Multi-stage casing for lightweight compression component of aero-engine

Abstract

A multi-stage casing for a lightweight compression component of an aero-engine comprises two split casing bodies, and each split casing body comprises a semicircular metal functional frame and a composite material plate of the semicircular metal functional frame; the metal functional frame comprises a front mounting edge, a rear mounting edge, a plurality of adjustable stator blade mounting rings arranged between the front mounting edge and the rear mounting edge, and split mounting edges connected to the two ends of the front mounting edge, the rear mounting edge and the adjustable stator blade mounting rings; the split mounting edges of the two metal functional frames are connected through bolts to form a whole ring structure; a plurality of assembly holes distributed in the circumferential direction are formed in the adjustable stator blade mounting ring; the composite material plates are arranged between the front mounting edge and the adjustable stator blade mounting rings, between the adjustable stator blade mounting rings and between the adjustable stator blade mounting rings and the rear mounting edge; an arc-shaped containing cavity is formed in the inner side of the composite material plate, a containing ring is arranged in the arc-shaped containing cavity, and the containing ring is made of aramid fiber or polyimide fiber reinforced composite materials.

Description

Technical Field

[0001] This application belongs to the technical field of the design of casings for aero-engine compression components, and particularly relates to a multi-stage casing for a lightweight compression component of an aero-engine. Background Art

[0002] The fan / compressor is an important compression component in an aero-engine. In addition to the conventional functions of force transmission, forming a flow path, and providing stator blade assembly, its casing also needs to have a high containment capacity.

[0003] Resin matrix composites have the characteristics of high specific strength and high specific stiffness. With the gradual maturity of their design and manufacturing technologies, they are gradually widely used in the design of fan / compressor casings and tend to replace the conventional casing design technologies.

[0004] Currently, the material selection and configuration of composite fan / compressor casings are mainly divided into three categories: high-strength fiber-wound reinforced metal casings, braided prepreg-wound all-composite casings, and all-composite split containment casings.

[0005] High-strength fiber-wound reinforced metal casings and braided prepreg-wound all-composite casings are mostly of integral ring structures with simple structural features. They are only applicable to single-stage fans / compressors and have been widely used in the design of fan casings for commercial large bypass engines. Due to the assembly characteristics of integral ring casings, for the cases where the number of fan / compressor stages is relatively large and the trend of the change in the height of the aerodynamic external flow path is inconsistent, there are problems such as poor assembly, and even the situation of impossible assembly. Moreover, the online inspection and repair of the engine cannot be realized, and the maintainability is poor. The all-composite split containment casing is relatively applicable to medium and small bypass engines under wide operating conditions.

[0006] The stator blades of the fan / compressor of medium and small bypass engines under wide operating conditions are often designed in an adjustable angle structural form. To realize the assembly and adjustment of the adjustable stator blades, a large number of circumferentially uniformly distributed assembly holes need to be opened at multiple positions on the all-composite split containment casing, resulting in a large range of fiber discontinuous regions on the all-composite split containment casing. The strength and stiffness of the all-composite split containment casing are highly sensitive to the punching. The mechanical properties such as strength and stiffness near the punching will be reduced by more than 50%, directly affecting the strength and stiffness of the casing. To supplement the loss of mechanical properties of the all-composite split containment casing, the method of increasing the thickness at the punching positions is usually adopted, but this technical method has little effect on strengthening the mechanical properties of the all-composite split containment casing with a large range of punching, and will greatly reduce the weight reduction effect of the all-composite split containment casing. Even more, the weight will increase compared with that of the conventional metal casing.

[0007] The all-composite split containment casing is a two-half-ring structure. There is a boundary effect at the split mounting edge of the containment ring, and the containment capacity is severely damaged. In addition, a large number of bolt holes are opened on the split mounting edge, and the fiber continuity is damaged, making it difficult to ensure the containment performance. When a blade is lost and impacts a position near the split mounting edge, it is extremely easy to occur that the all-composite split containment casing cannot bear the lost energy of the blade, resulting in containment failure and damage to the structural integrity of the casing.

