CN217354887U - Rotor blade, blade disc assembly and compressor rotor - Google Patents

Abstract

The utility model provides a rotor blade, including the tenon to inject the blade height direction, the tenon has the surface, and the surface is the surface of revolution, and the surface of revolution has axis and generating line, and the axis extends along the blade height direction, and the generating line has the convergent section, and the convergent section is close to the axis from the bottom side towards the top side gradually on the blade height direction. The utility model also provides a bladed disk subassembly and compressor rotor including above-mentioned rotor blade. With the rotor blade, the initial unbalance amount of the rotor can be reduced.

Description

Rotor blade, blade disc assembly and compressor rotor

Technical Field

The utility model relates to a rotor blade still relates to a bladed disk subassembly and a compressor rotor.

Background

In the field of aircraft engines and gas turbines, a compressor, which is one of core components, needs to compress gas in a flow passage to do work through the rotation of rotor blades in the actual working process. Especially, the unbalance of the rotor is ensured to be at a smaller level under high pressure, high temperature and high rotating speed so as to reduce the vibration of the rotor and ensure the safety of the engine.

Accordingly, it is desirable to provide an optimized rotor blade that reduces the initial imbalance of the rotor.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a rotor blade can reduce the initial unbalance amount of rotor.

The utility model provides a rotor blade, including the tenon to inject the blade height direction, the tenon has the surface, the surface is the surface of revolution, the surface of revolution has axis and generating line, the axis extends along the blade height direction, the generating line has the convergent section, the convergent section is close to from the bottom side towards the top side gradually on the blade height direction the axis.

In one embodiment, the busbar further has a top side diverging section that is continuous with a top side of the tapering section.

In one embodiment, the busbar further has a bottom side divergent section that is continuous with a bottom side of the convergent section.

In one embodiment, the bus bar is a smooth curve.

The utility model provides a bladed disk subassembly, including the rotor dish to inject circumference, the rotor dish distributes along circumference has a plurality of tongue-and-grooves, the bladed disk subassembly still includes aforementioned rotor blade, and is a plurality of rotor blade respectively adapt to in a plurality of tongue-and-grooves.

In one embodiment, the rotor disc comprises two sub-discs, each having a slot in the periphery, the two sub-discs abutting, whereby the slots of the two sub-discs together constitute the mortise.

In one embodiment, each of the sub-discs has an intermediate portion located inside the outer peripheral portion, each sub-disc has a through-hole in the intermediate portion, and the two sub-discs are butted by fastening members passing through the through-holes of the two sub-discs.

In one embodiment, each sub disc is provided with a mating spigot at the intermediate portion through which the two sub discs are positioned.

In one embodiment, the mating seam allowance is located outside the perforation.

The utility model provides a compressor rotor, including a plurality of aforementioned bladed disk subassemblies, divide and belong to two bladed disk subassemblies and adjacent minute dish parts as an organic whole.

The tenon of the rotor blade is provided with the revolution surface, so that the tenon can be matched with the mortise with the revolution surface, and the stress distribution in the revolution direction can be optimized, so that the connection structure is uniformly distributed in a whole circle, the initial unbalance amount of the rotor is reduced, and the rotor vibration caused by the unbalance amount is reduced.

Among the above-mentioned bladed disk subassembly, above-mentioned rotor blade passes through the surface of revolution cooperation with corresponding rotor and is connected, and rotor blade's fixed mode is simple, reliable, need not solitary locking structure, moreover, can increase rotor blade and rotor disk's area of contact, reduces local stress.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 is a perspective view of an exemplary rotor blade.

FIG. 2 is a cross-sectional view of an exemplary blisk assembly.

Fig. 3 is a perspective view of an exemplary wheel.

Fig. 4 is a perspective view of another tray that interfaces with the tray of fig. 3.

Fig. 5 is a perspective view of an exemplary rotor disk.

FIG. 6 is a perspective view of an exemplary blisk assembly.

FIG. 7 is a cross-sectional view of an exemplary compressor rotor with rotor blades omitted.

