An adaptive variable cycle aeroengine inner and outer bypass annular valve control mechanism

Abstract

The application belongs to the technical field of design of control mechanisms of annular valves of self-adaptive variable cycle aero-engines, and particularly relates to a control mechanism of annular valves of self-adaptive variable cycle aero-engines, which comprises an outer casing with a through hole, a splitter ring arranged in the outer casing and forming an outer channel with the outer casing and an inner channel in the splitter ring, a side wall of the splitter ring having an injection hole, an annular valve abutting against the splitter ring, a guide rail connected to the inner side of the outer casing and arranged in the axial direction, a linear bearing sleeved on the guide rail and connected to the annular valve, a transmission shaft arranged through the through hole, a connecting rod having one end hinged to the annular valve and the other end hinged to one end of the transmission shaft extending into the outer casing, and an actuating cylinder hinged between the outer wall of the outer casing and one end of the transmission shaft exposed outside the outer casing to drive the transmission shaft to rotate and then drive the splitter ring to move in the axial direction through the connecting rod, so as to open or close the injection hole.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of design of a control mechanism for an annular valve of an adaptive variable cycle aero-engine, and particularly relates to a control mechanism for an annular valve of an adaptive variable cycle aero-engine. BACKGROUND

[0002] The adaptive variable cycle aero-engine controls the distribution of flow between the inner and outer ducts by controlling the movement of the annular valve along the axial direction to open or close the injection holes on the split flow ring, so as to adapt to different flight states of the aircraft and keep the aero-engine in a relatively optimal performance.

[0003] Currently, in the adaptive variable cycle aero-engine, a sliding groove is formed on the stator structure, and the annular valve is arranged in the sliding groove, so that the driving mechanism drives the annular valve to move along the axial direction in the sliding groove to open or close the injection holes on the split flow ring. However, this technical solution has the following defects:

[0004] The annular valve and the sliding groove are in surface contact, and the relative movement has a large friction force. In addition, under high temperature conditions, uncoordinated deformation is prone to occur, and jamming is prone to occur. In the case of a large machining size tolerance, this problem is particularly prominent.

[0005] The present application is proposed in view of the above technical defects.

[0006] It should be noted that the disclosure of the above background art 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

[0007] The purpose of the present application is to provide a control mechanism for an annular valve of an adaptive variable cycle aero-engine to overcome or alleviate at least one aspect of the known technical defects.

[0008] The technical solution of the present application is:

[0009] A control mechanism for an annular valve of an adaptive variable cycle aero-engine, comprising:

[0010] An outer casing having a through hole thereon;

[0011] A split flow ring arranged in the outer casing to form an outer duct with the outer casing and an inner duct therein, and having injection holes in the side wall thereof;

[0012] An annular valve abutting against the split flow ring;

[0013] A guide rail is connected to the inner side of the outer casing and arranged in the axial direction.

[0014] A linear bearing is sleeved on the guide rail and connected to the annular valve.

[0015] A transmission shaft is arranged through the perforation.

[0016] A connecting rod is hingedly connected to one end of the annular valve and the other end of the transmission shaft exposed in the outer casing.

[0017] An actuating cylinder is hingedly connected between the outer wall of the outer casing and the end of the transmission shaft exposed in the outer casing, so as to drive the transmission shaft to rotate and further drive the annular valve to move in the axial direction through the connecting rod, thereby opening or closing the ejecting hole.

[0018] According to at least one embodiment of the present application, the annular valve is attached to the inner side of the split ring.

[0019] According to at least one embodiment of the present application, the annular valve is attached to the inner side of the split ring.

[0020] According to at least one embodiment of the present application, the annular valve is attached to the inner side of the split ring.

[0021] The guide rail is connected to the inner side of the outer casing through bolts at both ends, and a distance sleeve is sleeved on the bolt.

[0022] According to at least one embodiment of the present application, the annular valve is attached to the inner side of the split ring.

[0023] The linear bearing is installed in the bearing mounting hole.

[0024] According to at least one embodiment of the present application, the annular valve is attached to the inner side of the split ring.

[0025] An actuating cylinder support is connected to the outer wall of the outer casing and hingedly connected to the actuating cylinder.

[0026] According to at least one embodiment of the present application, the annular valve is attached to the inner side of the split ring.

[0027] An outer rocker arm is hingedly connected between the end of the transmission shaft exposed in the outer casing and the actuating cylinder.

[0028] An inner rocker arm is hingedly connected between the end of the transmission shaft exposed in the outer casing and the end of the connecting rod away from the annular valve.

[0029] According to at least one embodiment of the present application, in the adaptive variable cycle aero-engine inner and outer bypass annular valve control mechanism described above, the outer wall of the annular valve has a connecting joint connected to the end of the connecting rod towards the annular valve.