[0008] The materials of all parts of the all-composite split containment casing are the same. In the face of the situation where the airflow is gradually pressurized and heated during the operation of the fan / compressor, in order to ensure the highest temperature usage requirements, the entire casing is made of a resin matrix composite material with high heat resistance. The front-stage fan / compressor casings with lower working temperatures are also forced to use composite materials with high heat resistance. However, the forming process difficulty and cost of the resin matrix composite material increase with the increase of its usage temperature, resulting in the all-composite split containment casing often having great processing difficulty, high manufacturing cost, and poor product quality.

[0009] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0010] The purpose of this application is to provide a multi-stage casing for a lightweight compression component of an aero-engine to overcome or mitigate at least one aspect of the known technical defects.

[0011] The technical solution of this application is as follows:

[0012] A multi-stage casing for a lightweight compression component of an aero-engine includes two split casings. Each split casing includes a semi-circular metal functional frame and its composite material plate;

[0013] The metal functional frame includes a front mounting edge, a rear mounting edge opposite to the front mounting edge, and a plurality of adjustable stator vane mounting rings arranged between the front mounting edge and the rear mounting edge. The split mounting edges are connected to both ends of the front mounting edge, the rear mounting edge, and the adjustable stator vane mounting rings;

[0014] The split mounting edges of the two metal functional frames are bolted together to form a complete ring structure;

[0015] The adjustable stator vane mounting ring has a plurality of circumferentially distributed assembly holes;

[0016] There are a plurality of composite material plates, which are arranged between the front mounting edge and the adjustable stator vane mounting ring, between the adjustable stator vane mounting rings, and between the adjustable stator vane mounting ring and the rear mounting edge;

[0017] There are front mounting edges, inner sides of rear mounting edges, both sides of the adjustable stator vane mounting ring, inner sides of split mounting edges, both sides of the composite material plate and mounting wings at both ends. Among them, the mounting wings on both sides of the composite material plate are connected to the mounting wings on the front mounting edge, the inner side of the rear mounting edge and both sides of the adjustable stator vane mounting ring by rivets; the mounting wings at both ends of the composite material plate are connected to the mounting wings on the inner side of the split mounting edge by rivets;

[0018] The composite material plate is made of carbon fiber reinforced resin matrix composite material;

[0019] There is an arc-shaped accommodating cavity on the inner side of the composite material plate, and an accommodating ring is arranged in the arc-shaped accommodating cavity. The accommodating ring is made of aramid or polyimide fiber reinforced composite material.

[0020] According to at least one embodiment of the present application, in the multi-stage casing for the lightweight compression component of the aero-engine described above, each composite material plate and its accommodating ring are made of composite materials with corresponding temperature resistance according to the working temperature grade of the fan / compressor at the axial position where they are located. The high temperature resistance of the composite material plates and their accommodating rings in the subsequent stages increases gradually according to the actual situation.

[0021] According to at least one embodiment of the present application, in the multi-stage casing for the lightweight compression component of the aero-engine described above, the front mounting edge, the rear mounting edge, the adjustable stator vane mounting ring and the split mounting edge are integrally formed by machining or connected by welding.

[0022] According to at least one embodiment of the present application, in the multi-stage casing for the lightweight compression component of the aero-engine described above, rabbets are provided on the front mounting edge and the rear mounting edge.

[0023] According to at least one embodiment of the present application, in the multi-stage casing for the lightweight compression component of the aero-engine described above, there are a plurality of positioning bosses on the outer side of the adjustable stator vane mounting ring, and positioning holes communicating with the assembly holes are provided on each positioning boss.

[0024] According to at least one embodiment of the present application, in the multi-stage casing for the lightweight compression component of the aero-engine described above, there are a plurality of axially arranged reinforcing ribs on the outer side of the mounting wings on the inner side of the split mounting edge.

