A turbofan engine intermediate duct

Abstract

The application belongs to the technical field of intermediate duct design of turbofan engines, and particularly relates to a turbofan engine intermediate duct, which comprises an outer duct, an inner ring arranged in the outer duct, a plurality of support plates supported between the outer duct and the inner ring in a circumferential direction, an inner-duct-side splitter ring located at trailing edges of the support plates and formed with a plurality of inner-duct-side flow channel profile plates, each inner-duct-side flow channel profile plate being connected between two adjacent support plates and having a front end bent rearward, and an outer-duct-side splitter ring connected at a rear end of the inner-duct-side splitter ring and formed with a plurality of outer-duct-side flow channel profile plates, each outer-duct-side flow channel profile plate being correspondingly arranged above one inner-duct-side flow channel profile plate, having a front end inclined downward and extending into a position where a front end of the corresponding inner-duct-side flow channel profile plate is bent rearward, and abutting between the corresponding inner-duct-side flow channel profile plate and the position bent rearward.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of intermediate duct design of a turbofan engine, and particularly relates to an intermediate duct of a turbofan engine. BACKGROUND

[0002] The intermediate duct of the turbofan engine comprises an outer duct, an inner ring, a split ring and a plurality of support plates, wherein the inner ring is arranged in the outer duct; each support plate is supported between the outer duct and the inner ring in a circumferential direction; the front edge of the split ring has a plurality of notches, each notch is clamped to the rear edge of one support plate; the split ring forms an outer bypass flow channel with the outer duct and an inner bypass flow channel with the inner ring, and splits the airflow.

[0003] At present, in order to facilitate assembly and ensure the stiffness of the split ring, the split ring is mostly designed as a solid structure, and this kind of technical scheme has the following defects:

[0004] 1) The solid split ring has a relatively large weight, so that the turbofan engine has a relatively large mass as a whole, which is inconsistent with the current requirement of weight reduction of an aero-engine;

[0005] 2) The solid split ring has a relatively large weight, and needs to be fixed by a large number of fasteners, which will further cause the turbofan engine to have a relatively large mass as a whole.

[0006] The present application is proposed in view of the existence of the above technical defects.

[0007] It should be noted that the disclosure of the above background art content is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present patent application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0008] The purpose of the present application is to provide an intermediate duct of a turbofan engine to overcome or alleviate at least one aspect of the known technical defects.

[0009] The technical solution of the present application is:

[0010] An intermediate duct of a turbofan engine comprises:

[0011] an outer duct;

[0012] an inner ring arranged in the outer duct;

[0013] a plurality of support plates supported between the outer duct and the inner ring in a circumferential direction;

[0014] The inner content side flow ring is located at the trailing edge of each support plate, and a plurality of inner content side flow channel profile plates are formed on the inner content side flow ring; each inner content side flow channel profile plate is connected between two adjacent support plates, and the front end is bent rearward;

[0015] The outer content side flow ring is connected at the rear end of the inner content side flow ring, and a plurality of outer content side flow channel profile plates are formed on the outer content side flow ring; each outer content side flow channel profile plate corresponds to cover above an inner content side flow channel profile plate, and the front end is inclined downward to extend into the position where the front end of the corresponding inner content side flow channel profile plate is bent rearward, and abuts between the corresponding inner content side flow channel profile plate and the rearward bent position.

[0016] According to at least one embodiment of the present application, in the above-mentioned intermediate nacelle of the turbofan engine, the inner content side flow ring and the outer content side flow ring are connected by bolts and positioned by a stop.

[0017] According to at least one embodiment of the present application, in the above-mentioned intermediate nacelle of the turbofan engine, the position where the front end of each outer content side flow channel profile plate is inclined downward is in contact with the inclined surface between the corresponding inner content side flow channel profile plate and the rearward bent position.