Detailed Description

The present invention will be further described with reference to the following detailed description and the accompanying drawings, wherein the following description sets forth more details for the purpose of providing a thorough understanding of the present invention, but it is obvious that the present invention can be implemented in many other ways different from those described herein, and those skilled in the art can make similar generalizations and deductions based on the practical application without departing from the spirit of the present invention, and therefore, the scope of the present invention should not be limited by the contents of the detailed description.

For example, a first feature described later in the specification may be formed over or on a second feature, and may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.

The inventor analyzes and thinks that when designing a gas compressor, such as a rotor blade, a disk drum and the like, the structure of the rotor blade and the mounting structure thereof are optimized, and the initial unbalance amount of the rotor is reduced. At the same time, the stress distribution needs to be optimized as much as possible, so that the service life of the rotor structure is prolonged. The operation difficulty of installing the blades is also required to be considered, and the damage risk of parts due to disassembly and assembly is reduced.

Under the current technical conditions, in order to realize the installation of the rotor blade, an axial tongue-and-groove or circumferential tongue-and-groove installation method is generally adopted.

Both of these mounting methods have the following disadvantages. For the mode of axial tongue-and-groove installation, because there is the clearance between the tenon of the tenon groove of dish and blade, the phenomenon of axial gas leakage appears easily, and blade locking structure exposes in the gas of high-speed flow, appears eroding easily. For the circumferential tongue-and-groove installation mode, the initial unbalance amount is increased because the locking block is generally arranged at a certain position fixed in the circumferential direction, the unbalance amount needs to be reduced by adding the balance block, and the locking block for installing the blade is limited by the installation space and the size, so that the blade body is not easy to operate and is easy to damage.

Therefore, the utility model provides a following rotor blade, bladed disk subassembly and compressor rotor structure, the intention optimizes rotor blade's self structure and mounting structure, reduces the initial unbalance amount of rotor. In addition, the installation difficulty of the rotor blade is reduced, and the fixing mode of the rotor blade is simplified, so that a locking structure is not needed. Furthermore, it is also intended to increase the contact area at the connection of the blades and the rotor disk, reducing local stresses.

FIG. 1 illustrates an example configuration of a rotor blade 10 provided by the present invention. FIG. 2 illustrates an example configuration including a blisk assembly 100. It is to be understood that the drawings are designed solely for purposes of illustration and not as an isometric definition, and should not be construed as limiting the scope of the invention as it is actually claimed.

The rotor blade 10 includes a dovetail 1 and defines a blade height direction H0 (in fig. 1, a generally up-down direction). The tenon 1 has an outer surface 11.

The outer surface 11 is a surface of revolution. The surface of revolution has an axis X0 and a generatrix L0. The axis X0 extends in the blade height direction H0. The bus bar L0 has a tapered section L1. The tapered section L1 gradually approaches the axis X0 from the bottom side toward the top side in the blade height direction H0.

A surface of revolution is also a surface which is formed in space when a curve revolves around a fixed straight line, and is also called a surface of revolution. Wherein the fixed straight line is the axis of the revolution surface, and the curve is the generatrix of the revolution surface. The surface of revolution of the generatrix L0 with the tapered section L1 in fig. 1 may also be referred to as a conical surface of revolution, or conical surface.

The tenons 1 of the rotor blade 10 described above have an outer surface 11 in the form of a surface of revolution and thus can cooperate with corresponding mortises to form stops in all directions, so that stress distribution can be optimized, the initial unbalance of the rotor is reduced and the life of the rotor blade 10 can be extended.

It is to be understood that references herein to two directions being "perpendicular", "coincident", "parallel", etc. do not necessarily satisfy mathematically strict angular requirements, but allow for a range of tolerances, e.g. within 20 ° compared to mathematically required angles, whereas "along" a direction means having at least a component in that direction, preferably within 45 ° and more preferably within 20 ° or even 10 ° from that direction.

Referring to fig. 2, the bus bar L0 may also have a top-side diverging section L21. The top side diverging section L3 may be continuous with the top side of the tapering section L1.