[0025] The present application has at least the following beneficial technical effects:

[0026] A multi-stage casing for the lightweight compression component of an aero-engine is provided. On the basis of overcoming the problems of the existing casing in terms of assembly, maintainability, reliability, etc., the forming process and manufacturing cost of the composite material components are fully considered, and the manufacturing cost and quality control of the composite material containment casing are realized from the design level. Description of the Drawings

[0027] Figure 1It is a schematic diagram of a multi-stage casing for a lightweight compression component of an aero-engine provided by an embodiment of the present application;

[0028] Figure 2 It is a cross-sectional view of a split casing provided by an embodiment of the present application;

[0029] Figure 3 It is a schematic diagram of a metal functional framework provided by an embodiment of the present application;

[0030] Figure 4 It is a schematic diagram of the bolt connection position between the split mounting edges of two metal functional frameworks provided by an embodiment of the present application;

[0031] Figure 5 It is a schematic diagram of a front mounting edge provided by an embodiment of the present application;

[0032] Figure 6 It is a schematic diagram of a rear mounting edge provided by an embodiment of the present application;

[0033] Figure 7 It is a schematic diagram of an adjustable stator vane mounting ring provided by an embodiment of the present application;

[0034] Figure 8 It is a partial cross-section of an adjustable stator vane mounting ring provided by an embodiment of the present application;

[0035] Figure 9 It is a schematic diagram of a composite material plate provided by an embodiment of the present application;

[0036] Figure 10 It is a cross-sectional view of a composite material plate provided by an embodiment of the present application;

[0037] Wherein:

[0038] 1 - Split casing; 2 - Metal functional framework; 3 - Composite material plate;

[0039] 21 - Front mounting edge; 22 - Rear mounting edge; 23 - Adjustable stator vane mounting ring; 24 - Split mounting edge; 25 - Positioning boss; 26 - Reinforcing rib;

[0040] 31 - Containment ring.

[0041] For better illustration of this embodiment, some contents of the drawings are omitted, enlarged or reduced, which are only for exemplary illustration and should not be construed as a limitation to the present application. Detailed implementation manners

[0042] To make the technical solutions and their advantages of this application clearer, the following will further describe the technical solutions of this application clearly and completely in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application and not to limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design.

[0043] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The "including" used in the description of this application means that the concept appearing before this word covers the concepts listed after this word and their equivalents, without excluding other related concepts.

[0044] In addition, the words indicating directions used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that unless otherwise clearly specified and limited, the words such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to the specific situation.

[0045] In view of the technical problems of poor assembly of the multi-stage fan / compressor integral casing, the need for adjustable stator blades of the wide-operating-condition fan / compressor, serious reduction of the stiffness and strength of the component due to continuous large-range composite material openings, and poor anti-impact performance of the split mounting edge, the embodiment of this application provides a multi-stage casing for an aero-engine lightweight compression component, which can realize the function of adjustable multi-stage stator blades while ensuring high reliability, and takes into account the problems of the structural functionality of the fan / compressor, the characteristics of the composite material itself, the processing technology, and the assembly technology.

[0046] As Figure 1 shown, the multi-stage casing for an aero-engine lightweight compression component includes two split casings 1. The split casing 1 includes a semi-circular metal functional frame 2 and its composite material plate 3, as Figure 2 shown.

[0047] The metal functional frame 2 includes a front mounting edge 21, a rear mounting edge 22 opposite to the front mounting edge 21, and a plurality of adjustable stator blade mounting rings 23 arranged between the front mounting edge 21 and the rear mounting edge 22. The split mounting edges 24 are connected to both ends of the front mounting edge 21, the rear mounting edge 22, and the adjustable stator blade mounting rings 23, as Figure 3As shown, there are two adjustable stator vane mounting rings 23.

[0048] The front mounting edge 21, the rear mounting edge 22, the adjustable stator vane mounting ring 23, and the split mounting edge 24 are integrally formed by machining or connected by welding.

