CN217926077U - Low-cost lightweight triangular rotor part for aeroengine - Google Patents

Abstract

A low-cost lightweight triangular rotor part for an aeroengine is characterized in that three corners of the low-cost lightweight triangular rotor part are respectively provided with a radial seal groove; the triangular rotor component comprises a nodular/alloy cast iron core as a supporting framework, and a triangular rotor body which is cast outside the nodular/alloy cast iron core and adopts an aluminum alloy material, wherein the nodular/alloy cast iron core comprises three reinforcing columns which are respectively located at three corners of the triangular rotor component, and every two reinforcing columns are connected through a connecting rib. The utility model can effectively improve the wear resistance and the groove wall strength of the radial seal groove at the corner of the triangular rotor part through the three reinforcing columns, thereby prolonging the service life of the whole machine; meanwhile, aluminum alloy materials with lower mass density and relatively low price are cast outside the nodular/alloy cast iron core to form the triangular rotor body, so that the manufacturing cost of the triangular rotor part is effectively reduced, the increasing light-weight requirement of the aviation rotor engine is met, and the reliability of the triangular rotor part is considered.

Description

Low-cost lightweight triangular rotor part for aeroengine

Technical Field

The utility model belongs to the technical field of the aeroengine, concretely relates to aeroengine is with low-cost lightweight triangle rotor part.

Background

At present, the materials of the triangle rotor of the domestic aviation rotor engine all adopt nodular cast iron or alloy cast iron, and the defects of the adopted nodular cast iron and the alloy cast iron are as follows: the mass density of the material is high, so that the power-weight ratio of the whole rotor engine is low, and the increasing light-weight requirement of the aviation rotor engine cannot be met; if the triangular rotor material adopts titanium alloy with relatively low density, the price is high, and the problem of titanium fire cannot be solved; if the triangular rotor is made of aluminum alloy, the service life of the engine is greatly shortened due to insufficient local strength and poor wear resistance.

Disclosure of Invention

In order to solve the technical problem, the utility model aims at providing an aeroengine is with low-cost lightweight triangle rotor part, this scheme not only can effectively reduce the manufacturing cost of triangle rotor part, can satisfy aeroengine's lightweight requirement moreover, compromise the reliability of triangle rotor part simultaneously.

In order to accomplish the above object, the utility model adopts the following technical scheme: the utility model provides a low-cost lightweight triangle rotor part for aeroengine, the three bight department of this triangle rotor part sets up radial seal groove 3 respectively, the triangle rotor part includes nodular cast iron core 2 or alloy cast iron core as supporting framework, casts in the nodular cast iron core or alloy cast iron core outside and adopts aluminium alloy material's triangle rotor body 1, nodular cast iron core or alloy cast iron core are including the three enhancement post 5 that is located the three bight department of triangle rotor part respectively, connect through splice bar 6 between per two enhancement posts 5.

Has the advantages that: the utility model relates to a low-cost lightweight triangular rotor part for an aeroengine, which can effectively improve the wear resistance and the groove wall strength of a radial seal groove at the corner part of the triangular rotor part through three reinforcing columns, thereby prolonging the service life of the whole machine; meanwhile, an aluminum alloy material with lower mass density and relatively low price is cast outside the nodular cast iron core or the alloy cast iron core to form the triangular rotor body, so that the manufacturing cost of the triangular rotor component is effectively reduced, the increasing light-weight requirement of the aviation rotor engine is met, and the reliability of the triangular rotor component is considered.

Furthermore, a plurality of heat dissipation reinforcing ribs 4 extending along the axial direction of the triangular rotor body are arranged on the inner wall of the corner part close to the triangular rotor body 1.

Has the advantages that: the design can effectively reduce the material quantity of triangle rotor body on the one hand like this, and on the other hand can play the radiating effect to triangle rotor part.

Furthermore, a plurality of circumferential positioning ribs 7 distributed along the axial direction are arranged on the outer wall of each reinforcing column 5.

Furthermore, a plurality of radial positioning ribs 8 distributed along the circumferential direction are arranged on the outer wall of each reinforcing column 5.

Has the advantages that: by means of the circumferential positioning ribs and the radial positioning ribs, the fact that the triangular rotor body and the nodular cast iron core which are cast completely have enough bonding strength is guaranteed.

Furthermore, a positioning boss 9 is convexly arranged on the end face of each reinforcing column 5.

Has the advantages that: with the help of the location boss, be convenient for carry out accurate location when the casting aluminum alloy.

The foregoing description is only an overview of the technical solutions of the present invention, and in order to make the technical means of the present invention more clearly understood, the present invention may be implemented according to the content of the description, and in order to make the above and other objects, features, and advantages of the present invention more obvious and understandable, the following preferred embodiments are described in detail with reference to the accompanying drawings.

Drawings

Fig. 1 is a schematic structural diagram of a low-cost and lightweight delta rotor component for an aircraft engine according to the embodiment.

Fig. 2 is a schematic structural diagram of the triangular rotor body in the embodiment shown in fig. 1.

Fig. 3 is a schematic structural view of the spheroidal graphite cast iron core in the embodiment shown in fig. 1.