[0030] According to at least one embodiment of the present application, in the adaptive variable cycle aero-engine inner and outer bypass annular valve control mechanism described above, the guide rail and its corresponding component structure have multiple circumferential distributions.

[0031] According to at least one embodiment of the present application, in the adaptive variable cycle aero-engine inner and outer bypass annular valve control mechanism described above, the actuator cylinder and its corresponding component structure have multiple circumferential distributions. BRIEF DESCRIPTION OF DRAWINGS

[0032] Fig. 1 is a schematic diagram of the adaptive variable cycle aero-engine inner and outer bypass annular valve control mechanism provided by the embodiments of the present application;

[0033] Fig. 2 is a partial schematic diagram of a part of the adaptive variable cycle aero-engine inner and outer bypass annular valve control mechanism provided by the embodiments of the present application;

[0034] Fig. 3 is another partial schematic diagram of a part of the adaptive variable cycle aero-engine inner and outer bypass annular valve control mechanism provided by the embodiments of the present application;

[0035] Wherein:

[0036] 1-outer casing; 2-splitter ring; 3-annular valve; 4-guide rail; 5-linear bearing; 6-transmission shaft; 7-connecting rod; 8-actuator cylinder; 9-distance sleeve; 10-actuator cylinder support; 11-outer rocker arm; 12-inner rocker arm.

[0037] 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. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the patent. DETAILED DESCRIPTION

[0038] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further described in detail below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the usual 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.

[0039] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as having the common meaning to those of ordinary skill in the art to which the present application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the description of the present application indicate relative directions or positional relationships and are not intended to imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and the relative positional relationship can change accordingly when the absolute position of the described object changes, and therefore cannot be understood as a limitation on the present application. The words "first", "second", "third" and the like used in the description of the present application are only for the purpose of description and are used to distinguish different components, and cannot be understood as indicating or implying relative importance. The words "one", "an" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the number, but should be understood as the presence of at least one. The words "including" or "containing" and the like used in the description of the present application mean that the elements or objects appearing before the words are encompassed by the elements or objects listed after the words and their equivalents, and other elements or objects are not excluded.

[0040] In addition, it should be noted that, unless otherwise specified and limited, the words "mounting", "connecting", "connecting" and the like used in the description of the present application should be understood broadly, for example, the connection can be fixed connection, or detachable connection, or integral connection; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the connection between two elements, those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0041] The following will be described in detail in combination with the accompanying drawings Figs. 1 to 3 The present application will be further described in detail.

[0042] An adaptive variable cycle aero-engine inner and outer bypass annular valve control mechanism, comprising:

[0043] The outer casing 1 has a perforation thereon;

[0044] The shunt ring 2 is arranged in the outer casing 1, and forms an outer bypass between the outer casing 1 and an inner bypass formed therein, and the side wall has an injection hole;

[0045] The annular valve 3 is attached to the shunt ring 2;

[0046] The guide rail 4 is connected to the inner side of the outer casing 1 and arranged in the axial direction;

[0047] The linear bearing 5 is sleeved on the guide rail 4 and connected with the annular valve 3;

[0048] Transmission shaft 6, provided with a through hole;

[0049] Connecting rod 7, one end of which is hinged to annular valve 3, and the other end of which is hinged to one end of transmission shaft 6 extending into outer casing 1;

[0050] Actuating cylinder 8, hinged between the outer wall of outer casing 1 and the end of transmission shaft 6 exposed to outer casing 1, so as to drive transmission shaft 6 to rotate, and further drive annular valve 3 to move axially through connecting rod 7, so as to open or close the injection hole, in the process, the assembly of guide rail 4 and linear bearing 5 provides support for the axial movement of annular valve 3, and the guide rail 4 and linear bearing 5 are in rolling friction, the friction is small, and has a certain self-alignment ability, and is not easy to be stuck, which can effectively ensure the stability of the axial movement of annular valve 3.

[0051] In some optional embodiments, the self-adaptive variable cycle aero-engine inner and outer channel annular valve control mechanism described above has a plurality of injection holes distributed in the circumferential direction, and the specific number and distribution position thereof can be determined by relevant technical personnel according to specific actual conditions when applying the technical solutions disclosed in the present application, and no further detailed description is made here.

[0052] In some optional embodiments, the self-adaptive variable cycle aero-engine inner and outer channel annular valve control mechanism described above, annular valve 3 abuts against the inner side of split ring 2 to ensure the sealing performance between the abutting parts of annular valve 3 and split ring 2.

[0053] In some optional embodiments, the self-adaptive variable cycle aero-engine inner and outer channel annular valve control mechanism described above, guide rail 4 is connected to the inner side of outer casing 1 through bolts at both ends, and can be used in cooperation with self-locking nuts, locking plates and other accessories, a distance sleeve 9 is sleeved on the bolt, and the position of guide rail 4 in the radial direction can be adjusted by adjusting the effective length of distance sleeve 9, so as to facilitate the installation of guide rail 4 and linear bearing 5.