It will be understood that spatial relational terms, such as "top," "bottom," "upper," "lower," and the like, may be used herein to describe one element or feature's relationship to another element or feature as illustrated in the figures, for ease of description with reference to the orientations of fig. 1 and 2, and in particular the blade height direction H0, and are intended to encompass other orientations of the element or component in use or operation in addition to the orientations depicted in the figures. For example, if the components in the figures are turned over, elements described as "on top" of other elements or features would then be oriented "on bottom" of the other elements or features, and the spatially relative descriptors used herein should be interpreted accordingly.

In the illustrated embodiment, the bus bar L0 may also have a bottom side diverging section L22. The bottom side diverging section L22 may be continuous with the bottom side of the tapering section L1.

In the illustrated embodiment, the bus bar L0 may be a smooth curve.

It is understood that the use of particular words herein to describe embodiments of the invention, such as "one embodiment," "another embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the invention is included. Therefore, it is emphasized and should be appreciated that two or more references to "one embodiment" or "another embodiment" in various places throughout this specification are not necessarily to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the invention may be combined as appropriate.

Fig. 1 shows a rotor blade 10 with a surface of revolution on a dovetail 1, and fig. 1 also shows a rotor blade body 5 and a platform 6 of the rotor blade 10.

FIG. 2 illustrates an example cross-sectional configuration of the blisk assembly 100, and FIG. 6 illustrates a perspective configuration of the blisk assembly 100 with the rotor blade 10 installed.

Referring to fig. 2 and 6, blisk assembly 100 may include rotor disk 20 and define circumferential direction C0. The rotor disk 20 may have a plurality of tongues 2 distributed, for example evenly distributed, along the circumferential direction C0. The blisk assembly 100 may also include the aforementioned rotor blade 10, with a plurality of rotor blades 10 respectively fitted to the aforementioned plurality of mortises 2.

It is understood that "plurality" herein means more than two, including two, three, four, five, etc. The aforementioned blade height direction H0 is substantially coincident with the radial direction of the rotor disk 20.

With reference to fig. 2 to 6, the rotor disc 20 may comprise two sub discs 3a, 3 b. Fig. 3, 4 and 5 show an example perspective configuration of the disks 3a, 3b and the disks 3a, 3b jointly assembled into the rotor disk 20, respectively. As shown in fig. 3, taking the sub-discs 3a as an example, each sub-disc 3a may have a slot 32 in the peripheral portion 31. The two partial disks 3a, 3b are joined together, whereby the slots 32 of the two partial disks 3a, 3b together form the tongue-and-groove 2.

In fig. 2, the partial disk 3a is the left disk of the rotor disk 20, and the partial disk 3b is the right disk of the rotor disk 20. The pairs of slots 32 of the two sub-discs 3a, 3b are butted to form a plurality of mortises 2, and fig. 5 shows the mortises 2 formed after the two sub-discs 3a, 3b are connected. The mortise 2 is also a blade mounting groove. The blade mounting groove is not an axial mortise, nor a circumferential mortise, but a pit-type spherical mortise.

In the illustrated embodiment, taking the subdivisions 3a as an example, each subdivision 3a has an intermediate portion 33 located inside the peripheral portion 31. Each partial disc 3a may have a perforation 34 in the middle part 33, the two partial discs 3a, 3b being butted by fasteners through the perforations 34 of the two partial discs 3a, 3 b. For example, the fasteners may be bolts and the perforations 34 may be bolt holes.

In the illustrated embodiment, taking the subdivisions 3a as an example, each subdivisions 3a may be provided with an engagement spigot 35 at the intermediate portion 33. The two part- discs 3a, 3b can be positioned by means of the fitting seam allowance 35. The mating seam 35 may also be a connection seam, with the positioning being accomplished by a step feature fit.

In the illustrated embodiment, the mating seam allowance 35 may be located outside of the perforation 34. Thus, the installation is convenient.

In the illustrated embodiment, after the two sub-trays 3a and 3b are butted, a hollow space S0 may be formed between them, as shown in fig. 2. The hollow design between the two portions of the rotor disk 20 may contribute to weight reduction and may result in a reduction in the rotational inertia of the rotor disk.