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The structure comprises a triangular rotor body 1, a nodular cast iron core 2, a radial sealing groove 3, a heat dissipation reinforcing rib 4, a reinforcing column 5, a connecting rib 6, a circumferential positioning rib 7, a radial positioning rib 8 and a positioning boss 9.

Detailed Description

Features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. In the drawings and the following description, at least some well-known structures and techniques have not been shown in detail in order to avoid unnecessarily obscuring the present invention; also, the dimensions of some of the structures may be exaggerated for clarity. The features, structures, or characteristics described hereinafter may be combined in any suitable manner in one or more embodiments, and furthermore, the terms "first", "second", "third", and so forth are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

The directional terms used in the following description are intended to refer to directions shown in the drawings, and are not intended to limit the specific structure of the present invention. In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected. The specific meaning of the above terms in the present invention can be understood as the case may be, by those of ordinary skill in the art.

Referring to fig. 1, an embodiment of a low-cost and light-weight delta rotor component for an aviation rotor engine according to the present invention is shown. In the embodiment, three corners of the triangular rotor component are respectively provided with a radial sealing groove 3, and the radial sealing grooves are used for assembling radial sealing pieces; the triangular rotor component comprises a triangular rotor body 1 and a nodular cast iron core 2, the triangular rotor body 1 is made of aluminum alloy materials, the aluminum alloy is cast on the outer side of the nodular cast iron core 2, the triangular rotor body 1 is formed after casting is finished, and meanwhile, the triangular rotor body is firmly combined with the nodular cast iron core; the nodular cast iron core 2 is used as a supporting framework of the triangular rotor part, and is subjected to normalizing treatment before casting so as to obtain the best wear resistance and strength.

Referring to fig. 2, a plurality of heat dissipating ribs 4 extending along the axial direction of the delta rotor body are disposed on the inner wall near the corner of the delta rotor body, so that the material usage of the delta rotor body can be effectively reduced and the delta rotor component can be cooled.

Referring to fig. 3, the nodular cast iron core 2 includes three reinforcing columns 5 uniformly distributed along the circumferential direction, and each two reinforcing columns 5 are connected by at least one connecting rib 6, so as to form a triangular supporting framework, so that the reinforcing columns are accurately positioned at three corner positions of the triangular rotor component when the aluminum alloy is cast, and thus, the strength and the wear resistance of a radial sealing groove at the corner of the triangular rotor component are improved, and the service life of the whole engine is further improved. Set up a plurality of circumference location muscle 7 along axial distribution, a plurality of radial orientation muscle 8 along circumference distribution on the outer wall of every enhancement post 5, with the help of the existence of circumference location muscle and radial orientation muscle, guarantee that the triangle rotor body 1 and the nodular cast iron core 2 that the casting was accomplished have sufficient bonding strength. The end face of each reinforcing column 5 is convexly provided with a positioning boss 9, and accurate positioning is facilitated during aluminum alloy casting by virtue of the positioning bosses.

In the embodiment, the three reinforcing columns distributed in a triangular shape can effectively improve the groove wall strength and the wear resistance of the radial sealing groove at the corner position of the triangular rotor component, so that the service life of the whole machine is prolonged; meanwhile, an aluminum alloy material with lower mass density is cast outside the nodular cast iron core to form the triangular rotor body, the increasing lightweight requirement of an aviation rotor engine can be met, the reliability of the triangular rotor component can be considered, and meanwhile, the manufacturing cost of the triangular rotor component can be greatly reduced due to the fact that the price of the aluminum alloy is relatively low.

Of course, in other embodiments of the present invention, an alloy cast iron core may be used instead of a ductile cast iron core as the supporting framework of the triangular rotor component.

In the above, only the preferred embodiment of the present invention is shown, and any person skilled in the art can easily modify, change and modify the above embodiments according to the technical features of the present invention without departing from the technical scope of the present invention.

Claims (5)

1. The utility model provides an aeroengine is with low-cost lightweight triangle rotor part, the three bight of this triangle rotor part sets up radial seal groove (3) respectively, characterized by the triangle rotor part includes nodular cast iron core (2) or alloy cast iron core, the casting as supporting framework and adopts aluminium alloy material's triangle rotor body (1) in nodular cast iron core or alloy cast iron core outside, nodular cast iron core or alloy cast iron core are including three enhancement post (5) that are located the three bight department of triangle rotor part respectively, connect through splice bar (6) between per two enhancement post (5).

2. A low-cost and light-weight triangular rotor part for an aircraft engine according to claim 1, wherein a plurality of heat dissipation ribs (4) extending in the axial direction of the triangular rotor body are provided on the inner wall of the triangular rotor body (1) near the corner.

3. A low-cost lightweight triangular rotor component for an aircraft engine according to claim 1, wherein a plurality of circumferential positioning ribs (7) are arranged on the outer wall of each reinforcing column (5) and distributed along the axial direction.

4. A low cost lightweight triangular rotor member for an aircraft engine according to claim 1, wherein the outer wall of each reinforcing column (5) is provided with a plurality of radial positioning ribs (8) distributed along the circumferential direction.

5. A low-cost lightweight triangular rotor component for an aircraft engine according to claim 1, wherein a positioning boss (9) is convexly provided on the end face of each reinforcing column (5).

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