[0018] According to at least one embodiment of the present application, in the above-mentioned intermediate nacelle of the turbofan engine, the side wall of each support plate has a clamping groove;

[0019] The two side edges of each outer content side flow channel profile plate are clamped into the clamping groove on the side wall of the corresponding support plate.

[0020] According to at least one embodiment of the present application, in the above-mentioned intermediate nacelle of the turbofan engine, the outer nacelle, the inner ring, the inner content side flow ring, and each support plate are integrally formed. BRIEF DESCRIPTION OF DRAWINGS

[0021] Fig. 1 is a structural schematic diagram of the intermediate nacelle of the turbofan engine provided by the embodiments of the present application;

[0022] Fig. 2 is a three-dimensional schematic diagram of the intermediate nacelle of the turbofan engine provided by the embodiments of the present application;

[0023] Among them:

[0024] 1-outer nacelle; 2-inner ring; 3-support plate; 4-inner content side flow ring; 5-outer content side flow ring.

[0025] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size, and in addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present patent. DETAILED DESCRIPTION

[0026] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described below in conjunction with the drawings. It should be understood that the specific embodiments described herein are only partial embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0027] In addition, unless otherwise defined, the technical terms or scientific terms used in the present application description should be the general meanings understood by the general technical personnel in the field of the present application. The words indicating the direction or position relationship such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the present application description are only used to indicate the relative direction or position relationship, but not to imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and the relative position relationship may also change accordingly when the absolute position of the described object changes, therefore it cannot be understood as a limitation on the present application. The "first", "second", "third" and the like used in the present application description are only for the purpose of description, to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" or "the" and the like used in the present application description should not be understood as an absolute limitation on the quantity, but should be understood as the existence of at least one. The "including" or "containing" and the like used in the present application description means that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and do not exclude other elements or objects.

[0028] In addition, it should be further noted that, unless otherwise explicitly specified and limited, the "mounting", "connection", "connection" and the like used in the present application description should be understood in a broad sense, for example, the connection can be a fixed connection, or a detachable connection, or an integral connection; can be a mechanical connection, or an electrical connection; can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements, and the person skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0029] The technical solutions of the present application will be further described below in conjunction with the drawings Figs. 1-2 The present application will be further described below.

[0030] A turbofan engine intermediate nacelle, comprising:

[0031] An outer nacelle 1;

[0032] An inner ring 2 arranged in the outer nacelle 1;

[0033] A plurality of support plates 3 are supported circumferentially between the outer casing 1 and the inner ring 2;

[0034] An inner bypass side split ring 4 is located at the trailing edge of each support plate 3, and a plurality of inner bypass side flow channel profiles are formed on the inner bypass side split ring 4; each inner bypass side flow channel profile is connected between two adjacent support plates 3, and the front end is bent rearward;

[0035] An outer bypass side split ring 5 is connected at the trailing end of the inner bypass side split ring 4, and a plurality of outer bypass side flow channel profiles are formed on the outer bypass side split ring 5; each outer bypass side flow channel profile covers the corresponding inner bypass side flow channel profile from above, and the front end is inclined downward to extend into the position where the front end of the corresponding inner bypass side flow channel profile is bent rearward, and abuts between the corresponding inner bypass side flow channel profile and the bent position.

[0036] For the intermediate casing of the turbofan engine disclosed in the above embodiment, those skilled in the art can understand that the design of the outer casing 1, the inner ring 2, and the support plate 3 forms the load-bearing structure of the intermediate casing, which is stable and reliable as a whole. On this basis, the split ring is composed of the inner bypass side split ring 4 and the outer bypass side split ring 5, the inner bypass side flow channel profiles formed on the inner bypass side split ring 4, and the outer bypass side flow channel profiles formed on the outer bypass side split ring 5, which construct the inner flow path profile of the outer bypass and the outer flow path profile of the inner bypass, and the whole is a hollow structure, which can effectively reduce the overall weight of the aero-engine. Each inner bypass side flow channel profile is connected between the corresponding two adjacent support plates 3, realizing reliable connection of the split ring as a whole at the trailing edge of each support plate 3. Moreover, the cross section of the inner bypass side split ring 4 and the inner bypass side flow channel profiles thereon is L-shaped, and the cross section of the outer bypass side split ring 4 and the outer bypass side flow channel profiles thereon is L-shaped, which are hooked together. In addition, the front end of each inner bypass side flow channel profile is inclined downward to extend into the position where the front end of the corresponding inner bypass side flow channel profile is bent rearward, and abuts between the corresponding inner bypass side flow channel profile and the bent position, so that the combination between the inner bypass side split ring 4 and the outer bypass side split ring 5 is reliable.