[0049] The split mounting edges 24 of the two metal functional frames 2 are bolt-connected to form an integral ring structure, as Figure 4 shown.

[0050] The front mounting edge 21 and the rear mounting edge 22 are used to connect with the components before and after the casing. Specifically, bolt connection can be adopted, and a rabbet can be set on the front mounting edge 21 and the rear mounting edge 22 for positioning and centering with the components before and after the casing, as Figure 5 - Figure 6 shown.

[0051] The adjustable stator vane mounting ring 23 has a plurality of circumferentially distributed assembly holes and a plurality of positioning bosses 25 located on the outside, as Figure 7 - Figure 8 shown. The assembly holes are used to install the journal on the adjustable stator vane and can be designed to match the boss on the journal of the adjustable stator vane. Each positioning boss has a positioning hole communicating with the assembly hole. The positioning hole is designed with high precision and is coaxial with the assembly hole. It can ensure the positioning and accurate angle adjustment of the adjustable stator vane while assembling the journal on the adjustable stator vane. In addition, the positioning boss 25 has a local strengthening effect and can supplement the strength loss caused by opening the assembly holes on the adjustable stator vane mounting ring 23.

[0052] There are multiple composite material plates 3, as Figure 9 shown, which are arranged between the front mounting edge 21 and the adjustable stator vane mounting ring 23, between the adjustable stator vane mounting rings 23, and between the adjustable stator vane mounting ring 23 and the rear mounting edge 22.

[0053] The inner sides of the front mounting edge 21 and the rear mounting edge 22, both sides of the adjustable stator vane mounting ring 23, the inner side of the split mounting edge 24, both sides and both ends of the composite material plate 3 have mounting wings. Among them, the mounting wings on both sides of the composite material plate 3 are connected to the mounting wings on the inner sides of the front mounting edge 21, the rear mounting edge 22, and both sides of the adjustable stator vane mounting ring 23 by rivets or can also be connected by bonding; the mounting wings at both ends of the composite material plate 3 are connected to the mounting wings on the inner side of the split mounting edge 24 by rivets or can also be connected by bonding.

[0054] The mounting wings on the front mounting edge 21, the rear mounting edge 22, the adjustable stator vane mounting ring 23, the split mounting edge 24, and the composite material plate 3 are designed with a sufficient connection and matching range. And to compensate for the influence of punching on strength and stiffness, the mounting wings on it are strengthened on the basis of the thickness of the composite material plate 3. Specifically, the mounting wings on it can be designed to have a larger thickness, as Figure 10as shown

[0055] On the outer side of the inner mounting wing of the split mounting edge 24, there are a plurality of axially arranged reinforcing ribs 26, which can enhance the strength and containment capacity of the boundary part of the split mounting edge 24.

[0056] The composite material plate 3 mainly undertakes the functions of load bearing, transfer and formation of the pneumatic flow path, and can be made of a carbon fiber reinforced resin matrix composite material with high specific strength and high specific stiffness.

[0057] On the inner side of the composite material plate 3, there is an arc-shaped containment cavity, and a containment ring 31 is arranged in the arc-shaped containment cavity. The containment ring 31 is used to achieve the containment function of the casing, and can be made of a fiber reinforced composite material with better impact resistance such as aramid and polyimide.

[0058] Each composite material plate 3 and its containment ring 31 can select composite materials with corresponding temperature resistance according to the working temperature grade of the fan / compressor at the axial position where they are located.

