with a plurality of first inclined holes, and the first inclined holes are positioned close to the edges of the tray bodies and are radially distributed in the center of the circle of the tray bodies;
each mounting piece is provided with a second inclined hole, and when the mounting piece abuts against the disc body, the first inclined holes and the second inclined holes are positioned on the same axis;
the inclined pins penetrate through the first inclined holes and the second inclined holes at the same time, and are fixedly connected with the tray body and the mounting piece.
As a preferred embodiment of the turbine blade disc structure of the present invention, at least two of said disc bodies are spaced apart from at least one of said bosses.
As a preferred embodiment of the turbine blade disc structure of the present invention, each of the disc bodies has a first shaft hole, respectively;
Each boss is provided with a second shaft hole respectively; the first shaft hole and the second shaft hole are positioned on the same axis.
As a preferred embodiment of the turbine blade disk structure of the present invention, the second inclined holes in at least two of the disks are respectively located at different or non-parallel positions of the disks, and the second inclined holes in the two disks form an axis of inclination.
The production method of the turbine blade disc comprises the following steps:
The total thickness of the turbine blade disc is confirmed,
The thickness of each disc body is 5-8mm, so that the disc body can reach a high densification preparation level quickly;
selecting the number of the disk bodies and the thickness and the number of the bosses according to the total thickness of the turbine blade disk and the actual thickness of the single disk body;
the different disc bodies are separated by the boss and assembled;
Fixedly connecting the disk body with the boss, and performing secondary deposition and solidification to obtain a main body part of the turbine blade disk;
blades fixedly connected with the tray body are uniformly distributed around the outer edge part of the tray body.
As a preferred embodiment of the method for producing a turbine blade disc of the present invention, the disc body and the boss are fixedly connected by a straight pin;
a fixed integral mounting piece is arranged below the blade and is arranged between the two disc bodies;
The disc body is fixedly connected with the blades through inclined pins; and the oblique pin is inserted into the tray body and the mounting member at an oblique angle.
The strength and thickness balancing method of the turbine blade disc adopts the production method of the turbine blade disc.
The aeroengine of the present invention comprises at least a turbine blade disc structure according to any of the preceding claims and/or an apparatus produced by a method according to any of the preceding claims.
Advantageous effects
The invention has the following innovative advantages:
1. According to the invention, the existing single large thick disc body is split into a plurality of single-layer disc bodies, the bosses and the blade assemblies, so that the densification degree and the processing efficiency of the substrate can be effectively improved; achieving high densification preparation; on one hand, the thickness of the blade disc is realized, the strength of the product is ensured, and meanwhile, the problem that the traditional fiber reinforced ceramic matrix composite is only suitable for manufacturing components with small size and small thickness is avoided; solves the contradiction existing between the strength and the thickness at present, and realizes the breakthrough of quality.
2. The invention provides a novel large-thickness riveted fiber reinforced ceramic matrix composite turbine blade disc structure, which changes the preparation thought of the original fiber reinforced ceramic matrix composite integral turbine blade disc, greatly improves the processing quality of the disc body and the blades, improves the densification degree of the blade disc and shortens the preparation period; and the problem of the prior art that the working procedures for producing the components with large thickness are numerous is solved;
3. The connection mode between the blade and the disk body is designed into a brand-new installation edge structure, so that the connection of the blade and the disk can be effectively realized, and the requirements on processing feasibility and strength are met; greatly improves the yield.
4. Wherein adopt straight round pin nail to connect between the disk body, lead to the boss to carry out the interval, reserve good blade installation limit space to solidify once more through the deposit, further can the effectual intensity of guaranteeing the disk body.
Drawings
FIG. 1 is a perspective view of the present invention;
FIG. 2 is a cross-sectional view of the present invention;
FIG. 3 is a perspective view of a component "tray";
FIG. 4 is a perspective view of a component "boss";
FIG. 5 is a schematic diagram of a "straight pin" installation process;
FIG. 6 is a schematic illustration of a "blade" installation process;
FIG. 7 is another angle of FIG. 6;
FIG. 8 is a perspective view of a component "blade";
FIG. 9 is a perspective view of a component "straight pin";
fig. 10 is a perspective view of the component "tilt pin".
In the figure: 1. the novel hydraulic support comprises a disc body, a boss, a blade, a mounting piece, a first pin hole, a second pin hole, a straight pin, a first inclined hole, a second inclined hole, an inclined pin, a first shaft hole and a second shaft hole.
Detailed Description
In order to make the objects, technical solutions and advantages of the technical solutions of the present disclosure more clear, the technical solutions of the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings of the specific embodiments of the present disclosure.
Like reference numerals in the drawings denote like parts. It should be noted that the described embodiments are some, but not all embodiments of the present disclosure.
All other embodiments, which can be made by one of ordinary skill in the art without the need for inventive faculty, are within the scope of the present disclosure, based on the described embodiments of the present disclosure.