[0037] In some optional embodiments, the intermediate casing of the turbofan engine disclosed above, the inner bypass side split ring 4 and the outer bypass side split ring 5 are connected by bolts, and are positioned by a stop.

[0038] In some optional embodiments, the intermediate casing of the turbofan engine disclosed above, the inclined part of the front end of each outer bypass side flow channel profile downwardly, and the inclined surface between the corresponding inner bypass side flow channel profile and the bent position, can reliably support between the corresponding inner bypass side flow channel profile and the bent position, and can reduce the micro-friction and avoid damage caused by excessive friction.

[0039] In some optional embodiments, the intermediate casing of the turbofan engine disclosed above, the side wall of each support plate 3 has a clamping groove;

[0040] The two side edges of each outer side flow channel type plate are clamped into the clamping grooves on the side walls of the corresponding support plate 3 to be closely combined with the corresponding support plate 3, so as to reduce the possibility of gap between the corresponding support plate 3, ensure the overall performance of the aero-engine, and ensure the reliable connection of the splitter ring at the rear edge of each support plate 3, avoid the occurrence of severe vibration, and affect the overall performance of the aero-engine.

[0041] In some optional embodiments, in the above-mentioned intermediate nacelle of the turbofan engine, the outer nacelle 1, the inner ring 2, the inner side splitter ring 4 and each support plate 3 are integrally formed to constitute a stable force bearing frame of the intermediate nacelle.

[0042] Each embodiment in the specification is described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts between each embodiment can be referred to each other.

[0043] So far, the technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings. It should be understood by those skilled in the art that the protection scope of the present application is obviously not limited to these specific embodiments. Without deviating from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the related technical features, and the technical scheme after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A turbofan engine intermediate casing, characterized in that, include: Outer casing (1); The inner ring (2) is installed inside the outer casing (1); Multiple support plates (3) are circumferentially supported between the outer casing (1) and the inner ring (2); The inner side flow divider ring (4) is located at the rear edge of each support plate (3), and multiple inner side flow channel plates are formed on it; each inner side flow channel plate is connected between two adjacent support plates (3), and the front end is bent backward; The outer duct side split ring (5) is connected to the rear end of the inner duct side split ring (4), and multiple outer duct side flow channel plates are formed on it; each outer duct side flow channel plate covers one inner duct side flow channel plate, and the front end is inclined downward and extends into the part of the corresponding inner duct side flow channel plate that is bent backward, and abuts against the part of the corresponding inner duct side flow channel plate and the part that is bent backward. The downward-sloping front end of each outer duct side flow channel plate makes contact with the inclined surface of the corresponding inner duct side flow channel plate and the backward-bending part.

2. The turbofan engine intermediate casing according to claim 1, characterized in that, The inner duct side split ring (4) and the outer duct side split ring (5) are connected by bolts and positioned by a stop.

3. The turbofan engine intermediate casing according to claim 1, characterized in that, Each support plate (3) has a slot on its side wall; The two sides of each outer duct side flow channel plate are inserted into the slots on the side wall of the corresponding support plate (3).

4. The turbofan engine intermediate casing according to claim 1, characterized in that, The outer casing (1), inner ring (2), inner side flow divider ring (4), and each support plate (3) are integrally formed.

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