[0059] The multi-stage casing for the lightweight low-temperature compression component of the aero-engine disclosed in the above embodiment is designed in a split form, which can overcome the problems of poor assembly and maintainability of the integral ring casing. And it is designed to connect the split mounting edge 24 with the metal functional frame 2, and drill holes in the metal functional frame 2 to install the adjustable stator blades, so as to avoid the reduction of the load-bearing capacity of the composite material caused by large-scale drilling on the composite material. And reinforcing ribs 26 are arranged on the split mounting edge 24, which can effectively compensate for the stiffness of the holes drilled in the split mounting edge 24 and the composite material plate 3, and compensate for the reduction of the containment capacity caused by the boundary effect of the containment ring 31. In addition, the composite material plates 3 are installed on the metal functional frame 2 in stages, and composite materials with corresponding temperature resistance can be selected according to the working temperature grade of the fan / compressor at the axial position where they are located. The high temperature resistance of the subsequent stages can be increased gradually according to the actual situation, instead of using a resin matrix composite material with higher high temperature resistance according to the highest temperature usage requirements, which can reduce the overall processing difficulty and manufacturing cost of the casing and improve the product quality.

[0060] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present application.

Claims

1. A multi-stage casing for a lightweight compression component of an aero-engine, characterized in that, It includes two split casings (1), and the split casing (1) includes a semi-circular metal functional frame (2) and its composite material plate (3); The metal functional frame (2) includes a front mounting edge (21), a rear mounting edge (22) oppositely arranged with the front mounting edge (21), and a plurality of adjustable stator vane mounting rings (23) arranged between the front mounting edge (21) and the rear mounting edge (22). Split mounting edges (24) are connected to both ends of the front mounting edge (21), the rear mounting edge (22), and the adjustable stator vane mounting ring (23); The split mounting edges (24) of the two metal functional frames (2) are bolt-connected to form an integral ring structure; The adjustable stator vane mounting ring (23) has a plurality of assembly holes distributed circumferentially; There are a plurality of composite material plates (3), which are arranged between the front mounting edge (21) and the adjustable stator vane mounting ring (23), between the adjustable stator vane mounting rings (23), and between the adjustable stator vane mounting ring (23) and the rear mounting edge (22); Mounting wings are provided on the inner sides of the front mounting edge (21) and the rear mounting edge (22), on both sides of the adjustable stator vane mounting ring (23), on the inner sides of the split mounting edges (24), on both sides and at both ends of the composite material plate (3). Among them, the mounting wings on both sides of the composite material plate (3) are riveted to the mounting wings on the inner sides of the front mounting edge (21), the rear mounting edge (22), and on both sides of the adjustable stator vane mounting ring (23); the mounting wings at both ends of the composite material plate (3) are riveted to the mounting wings on the inner side of the split mounting edge (24); The composite material plate (3) is made of carbon fiber reinforced resin matrix composite material; An arc-shaped accommodating cavity is provided on the inner side of the composite material plate (3), and an accommodating ring (31) is arranged in the arc-shaped accommodating cavity. The accommodating ring (31) is made of aramid or polyimide fiber reinforced composite material.

2. The multi-stage casing for a lightweight compression component of an aeroengine according to claim 1, characterized in that Each composite material plate (3) and its accommodating ring (31) are made of composite materials with corresponding temperature resistance capabilities according to the working temperature grade of the fan / compressor at the axial position where they are located. The high temperature resistance of the composite material plates (3) and their accommodating rings (31) at the subsequent stages gradually increases according to the actual situation.

3. The multi-stage casing for a lightweight compression component of an aeroengine according to claim 2, characterized in that The front mounting edge (21), the rear mounting edge (22), the adjustable stator vane mounting ring (23), and the split mounting edge (24) are integrally formed by machining or welded together.

4. The multi-stage casing for a lightweight compression component of an aeroengine according to claim 3, characterized in that Rabbet joints are provided on the front mounting edge (21) and the rear mounting edge (22).

5. The multi-stage casing for a lightweight compression component of an aeroengine according to claim 4, characterized in that A plurality of positioning bosses (25) are provided on the outer side of the adjustable stator vane mounting ring (23), and positioning holes communicating with the assembly holes are provided on each positioning boss.

6. The multi-stage casing for a lightweight compression component of an aeroengine according to claim 5, characterized in that On the outer side of the inner mounting wing of the split mounting edge (24), there are a plurality of reinforcing ribs (26) arranged axially.

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