Example 1
The turbine blade disc structure comprises a disc body 1, a boss 2, blades 3 and a mounting piece 4 which are respectively made of fiber reinforced ceramic matrix composite materials; the structure is as shown in fig. 1 to 10, and comprises: a tray body 1, wherein the number of the tray bodies 1 is at least two; fig. 5 and 6 show that the tray 1 has a plurality of trays arranged in parallel; wherein the thickness of the individual discs 1 is selected to be 5-8mm, in which state the discs can reach a high densification production level relatively fast. The boss 2 is at least one, as shown in fig. 7, the boss 2 abuts against the disc body 1, and the centers of the boss 2 and the disc body 1 are located on the same axis. Blades 3, the number of the blades 3 is at least three, and fig. 1 shows an effect diagram after the blades 3 are installed around the disc 1; as shown in fig. 8, each of the blades 3 has a fixed integral mount 4, respectively; fig. 1 shows that at least three blades 3 are radially distributed around the center of the disc 1 and abut against the outer edge of the disc 1; referring to fig. 2, the mounting member 4 is located between at least two of the trays 1 and is fixedly connected to at least two of the trays 1. Wherein the two parts of the blade 3 and the mounting piece 4 are also made of fiber reinforced ceramic matrix composite materials, and the connection position of the blade 3 and the mounting piece 4 ensures the continuity of fibers through bending of the fibers.
Referring to fig. 3, each of the trays 1 has at least three first pin holes 5, and at least three first pin holes 5 are located near the middle of the tray 1 and are radially distributed at the center of the tray 1. As shown in fig. 4, the boss 2 has at least three second pin holes 6; when the boss 2 abuts against the disc 1 and the center of the boss 2 overlaps with the center of the disc 1, the second pin hole 6 is on the same axis as the first pin hole 5. The number of the straight pins 7 is at least three, see fig. 5, the straight pins 7 simultaneously penetrate through the first pin holes 5 and the second pin holes 6, the straight pins 7 are fixedly connected with the tray body 1 and the boss 2, the step of installing the straight pins 7 is shown in fig. 5, and the effect of the installed straight pins 7 is shown in fig. 1.
Referring to fig. 3, each of the trays 1 is provided with at least three first inclined holes 8, that is, as shown in fig. 3, a circle of holes are uniformly distributed on the outer edge of the tray 1, and the number of the holes is identical to that of the blades 3. At least three first inclined holes 8 are positioned near the edge of the tray body 1 and are radially distributed along the center of the tray body 1. Referring to fig. 8, each of the mounts 4 has a second inclined aperture 9; as shown in fig. 6 and 7, when the mounting member 4 abuts against the tray body 1, the first inclined hole 8 and the second inclined hole 9 are on the same axis; and at least three inclined pins 10 are provided, referring to fig. 6 and 7, the inclined pins 10 pass through the first inclined holes 8 and the second inclined holes 9 at the same time, and the inclined pins 10 are fixedly connected with the tray body 1 and the mounting piece 4.
As shown in fig. 7, at least two of the trays 1 are spaced apart from at least one of the bosses 2.
Referring to fig. 3 and 4, each of the trays 1 has a first shaft hole 11; each boss 2 has a second shaft hole 12; the first shaft hole 11 and the second shaft hole 12 are coaxial.
As shown in fig. 6 and 7, the second inclined holes 9 in at least two of the trays 1 are respectively located at different positions or non-parallel positions of the trays 1, and the second inclined holes 9 in the two trays 1 form an axis of inclination angle.
Example 2
The turbine blade disk production method of the present invention, which can be used to produce the apparatus of example 1; the method specifically comprises the following steps:
The total thickness of the turbine blade disc is confirmed,
The thickness of the tray body 1 is 5-8mm, so that the tray body 1 can reach a high densification preparation level faster;
the number of the disk bodies 1 and the thickness and the number of the bosses 2 are selected according to the total thickness of the turbine blade disks and the actual thickness of the single disk body 1;
The different disc bodies 1 are separated by the boss 2 and assembled;
fixedly connecting the disk body 1 with the boss 2, and performing secondary deposition and solidification to obtain a main body part of the turbine blade disk;
blades 3 fixedly connected with the disc body 1 are uniformly distributed around the outer edge part of the disc body 1.
Further, the tray body 1 and the boss 2 are fixedly connected through a straight pin 7;
a fixed integral mounting piece 4 is arranged below the blade 3, and the mounting piece 4 is arranged between the two disc bodies 1;
The disc body 1 and the blades 3 are fixedly connected through inclined pins 10; and the inclined pin 10 is inserted into the tray 1 and the mount 4 at an inclined angle.
Example 3
The method for balancing the strength and the thickness of the turbine blade disc is completed by adopting the method described in the embodiment 2.