[0054] In some optional embodiments, the self-adaptive variable cycle aero-engine inner and outer channel annular valve control mechanism described above, the outer wall of annular valve 3 has a bearing mounting seat, and the bearing mounting seat has a bearing mounting hole;

[0055] Linear bearing 5 is mounted in the bearing mounting hole.

[0056] In some optional embodiments, the self-adaptive variable cycle aero-engine inner and outer channel annular valve control mechanism described above further comprises:

[0057] Actuating cylinder support 10 is connected to the outer wall of outer casing 1 and is hinged to actuating cylinder 8.

[0058] In some optional embodiments, the self-adaptive variable cycle aero-engine inner and outer channel annular valve control mechanism described above further comprises:

[0059] The outer rocker arm 11 is hinged between the exposed end of the transmission shaft 6 in the outer casing 1 and the actuating cylinder 8, and transmits power between them.

[0060] The inner rocker arm 12 is hinged between the end of the transmission shaft 6 extending into the outer casing 1 and the end of the connecting rod 7 facing away from the annular valve 3, and transmits power between them.

[0061] In some alternative embodiments, the annular valve 3 has a connecting rod connecting joint on its outer wall, which is hinged to the end of the connecting rod facing the annular valve 3.

[0062] In some alternative embodiments, the guide rail 4 and its corresponding component structure have multiple circumferential distributions, and the specific number and distribution positions can be determined by relevant technical personnel according to specific actual conditions when applying the technical solutions disclosed in the present application, and no further detailed description is made here.

[0063] In some alternative embodiments, the actuating cylinder 8 and its corresponding component structure have multiple circumferential distributions, and the specific number and distribution positions can be determined by relevant technical personnel according to specific actual conditions when applying the technical solutions disclosed in the present application, and no further detailed description is made here.

[0064] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other.

[0065] The technical solutions of the present application have been described in conjunction 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 solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. An adaptive variable cycle aeroengine inner and outer bypass annular valve control mechanism, characterized by, It comprises: An outer casing (1) with a through hole; A splitter ring (2) arranged in the outer casing (1) to form an outer channel with the outer casing (1) and an inner channel in it, and the side wall of which has an injection hole; A ring valve (3) abutting against the splitter ring (2); A guide rail (4) connected to the inner side of the outer casing (1) and arranged in the axial direction; A linear bearing (5) sleeved on the guide rail (4) and connected with the ring valve (3); A transmission shaft (6) arranged through the through hole; A connecting rod (7) one end of which is hinged to the ring valve (3) and the other end of which is hinged to the end of the transmission shaft (6) exposed in the outer casing (1); An actuator (8) hinged between the outer wall of the outer casing (1) and the end of the transmission shaft (6) exposed in the outer casing (1) to drive the rotation of the transmission shaft (6), and further drive the ring valve (3) to move in the axial direction through the connecting rod (7), so as to open or close the injection hole; An outer rocker arm (11) hinged between the end of the transmission shaft (6) exposed in the outer casing (1) and the actuator (8); An inner rocker arm (12) hinged between the end of the transmission shaft (6) exposed in the outer casing (1) and the end of the connecting rod (7) away from the ring valve (3); The injection hole has a plurality of circumferential distribution; The guide rail (4) and its corresponding component structure have a plurality of circumferential distribution.

2. The adaptive variable cycle aero-engine inner and outer channel ring valve control mechanism according to claim 1, wherein the ring valve (3) abuts against the inner side of the splitter ring (2).

3. The adaptive variable cycle aero-engine inner and outer channel ring valve control mechanism according to claim 1, wherein the guide rail (4) is connected to the inner side of the outer casing (1) through bolts, and a distance sleeve (9) is sleeved on the bolts.

4. The adaptive variable cycle aero-engine inner and outer channel ring valve control mechanism according to claim 1, wherein the outer wall of the ring valve (3) has a bearing mounting seat with a bearing mounting hole; The linear bearing (5) is mounted in the bearing mounting hole.

5. The adaptive variable cycle aero-engine inner and outer channel ring valve control mechanism according to claim 1, further comprising: An actuator support (10) connected to the outer wall of the outer casing (1) and hinged to the actuator (8).

6. The adaptive variable cycle aero-engine inner and outer channel ring valve control mechanism according to claim 1, wherein the outer wall of the ring valve (3) has a connecting rod connecting joint hinged to the end of the connecting rod towards the ring valve (3).

7. The adaptive variable cycle aero-engine inner and outer channel ring valve control mechanism according to claim 1, wherein the actuator (8) and its corresponding component structure have a plurality of circumferential distribution. ​ ​ ​ ​ ​ ​

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