Among the above-mentioned bladed disk subassembly, the rotor dish divide into left side dish and right side dish, has half blade mounting groove, bolt hole, cooperation tang on the left side dish, has half blade mounting groove, bolt hole, cooperation tang on the right side dish. The two adjacent disc bodies are connected through bolts, so that a complete blade mounting groove can be formed. The blade disc assembly is simple in structural form, uniform in circumferential direction and capable of reducing the initial unbalance amount of the rotor. Moreover, the rotor blade is simple in fixing mode, special tools are not needed, and an independent locking structure is not needed, so that the mounting difficulty of the rotor blade can be reduced. In addition, the contact area of the connecting part of the rotor blade and the rotor disc can be increased, and the local stress can be reduced.

Fig. 7 shows an example cross-sectional configuration of a compressor rotor 200. The compressor rotor 200 may include a plurality of the aforementioned blisk assemblies 100. The subdivisions belong to two blisk assemblies 100 and the adjacent subdivisions 3a or 3b may be an integral part. In fig. 7, the segment disk 3b belonging to the blisk assembly 100' and the segment disk 3a belonging to the blisk assembly 100 ″ are adjacent to each other, and they may be integrally formed by being connected together by a cylindrical connection portion 3 c. In other words, in fig. 7, the compressor rotor 200 may include multiple stages of rotor blades.

In the compressor rotor, each stage of rotor disk is divided into two parts, each part is provided with a half revolution surface, when the rotor blade is arranged on one disk body, and then the other disk body is tightly pressed, a complete revolution surface, namely a tongue-and-groove, can be formed. The two disc bodies can be matched through the seam allowance and then connected through the bolt.

In the compressor rotor, the rotor blade tenon with the revolution surface and the rotor disc mortise with the revolution surface matched with the rotor blade tenon are arranged, and the circumferentially complete mortise is composed of two parts. When the rotor blades are installed, the rotor blades can be installed on the sub-disc on one side firstly, and after all the rotor blades are installed in the circumferential direction, the sub-disc on the other side is pressed tightly, so that the installation of the rotor blades is achieved. This structural style is simple, need not solitary blade locking structure, and structural style reduces the rotor unbalance amount at circumference equipartition, increases rotor blade and the area of contact of dish connection position, reduces local stress.

Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.

Claims (10)

1. A rotor blade comprising a dovetail and defining a blade height direction, wherein the dovetail has an outer surface that is a surface of revolution having an axis extending in the blade height direction and a generatrix having a tapered section that tapers in the blade height direction from a bottom side toward a top side toward the axis.

2. The rotor blade according to claim 1, wherein the bus bar further has a top side diverging section that is continuous with a top side of the converging section.

3. The rotor blade according to claim 1, wherein the busbar further has a bottom side divergent section that is continuous with a bottom side of the convergent section.

4. The rotor blade according to claim 1, wherein the generatrix is a smooth curve.

5. A blisk assembly comprising a rotor disc and defining a circumferential direction, said rotor disc having a plurality of mortises distributed along the circumferential direction, characterized in that it further comprises a rotor blade according to any one of claims 1 to 4, the plurality of rotor blades being respectively adapted to said plurality of mortises.

6. A blisk assembly according to claim 5, wherein the rotor disc comprises two sub-discs, each having a slot in the periphery, the two sub-discs abutting, whereby the slots of the two sub-discs together constitute the mortise.

7. The blisk assembly according to claim 6, wherein each sub-disk has a middle portion located inside the outer peripheral portion, each sub-disk having a perforation in the middle portion, the two sub-disks being butted by fasteners passing through the perforations of the two sub-disks.

8. The blisk assembly according to claim 7, wherein each sub-disk is provided with a mating spigot at the intermediate portion, the two sub-disks being positioned by the mating spigots.

9. The blisk assembly according to claim 8, wherein the mating seam allowance is located outside the perforation.

10. A compressor rotor, comprising a plurality of blisk assemblies according to any one of claims 5 to 9, each blisk assembly being divided into two blisk assemblies and adjacent subdivisions being integral parts.

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