Example 4
The aero-engine of the present invention, other structures in the engine all employ prior art products, wherein the turbine blade disc employs the turbine blade disc structure described in example 1 and/or the apparatus produced by the turbine blade disc production method described in example 2.
The terms first, second and the like in the description and in the claims, are not used for any order, quantity or importance, but are used for distinguishing between different elements. Likewise, the terms "a," "an," or "the" and similar terms do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprising" or "comprises", and the like, is intended to mean that elements or items that are present in front of "comprising" or "comprising" are included in the word "comprising" or "comprising", and equivalents thereof, without excluding other elements or items. "upper", "lower", "left", "right", etc. are used merely to indicate relative positional relationships, which may also be changed when the absolute position of the object to be described is changed.
The preferred embodiments of the present invention described above are not intended to limit the present invention, and the scope of the present invention is defined by the appended claims, and other embodiments can be obtained from the drawings without inventive faculty to those skilled in the art, and any modifications based on the claims of the present invention are also the scope of the present invention.
Claims (10)
1. Turbine blade disc structure, characterized in that it comprises:
the tray body is a plurality of tray bodies;
The number of the bosses is several, the bosses are abutted against the disc body, and the bosses and the circle center of the disc body are positioned on the same axis;
The plurality of blades are provided with a plurality of fixed and integrated mounting pieces respectively; the blades are radially distributed at the center of the disc body and are abutted against the outer edge of the disc body; the mounting piece is positioned between at least two disc bodies and fixedly connected with the at least two disc bodies.
2. The turbine blade disc structure as claimed in claim 1, characterized by comprising:
Each tray body is provided with a plurality of first pin holes, and the first pin holes are positioned close to the middle part of the tray body and are radially distributed at the center of the tray body;
The boss is provided with a plurality of second pin holes; the second pin hole is coaxial with the first pin hole;
The straight pins penetrate through the first pin holes and the second pin holes at the same time, and are fixedly connected with the disc body and the boss.
3. The turbine blade disc structure as claimed in claim 1, characterized by comprising:
each tray body is provided with a plurality of first inclined holes, and the first inclined holes are positioned close to the edges of the tray bodies and are radially distributed in the center of the circle of the tray bodies;
each mounting piece is provided with a second inclined hole, and when the mounting piece abuts against the disc body, the first inclined holes and the second inclined holes are positioned on the same axis;
the inclined pins penetrate through the first inclined holes and the second inclined holes at the same time, and are fixedly connected with the tray body and the mounting piece.
4. The turbine blade disk structure of claim 1 or 2 wherein at least two of said disks are spaced from at least one of said bosses.
5. The turbine blade disc structure according to claim 1, wherein each of the disc bodies has a first shaft hole, respectively;
Each boss is provided with a second shaft hole respectively; the first shaft hole and the second shaft hole are positioned on the same axis.
6. The turbine blade disk structure of claim 1 wherein the second inclined holes in at least two of said disks are respectively in different or non-parallel positions of said disks, the second inclined holes in two of said disks forming an axis of inclination.
7. A method of producing a turbine blade disc, comprising:
The total thickness of the turbine blade disc is confirmed,
The thickness of each disc body is 5-8mm, so that the disc body can reach a high densification preparation level quickly;
selecting the number of the disk bodies and the thickness and the number of the bosses according to the total thickness of the turbine blade disk and the actual thickness of the single disk body;
the different disc bodies are separated by the boss and assembled;
Fixedly connecting the disk body with the boss, and performing secondary deposition and solidification to obtain a main body part of the turbine blade disk;
blades fixedly connected with the tray body are uniformly distributed around the outer edge part of the tray body.
8. The production method of a turbine blade disc according to claim 7, characterized in that the disc body and the boss are fixedly connected by a straight pin;
a fixed integral mounting piece is arranged below the blade and is arranged between the two disc bodies;
The disc body is fixedly connected with the blades through inclined pins; and the oblique pin is inserted into the tray body and the mounting member at an oblique angle.
9. A method for balancing the strength and thickness of a turbine blade disc, characterized in that the turbine blade disc production method according to any one of claims 7 to 8 is used.
10. Aeroengine, characterised in that it comprises at least a turbine blade disc structure according to any one of claims 1 to 6 and/or an apparatus produced by a method according to any one of claims 7 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410017532.XA CN118030194A (en) | 2024-01-03 | 2024-01-03 | Blade disc structure, production method, strength and thickness balancing method and engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410017532.XA CN118030194A (en) | 2024-01-03 | 2024-01-03 | Blade disc structure, production method, strength and thickness balancing method and engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118030194A true CN118030194A (en) | 2024-05-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410017532.XA Pending CN118030194A (en) | 2024-01-03 | 2024-01-03 | Blade disc structure, production method, strength and thickness balancing method and engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118030194A (en) |
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2024
- 2024-01-03 CN CN202410017532.XA patent/CN118030194A/en active Pending
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